SCIENTIFIC ABSTRACT SHERSTYUK, A.F. - SHERSTYAK, B.N.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R001549310010-7
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: November 2, 2016
• Document Release Date: August 9, 2001
• Sequence Number: 10
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT

SH3RSTYUK, Anatoliy A "dorovich; VIWITSKIY, G., red.; DANILINA, A.,
. . takhn. red. - ~ ' - --- "
[People's Bulgaria is blooming.] Rastsvetaet narodnaia Bolgariia.
,-.Moskva, Gos.izd-vo polit.lit-ry, 1959. 110 p. (MIRA 12-:9)
(Bulgaria--Politics and government)
(Bulgaria-Bconomic conditions)

15-57-4-4631
Translation from: Referativnyy zhurnal, Geologiya, 1957, Nr 4,
pp 92-93 (USSR)
AUTHOR: Sherstyuk, A. I.
TITLE: Fluorite and Stilbite From the Rezh Region (Flyuorit i
desmin iz Rezhevskogo rayona)
PERIODICAL: Tr. Sverdl. gorn. in-ta, 1956, Nr 26, pp 104-107.
AFSTRACT: In the Rezh region fluorite-bearing quartz-muscovite
and plagioclase veins with epidote-phlogopite and
fluorite-muscovite pyritized borders occur near
granites, in gabbro-amphibolites, amphibolites, and
amphibolite schists. The fluorite foram thin veinlets
of lilac color in micaceous borders and also formless
accumulations of deep violet and rose colors. Bands
of deep-violet fluorite occur immediately next to the
muscovite borders. Toward the center of the vein they
give way to light-violet, rose, colorless, and milky-
white bands. Along the eastern contact of the granites
Card 1/2 in the Rezh region pegmatite veins are found that

Fluorite and Stilbite From the Rezh Region (Cont.)
15-57-4-4631
contain quartz, feldspar, stilbite, fluorite, and muscovite. Sheaf-
like aggregates of white stilbite tinged with yellow occur in a
massive granular aggregate of albitized feldspar, and form from 20
to 30 percent of the total quantity of the feldspar mass. The
stilbite aggregates reach 3 cm in length. The mineral has a glassy
luster, a hardness of 3 to 4, and a negative elongation. Ng = 1.501,
Nm = 1.498~ Np = 1.494; Ng - Np = 0.007. Tfte mineral is optically
negative and has a 2V of 330. It decomposes in HC1 with separation
of powdery silica. In the granular aggregate of feldspar, a very
few small grains and crystals of fluorite are found with the stilbite.
These are predominantly octahedral in outline and light--green in
color. The border parts of the crystals have a lighter color than
the central parts. Occasionally small cubic crystals of fluorite arE
encountered. Small grains and crystals of fluorite locally grow on
granular aggregates of quartz. The fluorite crystals are younger
than the tectonic movements and formed from hydrothermal solutions,
which also produced albitization and zeolitizat.-on of the potassium
feldspars.
Card 2/2 G. A. G.

SMLSTYUK, A. 1.
-ft4"L'6~~
Effect of isomorphous admixtures in beryl on its refractive
index. Nauch.dokl.vys.shkoly-, geol.-geog.nauki no.2:51-56 '58-
(MIRA 12:2)
1. Sverdlovskiy gornyy inatitut, kafedra mineralogii.
(Beryl) (Mineralogy, Determinative) (Refractive index)

SHFMTYUK, A.I.
Metasomatic changes in basic and ultrabasic rocks near the
high-temperature pneumatolith-hydrotheimml veins. Izv.vys.
ucheb.zav;geol. i razv. 1, no.8:43-51 Ag'.161. (MIRA 14:9)
1. Sverdlovskiy gornyy institut iraeni V.V. Vakhrusheva.
(Ural hfountaln region-Metasomatism.)

SHERSTYUK, A.I.
Amazonite and fluorite from the Murzinskiy granite Massif.
Trudy Gor.-geol.inst. IYAR SSSR no.56:81-83 161. (KIRA 15:7)
(Rezh District-Amazonstone)
(Rezh District-Fluorite)

ACCESSION NR: AT4019300 S/0000/63/003/001/0119/0122
AUTHOR: Tudorovskaya, N. A. Sherstyuk, A. 1.
TITLE: Study of the process of catalyzed crystallization by the method of differential
thermal analysis
SOURCE: Simpozitan po stekloobraznomu sostoyaniyu. Leningrad, 1962. Stekloobraznoye
sostoyaniye, vy*p. 1: Katalizirovannaya kristallizatsiya stekla (Vitreous state, no. 1:
Catalyzing crystallization of glass). Trudy* simpoziuma, v. 3, no. 1. Moscow, lzd-vo
AN SSSR, 1963, 119-122
TOPIC TAGS: thermal analysis, glass, glass crystallization, petalite, spodumene,
catalyzed crystallization, titanium dioxide, alumina silicate
ABSTIIACT: The thermal cifect of crystallization was Investigated In glasses of the
Sys-tern 1i 0-.A 1203-SiO2 having the composition of petatite or spodumene with admixtures
of Ti02 aZ other oxides in amounts less than 10% by weight. X-ray and mineralogical
sis showed that in glass having a composition close to spodumene, the first thermal
analy 6
effect is produced by the crystallization of the high-temperature spodumene. The
presence of the second high-temperature effect shows that a second, more refractory
Card 1/2

ACCESSION NR: AT4019300
phase is also crystallized in these glasses. For the two glasses investigated (glass 13
with 5% Ti02 and spodumene glass), thermograms were obtained at a hearing rate of 2-29.'
degrees/minute. The time during which the thermal effect disappears completely at a
given temperature of exposure determine the rate of crystallization of the glass at this
temperature. For glass 13, the effect of Ti02 (1-11% by weight) on the thermal effect
was also investigated, thermograms being plotted at a heating rate of 7 degrees/min. Oli
the basis of the amount and character of the exothermal effects on the thermogram, the
amount of each crystal.lized phase could be determined. Surface crystallization and overall.
crystallization could also be distinguished on the thermograms. The relative amount of j
crystal-lized phase was calculated from the ther7nograms by the method fa A. G. Vlasov,'
and A. I. Shersb
yuk. Orig. art. has: 2 figures and 2 tables.
ASSOCIATION: None
SUBMITTED: 17May63 DATE ACQ: 21Nov63 ENTCL: 00
SUB CODE: WIT NO REF SOV: 001 OTHER: 000
Card 2/2

ACCESSION NIL- AT4019299 S/0000/63/003/001/0116/0119
AUTHOR; Vlasov, A.G.; Sherstyuk, A. L.
TITLE: Theoretical Investigation of the possible use of the method of differential thermal
analysis for the quantitative study of the crystallization process
SOURCE: Simpozium po steldoobraznomu sostoyaniyu. Leningrad, 1962.
Soeldoobraznoye sostoyaniye, vy*p. 1: Katalizirovannaya kristallizatsiya stekla. (Vitreous
state, no. 1: Catalyzing crystallization of glass). Trudp simpoziuma, v. 3. no. 1.
0
Moscow, Izd-yo AN SSSR, 1963, 116-119
TOPIC TAGS: crystallization, thermal analysis, thermogram, glass
ABSTRACT: The method of differential thermal analysis used hitherto is unsuitable for the
accurate determination of the amount of crystallized phase, which is absolutely essential for
the study of the nature and dynamics of crystallization. For this purpose, new experimental
methods are suggested mid formulas are derived. The logarithm of the temperature
difference 0 is plotted against time in typical curves obtained from 'the thermograms. The
study of these diagrams showing the relationship between 0 and t makes it possible to de~
termine all the thermal characteristics of the test sample. Another very important value
Card.1/2

ACCESSION NR: AT4019299
is 1~ , the specific thermal effect of the reaction, which is proportional to the amount of
noncrystalline phase. By comparing the 6 values obtained for different substances, the
degree of crystallization of the material in relation to its preliminary treatment can be
established.
y. increasing the rate of heating, tmax becomes less dependent on tX (reaction
rate), thus decreasing the accuracy of the estimation of 04, by the time of maximum deviation.
In practice, the accuracy of the values o~ and 6 is � 10%. The accuracy of the calculation
can be improved considerably by a more accurate solution of the thermal conductivity
equation with the given limiting conditions and nonstationary heat sources uniformly distri-
buted inside the sample. The function of the heat sources F (t, T) win also have some
IrLAependent parameters, which must be determined experimentally. Orig. art. has-, 1
figure and 14 formulas.
ASSOCIATION: none
SUBMITTED: 17May63 DATE ACQ: 21Nov63 ENCL: 00
SUB CODE: MT, GC
NO REF SOV: 000 OTHER: 000
2/2

TUDOROVSKAYA, N.A.; SHE&MUP A.Is
St.udying 'the Droc(jp- of catalyzed crystallization by the method of
differential therral analysis. StAkloobr. sont. no.1:119--i-22 163.
(MIRA

(,,al imn Vnes. ml P,. ob-va
011'',.i". lpol
tu L
~~orny-i ins lcafedra pe trograf ii

A AT
SHE
q
"J'onstruction of the Characteristics of Multistage Axial and Centrifugal
0
Compressors According to the 3tage Characteristics".
Kotloturbostroyeniye, No. 1, ppil-16, 1953
The method suggested ky the suthor is based on the following two
assumptions: 1. The abstract characteristics -- dependence of the Co-
efficients of stress and efficiency upon the consumption coefficient -
are indentival for all stages. 2. The relative temperature change before
any stage ab all points of the characteristic is less than 0.15. In ac-
cordance with the givon abstract characteristics of a stagep an auxiliary
conditional characteristic is constructed in logarithmic coordinates. This
makes it possible to determine the efficiency coedfiency coefficient for
various peripheral velocitied of the rotor. (RZhMekh, No 8, 1955)
SO: Sum No 812, 6 Feb 1956

i,~,, of vents, rumps
nation of ',,'-e res-.' s,-ar,3.Y in thie orerat-
-,e det L it 1-nermy by nces o- ile U--,
ci,
ajj~, roj:j-r~:,3or.-,. _Ln,_-
jepartni-ent 0 i~-.,-iinical Sciences3 institute of 1955-

SSILIZUE6,J~1eksandr Nikolayavich; SAMOYLOVICH, G.S.. radRktor; VORONIN,
K.F. Te!-h-nTCAh"eRkiy- redaktor.
[Axial flow compressors; aerodynamic calculational Osev~-- kompresec-
ry; aerodin ichaskiy-raschet. Moskva, Gos.izd-vo, 1955. 247 P.
(Air compressors) (MIRA 8:4)

1A A - AID P - 2566
Subject USSR,/I;ngineering
Card 1/1 Pub. 110-a - 5/16
Author Sherstyuk, A. N., Kand. Tech. Sci.
Title Method of approximate calculation of curvilinear canals
Periodical Teploenergetika, 8, 26-29, Ag 1955
Abstracts A method for estimating potential compressible and
incompressible flow in curvilinear canals is presented
on the basis of mathematical analysis. It is mentioned
that this method was devised by G. Flyugel and later
developed by G. Yu. Stepanov. Seven diagrams. Two
Russian references, 1953, 1954.
Institu'-on : Moscow Power Engineering Institute
Submitted : No date

A, &I
7.t
for steady operation. its magnitudc is indicated by creattas A
R. Tleske, USA

KIRSANOV, Igor' Nikolayevich; SHSRSTYUK, A.N., redaktor; VOROHIN, K.P.,
tekh-nicheskiy redaktor-------------.,,
[Stationary steam turbines] Statsioaarnye parovye turbiny. Moskva.
Gos.energ. izd-vo, 1956. 199 p. (MIRA 9:11)
(Steam turbines)

AID P - 4384
Subject USSR/Power Engineering
Card 1/1 Pub. 110 a - 10/17
Author Sherstyuk, A. N., Kand. Tech. Sci. Moscow Power Institute
Title On.calculating centrifugal blowers and pumps
Periodical Teploenergetika, 5, 47-51, MY 1956
Abstract A mathematical analysis to facilitate the choice of
dimensions and revolutions of fans and pumps_Is tresented.
Two diagrams. Four Russian references, 1950 195 -
Institution : None
Submitted : No date

68/12/12 533-691A3
Calculation of Aerofo:Ll Profiles Izv..AJrad. Nauk, Ot-L
--bs-onic Speed t a Id 1. "Tauk.
1'8),12 -1277
5
4 N Sherst 1956
U. S. S. R.
,he bas'-d-MR-of the method of smLU distiLrbaaces is used
~o c~alculate the distribution of velocity aand speed ozi the
L
Tn-f - in comprussitble fluid using the kncwn di-stribution
c-- vcIc,;ity aqd p---assur-- on the profile in incompres bla
fl-~Lid. The deformation of the DroMe is assumed
By transforming the ecruatlons the preoi--ion of
M:tlhod has bo,,jn L--p-rcved. The method is also apIlicable
:)f' a 1.~tttlica of' slightly er- d 1 fil s.
cam' 3 ro a

446
,/,PHASJ I BOOK E OITATION
>
e sandr -Nikolayevic
Sherstyuk,
Ventilyatory I dymososy fVentilators and Exhaust Fans) Moscow, Goae-
nergoizdat, 1957. 183 P. 7,000 copies printed.
Ed,: Nevellson, M.I.; Tech. Ed.: Medvedev, L.Ya.
PURPOSE: This,is a textbook on blowing engines for students. of power
engineering institutes and it may also be useful to engineers en-
gaged in designing and operating such equipment.
COVERAGE: This book deals with design and operation of exhausters and
fiins. Special emphasis is placed on forced draft fans used in
heat power plants. The book contains contributions of the Heat
Engineering Department of the Moscow Power Engineering Institute.
The author begins with the basic concepts of hydraulics and
proceeds to the use of models for fan design and selection.
Operation and testing of fans are also discussed. One chapter is
devoted to modern types of fans and exhausters manufactured in
Card 1/8

Ventilators and Exhaust Faiis
3. Fan performance characteristics
Ch. II. Centrifugal Fans
1. Working principle of centrifugal fans
2. Derivation and analysis of Euler's formula
3. Centrifugal fan wheel
4. Radial grids
5. Determining the basic dimensions of a fan-wheel
6. Spiral-type casing
7. Design of centrifugal fans
8. Variable working conditions of centrifugal fans
Card 3/18
446
15
19
21
23
25
30
33
36
40

Ventilators and Exhaust Fans 446
3, Flat grids. Construction of profiles 60
4. Forces acting on grid profiles 63
5, Grid efficiency 67
6. Experimental data for flat-grid design 68
7. Axial-flow fan wheel 71
8. Axial-flow-fan guiding and straightening elements.
Collectors and diffusers 77
9. Blade element efficiency, hydraulic efficiency and
overall efficiency of axial-flow fans 8o
10. Designing axial-flow fans 82
Card 5/8

V-ixtllators and Exhaust Fan~ 446
Combined performance of several fans 11.0
Pan control I T 11
Ut-.. 7111. Types of Fans and Exhausters
1. Types of centrifugal fans based on, All-Union State
Standard 5976-55 130
2. Cent,rifugal fans and exhausters 131
3. 'Selecting exhausters and fans by catalog 143
!~. Remodeling centrifugal fans 148
5. Ax1al-flow fans 150
Ch. VIII. Testing and Operating Fans and Exhausters
1. Testing exhauster-s and fans 155
C'~Drd -11"/18

SPERSTY(TKI A' . N.
KOR YCHUX, Hikolay Karpovich; CHERNOV, Aleksandr Vasil'yevich; *AUj&&%ZX,
A.M.. 11suchnyy redaktor; ROGACHEV, F-V-, redkaktor; RAKOV, S.I.,
a nicheakiy redaktor
LKachiner7l Mashinovedenie. Moskva, Vaes.ucbabno-pedagog. izd-vo
Trudrezervizdat, 1957. 439 p. (RLRA 10:8)
(Engines)

__
i
REVELISON, M.I., kand. tekhn. man ; SHERSTYUK, A.R., kand. teldin. nauk.
Modeling centrifugal fans. Bnergomashinostroenie 3 no.10:18-19 0 157.
(Fans, Mechanical--Models) (M]MA 10:12)

AUTHOR: Sherstyuk, A. N. (Moscow). 24-4-18/34
TITLE: Potential flows past profiles of confusor and diffusor
cascades at sub-sonic speeds. (Potentsiallnoye obtekaniye
profiley konfuzornykh i diffuzornykh reshetok pri
dozv-ukovykh skorostyakh)..
PERIODICAL: "Izv. Ak .. Nauk, Otd. Tekh. Nauk"(Bulletin of tile Ac. SC.,
Technical bciences bectionT,77'957, No.49 pp.123-126 (USSR).
ABSMCT: A variant of the method of Khristianovich (1) is given
which permits increasing the accuracy of calculation of
cascades at high sub-sonic speeds.- If the parameters of
the flow of the incompressible liquid are knownp it is
easy to determine according to Fi,~.2 the speed of the gas
X and then, by means of eq. (3.2), p.125, to determine
the lines of the flow and the equipotential lines of the
gas flow. Changes in the cascade pitch and in the profile
setting angle can be determined accuratelypirrespective of
the shape of the profile; the pitch of the profileg t p
can also be easily-determined. There are 2 figures and 2
Russian references.
SUBMITTED: August 29, 1956.
AVAII,4BLE:
Card 1/1

IMITSKIY. V.V. [deceased], doktor tekhn. nauk, prepodavatell; SOKCLOVI,
Yee*Ya., doktor tekhn. nauk, prepodavatell; LIBIM. P.D., doktor
tekhn. nauk, prepodavatell;-GIMMIYARB, K.L., kand. tekhn. nauk,
prepgdavatell;'L&VROV, N.V., dokbo*r tekhn. nauk, prepodavatell-
IVANTSOV, Gepe, kL~nd. tekhn. nauk, prepodavatell;'GOLUBKOV, B.N.,
SM q'PYITw-.AwJ[,r-ka
kand. tekhn. nauk, prepodavatell; nd tekhn.
nauk, prepodavat'll; N3KITIN,'S.P., kand. tekhn,* nank, prepodamqlell~
CHISTYAMT, S.F., kand. tekhn. nauk., prepodavatell; WDNIKDVq Ye.G.0..
dokbor tekhn. nauk, prepodavatwell; BUUASTOV, A.M., ka~td. tekhn.
nauk, prepodavatell; VIMU, M.I., kand. tekhn. nark, prepodLx-atell;.
GAWIMOV, S.G., prof., red.; XAGAN, Ya.A., dote.. red.~;' ATZINSHM,
I.I., red.; VOROWIN, K.P., tekhn. red.; LARIONOV, G.Yee", tekhn. red.
[Heat engineering handbook] Teplotekhnicheskii spravochnik. Moskva,
Gos. energ. izd-vo. Vol.2. 1958. 672 pe- (JaRA 11:1,0)
(Heat engineering)

SOV/24-58-4-11/39
AUTHORS: samoylovich~ G.S. and Sherstyuk, A.N. (Moscow)
TITIE,; The Calculation of Curvilinear Axisymmetric Channels
(Raschet krivolineynykh osesimmetrichnykh kanalov)
PERIODICAL: Izvestiya Akademii Nauk SSSR, Otdeleniye Tekhnicheskikh
Nauk, 19581 Nr 4, pp 78 - 81 (USSR)
ABSTRACT: A method is described for the approximate calculation
of the potential flow of an incompressible fluid in
axisymmetric curvilinear channels (the intakes of
centrifugal and axial compressors, diffusers at the
exhausts of axial compressors, etc.). The calculation
is based on a generalisation of the method of calculating
plane curvilinear channels (Ref 1). There is a comparison
between the calculated results and exact solutions. Good
agreement is obtained. There are 5 figures and 1 Soviet
reference.
ASSOCIATION: Moskovski energeticheskiy institut (Moscow Power
Institute5
SUBMITTED: October 24, 195?
Card 1/1

DEYCH, M.Ye.: ZAffANKIN, A.Ye.-, SHERSTYUK, A.N.; DINEYEV, Tu.N.
Investigation of gate nechanisna of radial-flow turbines.
Hauch.dokl.vys.ahkmly; energ. no.4:195-206 158.
(NIRA 12-5)
1. Rakomandovana kafedroy parovykh i gazovykh turbin Moskovskogo
energqtichnnkogo instituta.
(Gas turbines)

A M I ORR Sherstyu1c, A.11. (Cand. Tech. Sci.
TITLE: The desiffn of aerodynamic gratings at high subsonic 4-peeds.
(Raschet aerodinamichesltikh reshetok pri boj'shikh'dozvukovykh
skorostyakh.)
PERIODMIL: Teploenergetika, 1958, No.3. pp.14-16 (USSR)
ABSTRACT: Available methods of designing aerodynamic -ratings at high subsonic
speeds are laborious and rather inaccurate. Simpler available
methods are not accurate enough close to the inlet and outlet edges
of the blade. This short article describes a simple approximate
method applicable to the design of gratings with small relative
blade pitch. The design procedure is as follows: the velocity
distribution over the profile is given for an incompressible liquid
and the corresponding velocity distribution with a gas is found.
Calculation of the potential flow of an incompressible liquid may be
made by existing analytical procedures or by an analogue method.
The potential flow of gas at high subsonic speeds is considered
(See Fig.l.) The equation of motion of the gas is given in a
previously published form. Simplifying assumptions are stated mid
a graph that may be used to simplify the calculation is given in
Fi-.2. The length of the equipotential line on the blade is
determined graphically as shown in Fig.3. Satisfactory agruement is
Card 1/2 claimed between calculated and test data. By way ol example Fi,;.4.

The design of aerodynamic gratings at high subsonic speeds. 96-3-4/26
shows experimental and calculated data for the velocity
distribution on .-rids of turbine blading. There are 4 figures,
3 literature references (Russian).
'Joscow Power Institute (Moskovskiy Energetic Jaes'kiy Instiiut).
AVAILU, U-: ijibrary of Congress.
Card 21/2

SHERSTTUK, A.N., kand.tekbn.nauk
Selecting the size of air drums for piston compressors. Vest.
mash. 38 no.9:18-19 S 158. (MIRA 11:10)
(Air compressors)

25M PHASE I BOOK EMOITATION SOV/3027
Sherstyuk, Aleksandr Nikolayevich
Kompressory (Compressors) Moscow, Gosenergoizdatp 1959- 190 P- Brrata
slip inserted. 17,000 copies printed.
Ed.: D.S. Rasskazov; Tech. Ed.: N.I. Borunov.
PURPOSE, This textbook is to be used for the general course, Air-blowing Ma-
chinery. It may also be used by designers and engineers.
COVERAGE: The fundamentals, theory, design, and operation of centrifugal,
axial,, and piston compressors.are discussed. Information on rotary
compressors and the mounting and installing of piston compressors is
presented. No personalities are mentioned, There are 64 references:
52 Soviet, 10 English, and 2 German.
TABIE OF CONTENTS:
Preface
3
Card l/ 5

Compressors SOV/3027
Ch. IjI. Axial Compressors 66
3-1. Arrangement of an axial compressor 66
3-2. Characteristic features of high-velocity flow in a plane Xcid 67
3-3. Stage of an axial compressor 75
3-4. Determining axial velocities in a stage of an arial compressor 81
3-5. Designing the stage of an axial coppressor 84
3-6. Designing axial compressors 88
3-7. Constructions of axial compressors 94
Ch. IV. Characteristics of Axial and Centrifugal Compressors, Mods3ing 103
4-1. Basic distinguishing features of characteristics 103
4-2. Dimensionless and reduced characteristics 108
4-3. Recalculation of characteristics in the case of changes in speeds
or inlet gas temperatures 113
44. Recalculation of characteristics because of changes.in the physical
properties of the working substance 117
4-5. Combined operation of compressor and the delivery system. Pulsation 121
4-6. Constructing characteristics of compressorir with interstage cooling 126
4-7. Design of compressors by the similitude method 128
Card 3/5

Compressors SOV/3027
7-2. Indicator diagrams of piston compressors 166
7-3. Determining the productivity and power consumption of piston com-
pressors 169
7-4. Determining basic dimensions of piston compressors 172
7-5. Regulating piston compressors 174
7-6. Constructions of piston compressors 176
7-7. mounting piston compressors 178
7-8. Testing piston compressors 183
7-9. Starting and servicing piston compressors 184
7-10. Comparing types of compressors* 186
Bibliography 188
AVAIIAME: Library of Congress
VK/jb
card 5/5 2-24-6o

SHERSTYUK, A.-N.
Dpsign of main gas pipelines. flauch.dokl.vys.shkoly; energ.
no.1:181-187 '59. (MIRA 12-5)
1. Rekomendovana kafedroy okononiki promyshlennosti i organiEataii
predpriyatiya Moskovskogo enargeticheskogo Ingtituta.
Waa-Pipelines)

SOV196-59-6-51422
L nces)
AUTIHOR: Sherstyuk, A.N. (Candidate of Technica" Saie.
TITLE: Loss DJ~ermlnaflon in Turbine Blades with Thick outlet
Edges (K opredeleniyu poter' v turbinnykh reshetkakh
s utoishchennymi vykhodnymi kromkami)
PERIODICALss Teploenergetika., 1959, Nr 6, pp 26-28 (USSR)
ABSTRACT: In gas turbines, when the in-let gas temperature exceeds
700 to 750 OC it is necessary to cool the stator and
.-otor bladings. Several effective methods of blade
cooling necessitate the use of thickened profilesq
particularly at the outlet edges. This thickening of the
outlet edges may cause appreciable losses which it is
necessary to evaluate. Little work has been published on
this subject, though Flyuge--' in his book on Steam
Turbines published in 1939 gave expression 0.) which is
ar. empiri-cal formula for the loss due to thickening of
the blade edges. A theoretical formula for the edge
losses 4n straigh-1--edged blading was given by G.Yu.
-L 0
Stepanov. It is in good agreement with experimental data
but is very difficult to use be--ause it requires
expe;imental determination of the pressure at the blade
Card 1/3 edge. A new 'theoretical- solution of this problem is then
given, with reference to -the blading diagram of Fig lo

sov/96-59-6-5/22
Loss Determination in Turbine Blades with Thick Outlet Edges
Zrle outlet -angle of the flow is given b7 the approximate
k .1 -on (3) is given foz the
empirical formula (2). Expressi
effective -.o-idth of the throat between the blades. Ann
expression -'~.s then derived. ignoring compressibility, for
the totall energy losses on going from section I-I to 2-2
(see Fig 1). Expreszion (5) is t-hen easily deri-,ed for
t"he *value a.-f the edge loss. Graphs of thq edge loss as a
fluactica of -t-he outiet-edge thickness and inter-blade
channel geometry are gi-.Tezi in Fig -2: each curve corres-
ponds to a par"A,3ular va::as of the ratio of elffeQtive t o
theoretical throa`%; width. The dotted graph on Fig 2
~_,or_rezponds t-,; Loo-Lmala (1) . In order to check the
acvaracy of fo=ula 15) a compay-ison was made between
experimental and calu-ulate,i dara for a nimber of blade
Drofiles. The results of the calculations are given in
Pigs LL and 1~, and arg briefly d~~scussed. It is
Considered 4~ufiat in all cases the agresment betwaen test
Card 2/3 and calaulated data. is satisfa._-tory. Moreover~

sov/96-59-6-5/22
Loss Determination in Turbine Blades with Thick Outlet Edges
formula (5) explains the observed dependence of the edge
loss on the relative pitch of the blading.
There are 5 figures and 2 Soviet references.
ASSOCIATION; Moskovskiy energeticheskiy institut
(Moscow Power Institute)
Card 3/3

-1.1
0001/0.,3000 SOV/016--9-11-.14/22
AUTHORS: Deych, M. Ye., Doctor of Technical Sciences,
Zaryankin, A. Ye., and Sherstyuk, A. N... Candidates
of Technical Sciences
TITLE: New Designs of Nozzle Blading for Supersonic Speeds
CD
PERIODICAL: Teploenergetika, 1959, Nr 11, pp 65-68 (USSR)
ABSTRACT: There is a need for high-efficiency nozzle blading for
supersonic speeds. Expanding nozzle blade profiles
developed in recent years are of high efficiency under
designed operating conditions 9 but the efficiency falls
off rapidly when the conditions are changed. This will
be seen from curve 1 of Fig 1 which gives profile
losses as function of Mach number for expanding nozzles
type TS-2V. At the design condition of Mach 1.6 the
losses are only 10%, but at Mach 1 they become 31%.
Normal nozzles with contracting channels work well only
at moderate supersonic speeds; see, for example, curve
4 in Fig 1. Methods of reducing the losses at
supersonic pressure-drops may be evolved from the
formulae for the change of direction of flow in the skew
section of the nozzles. To this end sections before and
after the nozzle are considered, as shown in Fig 2.
Card 1/4 The equations of continuity, conservation _)f energy and

665YO
SOV/96--59--11-14/22
New Designs of Nozzle Blading for Supersoni,-- Speeds
condition are applied to these two sections and formula
(1) is derived for the relationship between the flow
conditions before and after the blading. From this
formula it is easy to determine the change of direction
of flow in the skew section of the nozzle at supersonic
pressure drops, and formula (2) accordingly is derived.
If an experimental relationship between the velocity
ratio and pressure ratio is used. formula (2) is very
accurate. The accuracy is evident from Fig 3, where
experimental values are compared with values calculated
by formula (2). It has been shown that in nozzles with
expanding channels, for example those of the Moscow
Power Institute, the mean angle of discharge does not
depend much on the operatinS conditions. For this case
formula (2) may be used to determine the relationship
between the velocity coefficient and the pressure ratio,
as seen in Eq (3). The comparison of theoretical and
experimental results given in Fig 4 confirms the good
agreement. This agreement was obtained without detailed
Card 2/4 analysis of the nature of flow in the blading, Hence,
L11(

_V" -
SOV96-59-11-14/22
New Designs of Nozzle Blading for Supersonic Speeds
if the blading is made in such a way that the discharge
angle does not depend on the operating conditions, then
the losses must inevitably rise when the Mach number
is decreased. In this case the losses depend only on
the loss under design conditions of operation and on
the pressure ratio. This conclusion served as a
criterion of blade shape for supersonic pressure-drops.
The blade shapes should ensure variable discharge angle
on change of pressure-ratio and, therefore, the discharge
portion of the rear of the blade should be slightly
bent so as to increase the discharge area. Such blade
profiles differ from ordinary nozzle blades with
contracting channels only in the shape of the back face
of the blades. A group of new blade profiles that meet
this requirement are shown in Figs 5 and 6. Loss as a
function of Mach number for the new profile TS-2RV is
plotted in curves 2 and 3 in Fig 1. It will be seen
that for blading of similar efficiency at 1.5 the new
blading has much lower losses at lower Mach numbers.
Blade shape TS-lRV is recommended for nozzles where the
Mach number is 1.3 and blade shape TS-2RV when the Mach
Card 3/4 number is 1.5. Blades with backs of the new shape should

66570
SOV/96-59-11-14/22
New Designs of Nozzle Blading for Supersonic Speeds
be used for guide vanes and working blading in stages
with long blades, and in particular for the last stages
of condensing turbines which operate at high super-
critical heat-drops. In the root section of such stages,
the velocity at the outlet from the guide vanes is, as
a rule, appreciably higher than the speed of sound. The
discharge angle from runner blades is also supersonic near
the periphery. As the last stages may operate under very
variable conditions, both guide vanes and rimner blades
should have a curved back in the skew section., There
are 6 figures, 2 tables, and 2 Soviet references.
ASSOCIATION: Moskovskiy energeticheskiy institut (The Moscow
Power Institute)
Card 4/4

30244
/.,9
S/145/60/000/002/012/020
D221/D302
AUTHOR: Sherstyuk, -A_N_-r--,1andidate of Technical Sciences
TITLE: Calculating speeds in rotors of radial turbines
PERIODICAL: Izvestiya vysshikh uchebnykh zavedeniy. Mashino-
stroyeniye, no. 2, 19609 124 - 133
TEXT: The author proposes a simplified method of calculating the
speed of flow by reducing the three-dimensional problem 'to two di-
mensions. Three problems of practical interest are quoted. The
first concerns a rotor with straight blades (Fig. 1). Dotted li-
nes represent the curvilinear part of the blades calculated by
usual methods when Coriolis forces are insignificant. The flow in
the main part of the channel can be considered as taking place in
meridional sections. An elementary volume dv is considered, on
which The following forces are acting: Centrifugal in the relative
motion; centrifugal in the transfer motion and force thaT is pro-
duced by the ---Zference of pressures. The publication mentioned pro-
vides the approximate solution of speed distribution as i)e.-
C a r d I

3r'2111i
C2/012/020
st)ct2.~,S 1C, 107101,"- 0- 2-' /3',02
D
w
w a 2
E - k 1 h
(2)
where wa is the speed a- point A, other members being ratios of
sl-ze parameters of the -L-lemen-U. The author cites the graph of
speed ratio, it should *-)e remembered that speeds at different meri-
dional seclions differ from each other due to various speeds w a.
Mathematical analysis is included to support this view. The expres-
Sions are valid for the flow of compressible non-viscous fluid.
-Paialyticall equations are given for a non-compressible fluids They LA
allowg together with the above mentioned expressions determination
of speeds in all sections, except the small sections of inlets and
outlets of the channels,, The same method can be applied for calcu-
!ating ro-,ors with any shape of blades; the equations, however,
are too complicated. In the general case, 4;_-. is expedient to limit
-Ihils by determining the averaged speeds in the peripheral direct-
lon. A d_`Ifferentiai equation which determines the absence of mo-
Tions along the or-thogonals h (Fig. la), is worked out in a simi-
C a _- d ---' I/ -)

30244
S/145/60/000/002/012/0 20
Calculating speeds in rotors of D221/D302
lar manner to the previous case. Check computations of single sta-
ge radial turbines and compressors demonstrate that the field of
meridional projections of speeds is irregular. Vhen the disc and
ring are flat then the flow in the rotor can be considered as Dlane
parallelp thus reducing the problem to two dimensions. Mathema~i-r
cal equations are quoted for the above. In order to assess speeds
near the inlet and outlet edges,-it is necessary to elongate the
boundary lines of the stream inside the flow. Using equations ob-
tained to investigate the flow in channels between blades, impor-
tant deductions can be made. In particular, it must be noted that
the effect of Coriolis forces has a different effect on flows in
radial turbines (centripetal and centrifugal). The irregularity is
increased in the first instancep but improved in the case of cen-
trifugal motions. This should be taken into consideration when pro-
filing rotor blades. There are 5 figures and 4 Soviet-bloc refe-
rences.
ASSOCIATION: Moskovskly energeticheskiy institut (Moscow Power
Institute)
SUBMITTED: December 15, 1959
Card 311~5

S/024/60/000/02/022/031
E194/F.155
AUTHOR: Shers,tIyuk A.,N. (Moscow)
TITLE: On the Determination of Losses in 4urbine Bladine when
the Angle of Attack is Incorrect
PERIODICALs Izvestiya Akademii nauk SSSR, Otdeleniye tekhnicheskikh
nauk, Energetika i avtomatikaj 19607Nr 2,pp 177-180 (USSR)
ABSTRACT: Existing methods of assessing the losses that occur when
the angle of attack is not as designed are seldom
accurate for all types of blading. This brief article is
concerned with deriving improved formulae. The simple
case of thin straight flat blading is first considered,
neglecting compressibility and friction losses. The
diagram of Fig 3 is used in deriving the loss formula
when the angle of attack is not the same as the angle of
installation of the flat blading. The effect of the
discrepancy corresponds to a pressure drop, which may be
calculated by expression (2.1) and expression (2.2).
The latter coincides with Carnot's formula for the loss
Card of pressure when the section of a flow is suddenly in-
1/3 creased. The parameters of flow beyond the blading may
be calculated with allowance fcr compressibility, and

S/024/60/000/02/022/031
E194/E155
On the Determination of Losses in Turbine Blading when the Angle
of Attack is incorrect
Eq (3.1) is derived. Similar methods may be used to
derivo a formula for determining the losses in radial
blading with thin straight blades, giving expression
(4.1) for an incompressible fluid. Real turbine blades
are then considered; since the inlet edge is rounded,
the pressure loss is less than that given by Eq (2.2).
A correction factor is then introduced, as in expression
(5.1), and an appropriate value of this factor is
recommended for modern blade profiles. Expression (5.2)
is then derived for the relationship between the velocity
factor with the designed angle of inlet and with other
angles. The practical value of formulae (5.1) and (5.2)
depends on the validity of the blading correction factor
when the angle of attach and the types of profile arc
changed. Some idea of the accuracy of formula (5.2),
assuming a constant correction factor, may be obtained
Card from Fig 5, which compares experimental and calculated
2/3 data for three blades, two active and one reactive. The
satisfactory agreement between theory and calculations ir~o

S/02)+/60/000/02/022/031
E19VE155
On the Determination of Losses in Turbine Blading when the Angle
of Attack is Incorrect
these cases shows that formula (5.2) may be recommended
for determination of the velocity factor.
There are 5 figures and 3 Soviet references. 0
SUBMITTED: November 9, 1959
Card 3/3

69384
S/129/6o/ooo/o6/001/0 2.2
E073/E535
AUTHORS: Silayev, A.F., Fedortsov-Lutikov, G.P. and Sheshenev,M.F.
Candidates of Technical Sciences
TITLE: Properties of Castings1lof the Steel 12KhllV2NMF-L J~
PERIODICAL: Metallovedeniye i termicheskaya obrabotka metallov,
1960, Nr 6, pp 2-7 (USSR)
ABSTRACT: Use of austenitic steels for cast components of turbines
and fittings operating at 600 and 6100C is inadvisable
due to their high cost, low thermal conductivity and
relatively poor technological properties. Therefore,
intensive research work is being carried out in various
countries to develop for this purpose pearlitic class
steels and steels with 11 to 13% chromium. Investigations
showed that if properly alloyed, pearlitic steels, and
particularly stainless chromium steels of the type
lKhl3, are suitable for operation in this temperature
range. The subject of the work described in this paper
was to determine the effectiveness of small additions
of horophilic elements (barium, calcium, cerium) on the
Card 1/4 properties of type 12KhllV2NMF steel. For the purpose
U"y

69384
S/129/60/000/06/ool/022
B073/E535
Properties of Castings of the Steel 12KhllV2NMF-L
of comparison, one melt (7-104) was produced without
any additions. The chemical compositions of the
commercial heats used in the experiments are entered
in Table 1. Optimum heat treatment for this steel
proved to be as follows: homogenization at 1090 + 10OC;
normalization at 1050 + 10OC; tempering at 700 + 100C
followed by cooling in the furnace. It was found that
in the case of continuous cooling from the range of the
austenitic state with speeds below 250OC/hr, there will
only be pearlitic transformation, whilst for larger
cooling speeds (250 to 3000OC/hr) pearlitic, and
intermediate transformations take place. The plot,
Fig 1, contains data on the mechanical properties of
this steel at 200C for a melt containing AI-Ba-Ce
alloying additions. The plot, Fig 2, shows the changes
in the impact strength of steel as a function of the
test temperature for material containing Al-Ba-Ce
addition's (curve a), for material without any additions
Card 2/4 (curve b) and for material with Ca additions (curve B) X

69384
S/129/6o/ooo/o6/001/022
E073/E535
Properties of Castings of the Steel 12KhllV2NMF-L
The relatively high structural stability of the material
is evident from the data on the changes of the chemical
composition of the residue produced by electrolytic
dissolution of the steel after various ageing regimes,
Table 2. Table 3 and Fig 3 show the results of long-run
strength tests'(up to 2600 hours) in the temperature
range 600 to 670*C; the highest values were obtained for
material containing small additions of Al-Ba-Ca. Under
all test conditions fracture of the specimens occurred
along crystallites which were intensively deformed in
the neighbourhood of the fracture,as can be seen from
the microstructure of a specimen fractured at 6100C
after having been stressed for 1011 hours with a stress
of 15 kg/mm . Fig 5 shows a plot of the creep limit
of steel at 6100C for steel containing only Ca additions
and for steel containing Al-Ba-Ca additions. The
following conclusions are arrived at:
1) Introduction into the steel of a small quantity of a
Card 3/4 Al-Ba-Ca alloy does not result in any pyro-effect, brings

69384
S/l29/6o/ooo/o6/ool/o22
E073/E535
Properties of Castings of the Steel 12KhllV2NMF-L
about a considerable improvement of the technological
properties of the tested steel, an increase in the impact
strength and ensures a higher degree of hardening in the
original state and a less intensive process of softening
during operation.
3) Introduction into steel of small quantities of Al-Ba-Ca
alloys leads to a reduction of the nonun�formity in the
properties along the cross-section and this appears to be
due to a greater uniformity of the structure, which leads
to a reduction of the size effect.
3) Steel specimens from a 1.3 ton casting, produced with
a small addition of Al-Ba-Ca alloying material and
subjected to "soft" heat treatment, had the following
high temperature propertiest
6oo*c 2 6lo0c 2 61o0c 2
adrlo5 10 kg/mM a drl05 = 9 kg/mm ; an'l-10-5= 5.8kgAffim
(dr = do razrusheniya - to failure).
There are 5 figures, 3 tables and 3 Soviet references.
ASSOCIATION: TsNIITMASh
Card 4/4

S/096/6o 000/07/012/022
&7/ 23 V E194/E455
AUTHORS: Sherstyuk, A.N-, Candidate of Technical Sciences,
TITLE;
Zaychenk-6, Ye.N., Ignatlyevskiy, Ye.A. and
Sokolov, A.I., Engineers
An Investigation of Inlet Pipe Nozzles for S Centrifugal
Compressors
=3
56-59 (USSR)
1960,
PERIODICAL: Teploenergetika,
Nr 7, PP
ABSTRACT: The design of the inlet pipe influences the efficiency
of a compressor in two ways. Firstly, losses in ihe
inlet pipe itself directly reduce the efficiency of the
compressor. More important, the shape of the inlet pipe
influences the velocity distribution at inlet. to the
runner. If the distribution becomes unsuitable it can
appreciably reduce the efficiency of the runner because
the angles of attack at the inlet edge differ from the
required values. Despite the practical importance of
this question, little experimental work has been done
upon it. Accordingly, the present work gives the results
of the first stage of an investigation on axially-
symmetrical inlet pipes. The tests were made not on a
Card 1/5 compressor but on a special rig, illustrated in Fig 1,

s/o96/60/000/07/012/022
E194/E455
An Investigation of Inlet Pipe Nozzles for Centrifugal Compressors
which allows the influence of the runner to be excluded.
However, the outline of the duct beyond the inlet pipe
is made the same as in a normal runner in order to
obtain the required boundary conditions. Tests were
taken on 8 types of inlet pipe, 5 being axial and
3 radial. Sketches of the inlet pipes are given in
Fig 2. Combined data on the losses are also plotted in
the graphs of Fig 2 in each case as functions of
Reynolds number. Since Mach numbers were small (less
than 0.35), the test results were worked out without
allowing for compressibility. All the inlet pipes,
except type OR-80-V, have very low loss factors because
of the low values of Reynolds number and in all cases
there is an appreciable reduction in the losses as the
Reynolds number increases. As was to be expected, the
axial inlet pipe with the least losses is that in which
the ratio of the inlet diameter to the outlet section is
greatest. The greatest losses were obtained with the
cylindrical inlet pipes. The tests show the advantages
of using short cowls over the runner inlet. Data on the
Card 2/5 velocity distribution in the discharge section of the

S/o96/60/000/07/012/022
E194/F,455
An Investigation of Inlet Pipe Nozzles for Centrifugal Compressors
inlet pipe are also presented in Fig 2. The tests were
made for various values of average speed up to
110 metres/sec but because of the very slight influence
of the Reynolds number of the velocity distribution
Fig 2 gives mean curves. In all cases, except those of
the conical and cylindrical inlet tubes, there is marked
distortion of the velocity distribution. If the runner
were designed without allowing for this distortion, there
could be substantial reduction in efficiency. In the
axial inlet tubes, the velocity distribution depends on
the length of the cowl. It is most uniform with a cowl
of medium length and comparatively uniform with a
cylindrical inlet tube; but cylindrical tubes are not to
be recommended because of their inherently high losses.
Conical inlet tubes give a uniform velocity field and have
small losses. Thus they are the most suitable of the
axial inlet tubes, provided they can be accommodated in
the overall dimensions. Their main disadvantage is
their great length which can be overcome by making a
Card 3/5 profile of the kind illustrated in Fig 3. The results

6C-~48
s/o96/60/000/07/012/022
E194/E455
An Investigation of Inlet Pipe Nozzles for Centrifugal Compressors
with the radial and diagonal inlet tubes are of special
interest because these types sometimes have to be used
and it is obvious that the runner design must make
appropriate allowance for changes in the velocity
distribution. Moreover, inlet tubes of this kind should
not be used at high peripheral speeds because the Mach
number at the tips of the discharge edges of the runner
blades becomes excessive. One of the tasks of the work
was to evaluate the reliability of approximate methods of
calculating the velocity in relation to the design of
the inlet tubes. The point is that approximate methods
of calculating on curved channels are sufficiently
accurate only if the boundary of the channel changes
curvature smoothly. In the case under consideration,
the change in curvature is not smooth: from the
experimental results and velocity data given in Fig 4j
it is concluded that approximate methods of
calculation are not sufficiently accurate. Differences
between test and calculated velocities may be 10 to 20%
Card 4/5 and, therefore, in important cases the velocity should

S/096/60/000/011/017/018
E073/E135
AUTHORS: Deych, M.Ye., S~herst,yuk A N Zaryankin, A.Ye.,
Zatsepin, M.F.,---.Tna 2W0 to'~7'*L.B.
.U
TITLE: Investigation of Low Power Radial Turbines
PERIODICAL: Teploenergetika, 1960, No. 11, p 94
TEXT: This is an annotation of a recent research report by
MEI. The technique of calculation of radial turbines is considered,
giving experimental results on determining the influence of the
nozzle system, the outflow angle of the flow al and of the twist
of the runner wheel, on the economics of the turbine. An electronic
r.p.m. gauge is described. A method is presented of plotting
profiles of nozzle systems of radial turbines, their geometrical
dimensions and their experimental characteristics, and also data
on investigating five runner wheels of various types. A maximum
stage efficiency of rjoi = 0.32 was obtained. Theoretical
considerations are given on calculating the end losses in nozzle
lattices with a flow from the centre and towards the centre, and
also certain calculations on determining the optimum chord of
turbine profiles calculated for subsonic and supersonic flow speeds.
There are no figures, tables or references.
Card 1/1

SPERSTYU-K-,-- A-A-.-,
Reply to G.IU. Stepanov's remarks. Izv. AN SSSR. Otd. tekh. nauk.
Energ. i avtom. no.4:216 J1-Ag '61. MRA 14:9)
(Turbines)

s/143/61/1)00/002-/003/006
'V0 A207/A126
AUTHORS: Sherstyuk, A. N., Candidate of Technical Sciences, Sokolov. A. I.,
-n-%ineer
TITLE: Determination of the efficiency coefficient of the diffusion grids
from experimental data
PERIODICAL: F-nergetikallino. 2, 1961, 93 - 96
TIM. The authors derive the formulae for determirine the effic'iency coef-
ficient of a straight or radial diffusion grid from experimertal data. Graphs are
-ubmit-.ed which simplify the calculations considerably. Experiments were m e on
ad
straight compressor grids (profile packages) which led to -Tne mezhod*of determin-
ing the coefficient of 16sses described in this article. There are 2 figures and
2 Soviet-bloc references.
ASSOCIATION: Moskovskiy ordena Lenina energeticheskiy insti-cut, kafedra parovykh
i gazopakh turbin (The Moscow Order of Lenin Power Engineering Ins-
titute, Dpoartment of Steam and Gas 9"ur'b1nP.-,)
SUBM 1ITED: February-26, 1960
Card 1/1

TRUSOV, S.M., kand.tel:hn.nauk; SHFMTYUK, A.N., kand.takhn.rauk
Calculation of the field of velocities in a hydraulic torque
converter. Izv. vys. ucheb. za-v.; energ. 4,no.7:107-114-
01 161. (MIRA 14:7)
1. TSentrallnyy nauchno-issledovatelLskiy avtomobilInyy'i
avtomotornyy institut (for Trusov).* 2-. Moskovskiy ordena
Lenina energeticheskiy in6titut (for Sherstyuk).
(Hydraulic machinery)

ZARYPIIKIN, A.Ye., kand.tekhn.nauk; SHERSTYUK) A.N.., kand.tekhn.nauk;
ZATSEPIN, M.F.J. inzh.
Experimental characteristics of Francis-"type turbines.
Teploenergetilca 8 no.6:37-41 Je 161. (MIRA 14:10)
1. Moskovskiy energeticheskiy institut.
(Turbines-Testing)

- -1 -
S/143/62/00j/ /30-51/j06/0007
-let vo D238,/:)~02
ii., Candidlate of T~cl_nic-_a-'
:)I,DC On t
-a-res of r~, dial- f-, o,,.- allbilles
u I, L,_
c
13~:_ To- PrS.9-1,~il:h Lichabr-yk1r, zav ce -n-
lzve~3 Laya 1
- -, a 11 J
no. 5, _!~D62, 53-59
e o z~ u c 1- 1 i~ contIinU,'Lt_JO',I 01' ti-le woTI: _oubii6hed in the ijr_~-
OUS !SSL,Le -ils I, i I-Ire-ftce is ~-a-- for the
v 01 L odical uo which relf
1-iota-un-ons Lido )'ved in formulae . Ti~_, e Ul L:I Ue7, e-, I-Cle-10y is accord-
1 6 v - L ' oa_-a-_--,a-'U-cr x
---ven as a _tufict-ion of t'he sta'se reach-_' wn,
ad
a-~' t~-e --,eomietricai of the stac-s-e . ',,Ie S ua ~e el I J.-
.-u __ ::, ZD
cie-_,cY is -.'-en ded-uced, account oZ' t-he Liec-f.anical losses
u!
th-e bear7n-s and dis-',: los--es, yield-ing
I-rd 1/3 x

3/1 L3//62 /OJJ/Oj-z/jj-:- /337
Calculatin-1. ... D238./D30'2
102 G, 102
n e -b
GH
0 (2)
.:t-; N"
o e 0b 102 -q
U-
represents tl-e .2echan'Cal losses in bcari-n'-s a2--d
dis'r. losses. A L;tudy of particular cases L-vo' v--,- rad-fal
---nes de.:ion:j trates tu'l-le v-,riation in -e c,, -
s ua--: --aracu ---,i~--Uics wit"
U--
)ressu--Ie ratio . ThIree c'-1--"racteristic c;is~s ~re E, uudi-nd for
U-
the devilation in :-as coansum tion rated, con!:;idc-r-
u-
Card 2/3

S/I 4 3/62/000/00-5/006/007
D23~
SS4,ble fil at sub-criwical ve"Ocities, and
U__
0 i J, u 1' 0 Vu L U I M-I'CUla-~-ed
C~ I'Ves ci _u -60 :--ood on E~as consumptfo-- du ta one
-idi 'Ge
~3 :L.. -e of ~.L I'L tuu_,-bl ne me~',lod vie.Lds an aIM-0
-e ~aifi. c'-racterf tuics of a ra~ial---iow tu
L) e z3 ~;,a s c as rel-ctio.n, efficiency, --as consum-ption a-nd use-
fu, lculutlion~3 demonstrate subot-a-_-4
L ca, U n~lllzence
of ~;j-ed on consu.-.-,,.)t_ion. ~*_ fi-ure illub'ra-es -he des--*---.,n cha-
-D u u
ol- L~ rad-i--l axial turbine in --educed coord_i,.r,.uuuS
0.5; di = 16'; :-, 0 2 0.96;Y 2 = 0.9; 1).
2 = 30 0
C i _' T I Ol')7 arde, in'sulz u
IY I na- -Lenina
:'.oscow Order Ol Tenill
20,,.,er TrS4-jtute)
v.L
S-73,,7 I',', Tl~'D
u oril 7, !-"1
Card 3/3

SHERSTIUK, A.11., kand.tekhn.nauk, dotsent
Calculation of the characteristics of radial turbine stages.
Izv. vys. ucheb. VIV.; energ. 5 no.2:59-66 F 162. (MIRA 15:3)
1. Moskovskiy ordena Lenina energeticheskiy institut,
Predstavlena kafedroy parovvkh i gazovykh turbin.
(Turbines)

3751:4
3/09
6/62/000/005/001/009
E194/E454
z7aryankin, A.Ye., Candidate of Technical Sciences,
Sherstyuk, A.N., Candic41te of Technical Sciences,
-1-1 -T- -..9 k~
Zii Lscpin, -Ent-incer
71"TLE: Soi-.ie i-.avs of increasing the efficiency of mixed flow
turbines
PERICDICAL: Toplocnergetika, n6.:-., 1962, 32-35
At low pressure ratios (1.7 to 1-8) the efficiency of
r.iixed flow turbines is around 80'/'0, which it 4S importarft to 141
increase because small gas turbines of this type are widoly used.
When the ratio of the blade width to diameter is below 0.05
aDpreciable losses occur at discharge from the nozzles and runner
and due to disc friction. Nozzle efficiency can be increased by
mieridional profiling, that ismachining the blade with a twist in it,
which reduces the s-jeed and final pressure drops in the region of
i:',axii-,iu:-,i curvature of gas flow, However, in some cases
x-educing the losses a' subsonic speeds
Meridional profiling, wl~
:-,,,iy increase them at stipersonic speeds and -vIrhilst potentially very
advantageous, the subject requires much further experimental study.
Card 1/3

s/o96/62/000/005/001/009
So~:,.(_, i,,,ays of increasing ... E194/E454
bo coirrerted in the subsequent diffuser section. If the
turiiine disc'i,ir-as -to at.-.,,osphere a diffuser can reduce the
press-,:rc behind the runner so increasing the actual stage beat drop
an(-! increasing stage efficiency. Axially syi-mmetrical diffusers
directly beyond the runner are best but the discharge flow is often
irregular and then diffusers urhich operate well under uniform flow
condi*,-ions nre not always best. For instance, in practical tests
a curved diffuser was found better 'than a conical one although
static tests showed them to have equal performance. There are
7 figures.
ASSOCIATION: ',%,oslzovslciy energetichesiciy institut
(1,11oscow Power Engineering Institute)
Card 3/5

-qHFFSTyUli",,,H, (tIbskvu)
4proximate calculation of aeroA7nrmic cascades. Izv.AN SSSR.Otd,tekh.
n,gil Pbkh. i mashinostr. no.5.39-45 S-0 162. (MIRA 15:10)
(Cascad6s (Fluia dynamics)) - -' - :-'
I

38996
s/096/62/000/007/001/002
E191/E435
/ov,
AUTHORS: Sher_&t)aik_,_A_N_, Candidate of Technical Sciences
Novoderezhkin, V.P., Engineer
TITLE: Contribution to the determination of velocities in an
axial turbo-machine, taking into account the
curvature of the streamlines-in the axial cross-section
PERIODICAL: Teploenergetika,-no-7, 1962, 50-53
TEXT: The problem has been solved in principle but the solution
is laborious, requiring 2 sets of approximations. In the first
approximation, the axial velocity components are determined from
the given tangential components, ignoring.the curvature of the
streamlines in the axial cross-section. The c;ntin 'uity equations,
then yield the streamlines and their curvature. From this
curvature, another approximation of the axial components is
obtained. NASA Report No.955, 1950, contains an approkimate
formula for obtaining the second approximation streamlines from
the first so that a third approximation is unnecessary, but the
computations remain laborious. H. Petermann ("Konstruktion",
1$ 1956) has given an approximate solution dispensing with
Card 1/3

s/o96/62/000/007/001/002
Contribution to the determination ... E191/E435
computed with and without consideration of streamline~distortion,'
are compared. There are 3 figures.
ASSOCIATION: Moskovskiy energeticheskiy institut
(Moscow Power Engineering Institute)
Card 3/3

AL14016860 BOOK M[PLOITATION S/
Zaryankin, A. Ye.; Sherstyuk, A. N.
Low-pcuer radi-al-,axial turbines (kiaial'no-osevy*y& turbiny* maloy moshchrosti)
Moscalt, Mashgiz, 1963. 248 p. Illus., biblio. Errata slip inserted. 3000
copies printed. Reviewer: Professor 0. S. Zhiritskiy; Uanaging ediotr:
N. I-a. Zyugin; Publishing house editor: Engineer N. M. Paleyev; Technical
editor: A. F. Uvarova; Proofreader: Ye. Ko Shikunova; Cover artirt: Ye. V.
Beketova.
TOPIC TAU , radial-axial turbines., 10-,7power turbines, turbine
S-. radial turbines
stage, centripetal turbines, centrifugal turbines, turbine design.,aorodynamic
theory of turbines
PURPOSE k%'D COVERAGE: This book is intended for engineers and turbine specialists,-
concer-od -e.:Uh the design of radial-flow turbines. It also may be useful to
students at powar. and machine-desIgn vuzes in their study of turbine machinery.
The fundamentals of the theory and design of radial- and radial-exial-fla.7
turbines are preselted. Special attention is mid to Ongle-stage.low-power
radial-axial-flow turbines, -*hich have found wide application in r cant years.
Card 1/6
- -- --- -------------------------

AM4016860
The book'is based on the theoretical research of the authors and of other Russian
and foreign specialists. It contains experimental material, basically that of
the authors, on the testing of nozzle apparatuses.and turbine stages and the
influence of their geometry 6h.the efficiancy of stages. This book represents
one of the first attempts to systematiza the theory of radial-flcw turbines,
and contains only aerodynamic-de sign problems associsted with radial-flow turbineso
Engireer ?J. F. Zatsepin helped prepare paragraph 43,, Chapter VII, and, together
v,ith E-Zineer Yu. N. Dineyev, assisted with the experimental woek. Engineer
L. B. Frolov uss responsible for the development and application of the measure-
ment apparatus.
TABU OF CONT-ENTS-
Forenord 3
Ch. i. Certain information from aerodynamics
1. Equation of conservation of energy - -
2. Equations of motion (plano-parallel.1hlow)
3. Equations of motion in natural curvilinear coordinates (=ially sy=etrie
and plane-parallel flow) 15
carcQ/6

A=1680'0
1. Design of plane and axially sy=ctric airvilinear channels - 1?
5. 1',ethod and example of desi&ning a curvilinear channel - - 21
Ch. 1-1. Nozzle apparatuses
6. Straight and radial grids 26
7. Zhukov:;kiyls theorem for a radial grid 28
S. Designing the shape of nozzles for -ubcritical velocities in the-case of
flow tanard the center 34
9. Separation of a gas in the oblique section of nozzles in the case of super-
critical velocitics 39
10." -.nozzles for supercritical velocities in the case of flor, toward the center
43
11. Effect of the thickneGs of the outlet edge of shapes on the value of ~tha
velocity coefficient 4.6
12. End losses Ln radial-turbine nczzles 49
13. Opti= width of radial-turbine nozzles 57
14, aperimental investigation of radial-turbine 60
15. Geometric and aerodynamic characteristics'of test shapes - 64
Ch. Ill.. Radial-turbine impellers
16. Rotating radial grid 83
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~4-016860
7.
Equation of energy for a radial-turbine impeller 89
18. Impeller with cylindrical blades 91
19. Impeller losses in the case of nonrated attack angles 97
20. Disk losses 105
Ch. IV. Radial-axJal-turbine impellers
21. Impellers with blades with double curvature 109
22. Approximate determination of velociti-,3 in an Impeller with blades with dva-
ble cur7ature. Derivation of the fundamental differential equation 3.11
23. Determination of velccities in the impeller. Direct and reverse problems
115
21, Designing the shape of the meridian section 123
25. Simplified method of designing the shape of impeller blades 132
26. Designing the shape of Impellers with a given velocity field 139
27. An impeller with nonrated operating conditions 142
Ch. V. &perlmental Investigation of high-speed radial turbines
28. Statement of tha problem - - 145
29. Automodel flow Ln turbints 147
30. Description of experimental turbines of the radial type 149
326 Measuring apparatus 155
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A=16860
32. Experisefttal method and treatment of test results 165
Ch. VI. Singie-stage radial turbines
33. Radial-axial and centripetal turbines 170
34. Determination of fundamental over-all dimensions of a single-stage turbine -
- 172
3115. Detailed dasign of a single-stage turbine - - 178
36, -Sample dosign of a radial-axial turbine - - 184
37. Design and construction of single-ztage radial turbines 187
Ch. VII. Characteriet-Ics of a single-stage radial turbine
38. Statement of the problem. Fundamental simplifications 195
39. Degree of reaction of _n stage 198
40. Turbine efficiency - - 205
41. -Gas consumption through a turbine - - 210
Characteristics of a radial-axial t1arbine in standard coordinates 215
43.,~Eyperimental characteristics of single-zt.-ge turbines - - 216
441. ',Effect of radial clearance on the efficiency of a radial-axial turbine - 231
45. Effect of diffusers on the efficiency of a raduil-axial turbine - - 241
Literature 241
Card SZ/6

AM4016860
SUB CCDr: AP, PR
OMER: 007
Card 6/6
WDUll"IED; 20Apr63
DATE ACQ: 17Jan64
NR W 3OVi 056

----- -----
S/179/63/000/001/017/03-1
E031/E135
AUTHOR: Sherstyuk, A.N. Woscow)
TITLE; -(5-n the calculation of blade cascades for'subsonic
velocities
PERIODICAL: Akademiya nauk SSSR. Izvestiya. Otddleniye
tekhnicheskikh nauk Mekhanika i inashinostroyeniye
no.1, 1963, 138-14o
TEXT: The approximate method for. calculating blade cascades.,
-for an incompressible fluid, described in-an earlier paper of the...
aut.hor (Ref.l: Izv.AN SSSR, OTNt Energe'tika i 4vtouiatika, no.
1962) is 'generalized to the case of a Sas flow. The essential
point is the calculation on the -mean value ot (ctZ p)/e (where,
p is the angle between the relative ve *locity vector and the
cascade generator, and e is the gas density):
M ct`g dh 00
0
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:-S/281/63/000/00.'~i/ooz/4joj,-----
E191/E135
AUTHORSi- Stepanov G.Yu.',..,:~ixid~Sherst-yuk-A.N. a olf
C
TITLE*S Contribution to'::the..pr6bleUi of determining the losses
in plane turbine'dascades at.off-design entry angle
Izvestiya.' Otdel enly
PERIODICAL: Akademiyanduk SSSR: e
tekhnicheskikh nauk. Energetika i transport, no.21
1963, 210-2-13-
TEXT.; Sherstyuk (Izv.AN~SSSR,
A formula given earlier by A.N.
OTN, Energetika i avtomatik , no.2, U b
a 1960) and disc need Y
t ik riA
jL G.Yu. Stepanov (Izv.. AN:SSSR, OTN, Energetika 1~avtoma a , 0
iq6i). expresses the profile losses as-a function:bf thle - entry ..and.
exit angles and has empirical-coefficients. Minimuri losse
-formula,-occur at'the design entry a: le only'
according to this ng
when this is 90%. The-choice Of the,-coefficients depends :n the
definition of the exit angle.and the~choice of.,-the.design entry
angle. If the exit angle'', -is -.defined I by the. exit throat and the
-there-are several,methods -for. chdosing:,th e
blade pitch,, ntry angle4'
One method -is. baaed-- purely.-ou -`the- blade:ihape (t, n t'1
a a geilL -to the.mean~
line of the profile at the~-leading' dge)j- an ther-method def ines,:
13 V:. o
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SHERSTYUK, A.N.
Engineering method for calculating rectilinear channels.
Trudy MEI no.47:17-24 163. ,
Determination of losses in rotating blades of radial plates
with actual entrance angles. Ibid.:25-30 (MIRA 17:1)

EMITRIYEVSKIY V.I., doktor teklin. nauk, prof.; ETINGOF, M.N., kand. tekhn.
nauk; KUYINOV. A.G., kand. tekhn. naukj BEKNEV., V.S,, kand. tekhn.
nauk; SHERST-Yiff, A.N., kand. tekhn. nauk
Concerning K.F. Shpitallnik's book "Samigraphical methods for
determining the parameters nf air in a centrifugal compressor
stage." Reviewed by V.I. Dynitrievskii and others.
Teploenergetika 11 no.10-.93-95 0 164. (MIRA 18,3",
1. TSentrallnyy ordena Lenina nauchno-issiedovatellskiy institut
aviatsionnogo motorostroyenlya .4men! P.I. Baranova (for Dmitriyevskily,
Etingof). 2. TSentralln.-yy aerogidrodinamicheakiy instltu-~ imeni
N.Ye. Zhukovskogo (for Kukinov). 3. Moskovskoye vyssheye tekhni-
cheskoye uchilishche (for Beknev). 4. Moskovskiy ordena Lenina
energeticheskiy institut (for Sherstyuk).

L 221:55-65 EPA/E7~,.G(v)/EWT(1)/E'?IT(m)E~IF(k)/FPA(bb)-2/T-2/&P(w)/k~~(f)/EWP(i,)
p~-, -4 AEDC(b) /AEW(a)/ASDF-3/ASDP-3AFTC#IAFTC(p) EM/WW
-141 NR- AP5002201 s/boq6/65/bcp/0Ol/C043/0047
AUTHORS: Sherstyuk, A.,,-N,,, (Candidate of technical. sciences); Soko~qy,,A L,
(&ngineer5; =,Ysenko, V. P. (Engineer)
diffusers
TWLE: Mvestigation of dial _,~yp
axial-ra ecoMpEassors with..blad
SOUICE.- Teploenergetika, no. 1, 1965) 43-47
TOPIC77' --compressor~-~icomprefssor~-~b3-ade- diffuseri-,,-coWessoi~~btf-idiencyj~:~
-AGS:
-:--blade-size ---b--da~skaget- ---- 62 b us 18
la
9. VpPr;
dif f ser-- *4 1 --d1Cfu--- 7--
u 1 10
ABSTRACT: Results of eyperimental-ir-rvestiE;ation,s with blade aifixi"i-Ay"pe
compressors are report,,ad. The purpose of the inves bigzation -.was* to stud* the.
effect of blade geometry on compressor efficiency. The flowing sectiot-7 of. the
conpressor is given in Fig. 1 on the Enclosures. The details of theblade geo-
nietries (a total of 4 different types) are given in tabular form. All except
N-1-9-18 blades were profiled. The compressor was operated at.25 000*. r,psnG and
T 293K. Its efficiency was defined by
Tom I
Card

L 22155-65
ACCESSION NR: AP5002201
where F, is the pressure ratio across the compressor and subscript.-H.'and X
correspond to conditions before and after tile con4pressorrespectively.- Thd type
N-0.5-4-14 diffuser was investiGated first by holding the nw-aber ofwblades Z'- 25
but varying the mounting angle. The results showed a maximun efficiency of 81%
at cW, 3H - 160201 (see Fig. 2 on the Enclosures). The second test was-done, by
varying the number of blades. The optimum numberwas.zH 25-28.. The,efficienpy.
of the compress,or with N-0.5-4-18 type diffuser was less than the_'~'N-~0-5-4-14,
for th6se two profiled diffusers:
diffuser by 1.5%. Analysis of the ratio aVa3,
(see Fig. 2) shows the limit a4/a < a. 8-2.0. - Comparison -of the, efficianc 'f
3 Y'o
type compressor with variable b /b2 showed almost fio~ affect on the
compressor efficiency in the range 1.12- to 0.87. Finally., the.. N-1-9-18 diffuser, -
which had the simplest blade geometry; showed an efficiency of only 04% less blien
the more complicated N-0.5-4-14 diffuser compressor, -Orig._ art. baso' 8 ti&ures,
1 formula, and 1 table.
ASSOCIATION: Moskovskiy
Engineering)
SUB~,ITTSDi 00
NO Ri!Ir SOV: 000
Card 2/4
energetichaskiy institut.(Mloscow Insitiltute ofAeat'Power

C'54~8-65 EPA/EWT(I)/EWP(f)/EWG(v)/T-2/EPA(bb)-2 Pe-5/Pw-4 WV1
ACCESSION -NR: AP5011577 UR/0143165/000'/064/0051;10065
621-515
AUTHOR: 6herstyuk, A, 11. (Candidate of technical sciences, Docent);
Sokolov, A. ineer i Lysenko, V. P. (kngineer)
TITLE: Determining the optimal width of bladeless didusers, of a st-agle-stage
centrifugal compressor
SOURCE: IVUZ. Energetika, no. 4. 1965, 58-65
TOPIC TAGS: compressor, centrifugal compressor$ collvressovd-'Lffuser
ABSTRACT: As the data available in the literature- re the best width of a. blde-:
less diffuser has not been definite. special experimental studies have been
conducted to determine the optimal width of the diffuser in an axlradlal centrifugall
compressor. On the strength of theoretical considerations (later confirmedi by
experiments), the optimal N /hL should lie within 0, 8-0. 85, where b3 to the
diffuser width and b,, is the Impeller width. Tests~ at 25060 rpm were conducted
Card I /Z

L 52088-65 EPR/EPA(bb)-2/TL2/EWP(fl---
,ACCESSION NR: APS015358
UR/0286

: L 52088-6->7 -- -
ACCESSION NR: AP5015358
1 4 ~~o - --
I
! Card 2/2

SHEICSTYUK, A.N., kand.tekhn.nauk-; SOKCLOY, A.I., inzh.; LYSENKO, V.F., inzh.
Study of radial axi-al flow compressors with blade type dififusors.
Teploenergetilka 12 no.1:43-47 Ja 165.
(MIRA 18 4)
1. Moskovskiy energeticheskiy institut.

L 2575-66 EWP(k)/ETC(m) Vhf/Ek
AccEs ION NR: AP5019294 UR/O 143X6s hoo /667/o in'/d id's
542.78
AUTHOR: Sherstyuk, A. N -(Candidate of technical sciences, Docent)j,-,._:,_,`-
Kn_g _in_"~_r
Sokolov, A.I. T )14"Lysenko, V. P. (Engineer)
TITLE: Investigation of the simple -contour blade diffusers of centrifugal
com2ress r9
SOURCE: IVUZ. Energetika, no.' 7, 1965, 102-105
TOPIC TAGS: centrifugal compressor, diffuser performance
ABSTRACT; The results are reported of an experimental investigation of fiv
diffuser variants having 23-26 blades%Td a,,/a 3 ratios of 1. 74, 2. 00, Z. 25, and
2. 45 (see Enclosure 1); the fifth blade variant had no bend in the inlet section*
Blade width, 18 mm; impeller width, 16 mm. Compressor chAracteristics
iand q., plotted against flow) for different blade inlet an les and aq
/a3 ratios#
9
with all speeds reduced to 25000 rpm and at 293X, are a hbwn. In the first series
Card 1/3

L 2E:75-66
ACCESSION NR: AP5019294
of tests, with the 23 -blade impeller, an appreciable effect of the blade angle
(150301 to 180) on the maximum compressor efficiency (80.5 to 77.516) was
thit. .
detected. The second series of tests, with the 26-blade impeller, revealed
the effect of a,,/a. (1.75 to 2.5) on the maximum compressor efficiency is
insignificant (80 to 80. 7%). It was also found that the efficiency of one of the.
tested simple wedge-shape diffusers (no. 2) is only lower by 1% than that of a
complicated -shape aerodynamically "perfect" diffuser. Orig. art., has:
4 figures.
ASSOCIATION: Mos'kovskiy tnergeticheskiy institut (Moscow Power-Engineerill
9
Institute)
SUBMITTED: 03Sep64 ENCL: 01 8UB C:ODEi PR
'NO REF SOV: 001 OTIMM. 000
Card 2/3

-,5.;.66 1
25~fl
L
I ACCESSION NR: AP5019294
i
i . 11
! 4
C&rd 373
A.

L 102~~-66. EPA/Eei-r(m)/E,'IP(w)/E','iP(f)/EI'IP(v)/T-~/EWP(k)/ETC(rn)
ACC NRt Ap6oo3192 SOMCE, CODE: UR/0147/65/001
Mq/Em
AUTHOR: Sherstyuk, A. N.. Zmrchenko, Ye. N.; Aboltin, E. V.; Kriger, V. A.
ORG: none
TITLE: Effect of the number of rotor blades on the characteristics of a mixed-flov
2~e s s ~or
SOURCE: IVUZ. Aviatsionnaya tekhnika, no. 4, 1965, 125-132
TOPIC TAGS: compressor, mixed flow compressor, compressor design, compressor blade
ABSTRACT: A series of experiments were conducted to determine the effect of the
number arblades on the performance characteristics of a mixed-flow compressor with an
exit blade angle of 90'. The obtained results show that for a compressor with a
rotor diameter on the order of 130 mm, the optimum number of blades is about 14.
A reduction in the number of blades results in an increase in the opti.imim discharge
coefficient 0. For example, when the number of blades is reduced from 14 to 4, 4
increases from 0.23 to 0.25. This increase is due to the decrease in the angle of
attack, since the latter is 'directly proportional to the number of blades. The pre-
sented curves can be used to calculate compressor performance characteristics. Orig.
art. has: 6 figures and 5 formulas. [AS
SUB COD~: 131 SUBM DATE: 02Dec64/ ORIG REF: 003/
11Y/1
Card
ATD PRESS:

Lq~pjjN, 11 S.; SHERS-TYUK,_.
" AA.; ZA7CHENKO, Ye.N.; DINEYEV, YxA.,
P;RTHOV,---b-.I..q do-k~ tekhn.naukv pro1f., retsenzent
[Supercharging and superehargors of motor-vehicle angi:Ies]
Nadduv i nagnetateli avtomobillny~h dvigatelei. Moskva
MIa3hinostroenie, 1965. 221 p. 0 (MIR; !W)

GROW, S.V.; KRIVCHIK) P.T.; CHEBAIIETIKO, P.K.,' SHCHERBAK, I-P-; SHERSTYUK)
A.S.,, red.; A-LEKSEYEVy V., tekhn. red,
[The Dnieper Hydroelectric Power Station a first step in the
industrialization of the country; collection of documants on the
construction of V.I.Iomin Dnieper Hydroelectric Power Station2 1926-
19321 Pervenets industrializatsii strany - Dneproges imeni V.I.Ionina;
sbornik dolumentov o stroitellstve Dneprogesa im. V.I.Lenina 1926-193299-
Zaporozhle, Zaporozhskoe knizhnoe izd-vo) 1960. 286 p. (MIRA 14:11)
1. Kormunisticheskaya partlys. Ukrs~ny. Zaporozhskiy oblastnoy komitet.
Partiynyy arkhiv. (Dnieper Hydroelectric Power Statiob)

I M1011, IN, A..V.. HE.U~110, N~ I',,, I nzli. SHE113TYUK-, ]D,~il, , in;:h.
Parameters cf the st.,D-rsonic gas jet In thermal drilUng. Izv.
vys. itchei., zav.; gor. zhur. 5 no.1:90-97 162. WRA 15'.10
1. KazO-hskiy politekhnicheskiy institut. Rekomendovana kafedrcy
razratotki rudny'kh mestorozhdeniy Kazakhskoogo politekhnicheskogo
instituta. 2. Chlen-korrespondent AN Kazakhskoy SSR (for
Brichkin),
(Ecring-Equipment and supplies) (Jets)

BRICHKIN, A.V., prof., doktor tekhn.nauk; BELENKO, N.P., kand.tekhn.nauk;
BOLOTOV, A.V., inzh.; GENBACH, A.N., inzh.; SRAMIN, P.A., kand.
tekhn.nauk; SHERSTIYUK, B.F., inzh.
Experimental studies of the parameters of the stream of a jet-
pierding burner. Izv. vys. ucheb. zav.; gor. zhur. 6 no.3-.
52-58 163. (MIRA 16:10)
1. Kazakhskiy politekhnicheskiy institut. Rekomandovana kafedroy
razrabotki rudnykh mestorozhdoniy. 2. Chlen-korrespondent IIN
KazSSR (for Brichkin).

L U791-63 EWP
(q
ACCESSION NR: AP300CY782 A/6070/63/008/003/04W/04:59'
AUTHOR: K013ty*lev., S. A.; ~herstyak., ~B, No
TITLE- Electron-diffraction studios on-the structure of sublimated films 0-if
ZnS and zrGZMn
SOURCE: Kristallografiyap v. 8j no. 3js 1963p 456-459
TOPIC TAGS- x-ray diffraction~ sublimat~d'filmst Z6. Mn,:photoluminescence,
electroluminescenea, phosphor
ABSTRACT: This study aundertaken becauset of the
of sublimated films wa prevalence
tpurities in larger mas,-les. Films of Zns ana''Z -Mn were prepared in a -high
of ns
va m (10 sub -5 mm mercury) from powdered ZnS. pressed Uitoa disk and heated in
the vacuum at 1100C. Tests on the films~showed that the brightfiess of eladtro-,
luminescence did not increase on raising the heating temperature above 55Mor.on
holding the specimen at the-high temperature for more than 10 minutas.- Thq
brightness did increase with voltage.. boiiever.. and the authors.c6nclude thA this
6 corresponds to a certain degree of disordering in the lattice.~ to test this and
to verify the belief that the structuresof thick and thin films are alike, they
madex-ray diffraction studies of a 2-micron-thick sublimate-phosphor of ZrS_amn
and of the initial material. It was found that the x-ray pattern:of the initial
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