SCIENTIFIC ABSTRACT SHERSTYUK, A.N. - SHERSTYUK, M.I.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R001549120013-5
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: November 2, 2016
• Document Release Date: July 13, 2001
• Sequence Number: 13
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT

S . A61eksandr Nikolayavich; SAMOYWVICH, G.S., redo-ktar; VORONIN,
K.P., tekIfn- cneskiy redaktor.
[Axial flow compressors; aerody-namic calculations] Ose7ye koapresBc-
ry; acrodinamicheski7 raschet. Moskva, Gos.izd-vo, 1955. 247 p.
(Air compressors) (MUIA 8:4)
-

AID P - 2566
Subject USSR/Engineering
Card 1/1 Pub. 110-a - 5/16
Author Sherstyuk, A. N., Kand. Tech. Sci.
-%NSA ftl.*. r W ft -IOVA4-.4 av-,L, 'a V, S
Tltle Method of approximate calculation of curvilinear canals
Periodical Teploenergetika, 8, 205-29, 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.
Institution : Moscow Power Engineering Institute
Submitted : No date

-*- V! R, --r -,
yox
?t
ICE
fW1
f and M n ~wssl'anj 7-;'~
um S
Ah-7 N-u SSSR
21, 195-202, 1955.
In his investigation of pumping limits, author has c9asidefed
the combined operating characteristics brough!-a~out by the
interaction of both pump, blo :and associated
or COMprelsor
J-I
equipment and ducting of certain pit ticul at: instal lad..ons Whi-cb aze;
V of practical interesc.....
s of de arc, di S'.
'of ai;
as is usual, variation
For blowers
, y
analysis of pressure oscitlariows'! In the results,
regarded in the
-is- of critics! giabilicy for several
presented in tabular form, regio.
typical config* at! q defined.
ur on e
For compressors, both centrifugal ahd axial flow, density
variations are accounted for it, the equation for pressure fluctu
atiOns. After lincarizacion 6f this equation, achieved by disre-,
garding deviaiiens due to pulsations from the steady compreqsor.,
characteristic, 'air expression is given in terms of the I'Mmch number
of flow in the system for the limiting pressure pulse permissible
dy operation. Its magnitude is indicated by treating a
for $tea
USA
R. Teske
particular example.
t

KIRSANOV, Igor' Nikolayevich; SHERSTYUK, A.N., redaktor; VORONIN, K.P.,
tekhnirheskiy redaktoZ.--_._
[stationary steam turbines] Stat8loaarnve parovye turbiny. MoOcwa.
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 p resented.
Two diagrams. Four Russian references, 1950-1954 .
Institution : None
Submitted No date

I " ~ /~,/Y-
# 5 /~ Y,~~ K 4
v 1 5

PHASI I BOOKIE,XPLOITATION 446
"X
Sherstyuk, Aleksandr Nikolayevic/
Ventilyatory i dymososy fVentilators and Exhaust Fans) Moscow, Gose-
nergoizdat, 1957. 163 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
Nns. 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 FaiLs
3. Fan performance characteristics
Ch. II. Centrifugal Ans
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 3A
446
15
19
21
23
25
30
33
36
40

Ventilators and Exhaust Fans 446
Ch. III. Exhausters and the Fans Used in Mills
1. Uses of exhausters and fans for mills and their
characteristic working conditions 45
2. Wear in exhauster wheel-blades and discs 46
3. Basic measures for preventing wear 48
4. Effect of ashes on exhauster performance 50
5. Fans used in mills 52
6. Design characteristics of exhausters a-rid fans
used in mills 53
Ch. IV, Axial-flow Fans
1. Working principle of axial-flow fans 55
2. Principal schematic diagrams for axial-flow fan
design 57
Card 4/8

Ventilators and Exhaust Faris 446
Ch. V. Fan Characteristics. Model Testing
1. Dimensional character13tiCS Of f,-MU 88
2. Calculating fan characteristics for various speeds ari!
specific gravities of gas based on experimentally
established characteristics for given speed and specific
gravity
3. Calculation of characteristles foz~ geometrically
fans on the basis of model-test results 91
4. Dimensionless characteristics of fans 93
5. Testing with fan model 95
Ch. VI. Combined Performance of Fans and Duct-work
1. Performance of a duct system with a single fan 103
2. Pan stability. PU13ation --,,,)6
Card 618

V--_---mtIlatars and exhaust Fans 446
Starting and servicing exhausters and fans
Ix. Fan Design for Strength
i. Designing fan-wheel blades
Disc design for strength
Shaft design for strength
Calculating critical speed3 of rotors L .7,
Materials used and the detexinination of allowable
L
stresees
-aphy
Logr
Library of Congress
GO/ad
8-13-58

KORNEYCHUK, Nilcolay Xarpovich; CHERNOV. Aleksandr Vasil'yevich; SUORIJIM,
A.NL,.Apuchnyy redaktor; ROGACHEV, F.T., redkaktor; RAKOV, S.I.,
--fe-9nicheskiy redaktor
Lgachineryj Mashinovedenie. Moskva, Vses.uchabno-oedagog. izd-vo
Trudrezervizdat, 1957. 439 p. (MLRA 10:8)
(Engines)

% ~!~ .- ~ - ~ - _7~
NEVELISON, M.I., Icand. tel-chn. nauk; SIM TYW. A-N., kand. tekhn. nauk.
____I
Modeling centrifugal fans. Energomashinostroenie 3 no.10:18-19 0 157
(Fans, Mechanical--Models) (MIRA 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
dozvukovykh skorostyakh).
PERIODICAL: "Izv. Ak. Nauk, Otd. Tekh. Nauk"(Bulletin of the Ac. Se.,
Te-otinical Sciences bection), 1 57, No.4, pp.123-126 (USSR).
ABSTEACT: A variant of the method of Khristianovicia (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 known, it is
easy to determine according to Fi
.2 the speed of the gas
X and thent by means of eq.(3.2 p p.125, to determine
j
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 accurately,irrespective of
the shape of the profile; the pitch of the profilep t p
can also be easily-determined. There are 2 figures and 2
Russian references.
SUBMITTED: August 299 1956.
AVAILABLE:
Card 1/1

IIJKNITSKIY, V.V. [deceased], doktor tekhn. nauk, prepodavatell; SOMLOV,
Ye,Ya,, doktor tekhn. nauk, prepodavatell; LIBAW, P.D., doktor
tekhn. nauk, prepodavatell; GIMKBLIPAHB, X.L., imm. t9khn. nank,
prepodavatell;'LA,VROY. N.V., dokto'r tekhn. nauk, prepodaviatell; '
IVANTSOV, G.P., kand. tekhn. nauk, prepodavatell;'GOLUBKOV, B.N..
kand. tekhn. nauk, prepodavatell; -qffw--qmwv-A.-X..,-Imnd. tekhn.
nauk, prepodavatell; NIKITIN, S.P., kand. tekhn. nauko prepodavatell".
CHISTYAKCW, S.F., kand. tekhn. nauk., prepodavatell; DUDNIZOV, le.G.6
dokbor tekhn. mm, , prepodavatell; 3AKIASTOV. A.M., kand. tekhn.
nauk, prepodavatell; VIOU, M.I., kand. tekhn. nauk, prepodavatell;
GWASIMOV, S.G., prof., red.; KAGAN, Ya,A,, dots,, red.; AM101W,
I.I., red.; VORONIN. K.P., tekhn. red.; LARIONOV, G.Ye., tekhn. red.
[Heat engineering handbook] Teplotekhnicheskii spravochnik. Moskva,
Goe. energ. izd-vo. Vol.2. 1958. 672 p. (MIRA 11:1.0)
(Heat engineering)

SOV/24-58-4-11/39
AUTHORS.c Samoylovich; G.S. and Sherstyuk, A.N. (Moscow)
TITLE: The Calculation of Curvilinear Axisym-metric Channels
(Raschet krivolineynykh osesi-mmetrichn,7kh kanalov)
PERIODICAL: Izvestiya Akademii Nauk SSSR, Otdeleniye Tekhnicheskikh
Nauk, 1958, Nr 4, pp ?8 - 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; Moskovski5 ejaergetichesk-iy institut (Moscow Power
Institute
SUBMITTED: October 24, 195?
Card 1/1

DEYCH. M.Ye.; ZARYANKIN, A.Ye.-, SHERSTYUK, A.N.; DINEYEV, Yu.N.
Investigation of - to mechanisns of radial-flow turbines.
.a.
Nauch.dokl.vys.shkoly; anerg. no.4:195-2o6 158.
(MIRA 12:5)
1. Rokomendovana kafedroy parovykh I gazovykh tiirbin Moskovskogo
energgtichnskogo inBtituta.
(Gas turbines)

AUTII,O,',,: Sherstyuh,- (Caiid.Tech.Sci,)
TITLE: 'file de3i,rn of aerc-dynamic ,,,ratings at lii!-!i subsonic ipeeds.
(Itaschet acrodinamicheshikh reshetok pri boll shikh'dozvukorjkh
skoro5tyakh.)
11 M-10DICAL: Teploenergetika, 1958, No.3. pF.14-16 (USSIL)
ABSTRACT: Available methods of designing aerodynamic gratings at high subscilic
speeds are laborious and rather inaccurate. Simpler available
methods are not accurate enough close to the inlet and Lutlet ed-,ros
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 fourd.
Calculation of the potential flow of an incompressible liquid ma, be
riade by existing analytical procedures or by an analogue method.
The potential flow of fras at high subsonic s eeds is considered
p
(See Fig.l.) The equation of motion of the gas is given in a
previously published form. Simplifying assumptions are stated and
a graph that may be used to simplify the calculation is given in
The len-th of the equipotential line on the blade is
determined (rraphically as shown in Fig.3. Satisfactory a-r-lement is
Car.' 1 claimed bet~yecii calculated und test data. Dy way of exaiaple Fig.-I.

The Je--3i;rn (if aurodynamic gratings at high subsonic speeds.
shows experimental and calculated data for the velocity
distribution on grids of turbine blading. There are 4 fi_-,ures,
3 literature references (Russian).
AS.~1CL"EI01': Joscow Power Institute
-L,ibr.-:ry of Conjre~,,--~.
(LoskovskiY Energetic hes --~:i y -,-i :,ut)
Card

SHERSTYUK, A."I., k;ind.tekhn.nPu!r
Selecting the size of air drums for piston compressors. Vest.
mash. 38 no.9:18-19 S 158. (MIRA 11:10)
(Air coupressors)

25(~) PHASE I BOOK EXPWITATION SOV/3027
Sherstyuk, Aleksandr Nikolayevich
Kompressory (compressors) Moscow, Gosenergoizdat, 1959. 1-90 p. Errata
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-blaving 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 COW'ENTS:
Preface
Card l/ 5
3

Compressors SOV/302T
Ch. III. Axial Compressors 66
3-1. Arrangement of an axial compressor 66
3-2. Characteristic features of high-velocity flow in a plane grid 67
3-3. Stage of an axial compressor 75
3-4. Determining axial velocities in a stage of an axial compressor 81
3-5. Designing the stage of an axial compressor 84
3-6. Designing axial compressors 88
3-7. Constructions of axial compressors 9)4
Ch. IV. Characteristics of Axial and Centrifugal Compressors. Modeling 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
4-.4. 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 compressors vith 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
7-3. Determining the productivity and pover consumption of piston com-
pressors
7-4. Determining basic dimensions of piston compressors
7-5. Regulating piston compressors
7-6. Constructions of piston compressors
7-7- Mounting piston compressors
7-8. Testing piston compressors
7-9. Starting and servicing piston compressors
7-10. Comparing types of compressors'
Bibliography
AVAILABLE: Library of Congress
Card 5/5
166
169
172
174
176
178
183
184
186
188
VK/jb
2-24-6o

DEYCH. Mikhail Yefimovich; SAMOYLOVICH, Georgiy Semenovich; BEKNXV, V.S.,
kand.tekhn.nauk, retsenzent; SHKRSTTUK, A.N., kand.tekhn.nauk,
dotsent, red.; ZARYANKIN, A.Te._,_IEE~nte~khnnauk, red.; MOIEW,
B.I., tekhn.red.
[Fundamentals in aarodynamics of axial-flow turbomachines]
Osnovy aerodinamiki osevykh turbomashin. Moskva, Gos.nauchno-
tekhn.izd-vo mashinostroit.lit-ry, 1959. 427 P. (MIRA 12:8)
(T'urbomachinas--Aarodynamics)

SHERSTY-TK, A.N.
Design of main gas pipelines. Nauch.dokl.vys.shkoly; energ.
no.1:181-187 '59. (MIRA 12-:5)
1. Relcomendovana kafedroy ekonnniki promyshlennosti i organizatsii
prodpriyatiya Moskovskogo anergeticheskogo instituta.
(Cras-Pipplinos)

sov/96-59-6-5/22
AUTHOR: S h e r s 15, yi,1-
A.N. (Candidate of Te-hni-a' S^Iences)
TITLE: Loss ve-,L-,ermind-flon -in Turbine Blades with Thick Outlet
Edges (K opredeleniyu poter! v turbinnykh reshetkakli
s -dtolshchennyni vykhodnymi kromkami)
PERIODICAL: Teplceneigetika, 1959. Nr 16, pp 26-28 (USSR)
ABSTRACT: I-xi gas turbines, when the inlet gas temperature exceeds
0 -
700 to 750 ':C it is necessary to cool the stator and
rotor bladings, Severai effective methods of blade
cooling nece3sitate the use of thuickened profiles,
particularly at the outlelk; edges. This thickening of the
outlet edges may- cause appreciable losses which it is
necessary to e~,ralluare. L-Ittle work has been published on
subject., Fl,,,ugell -in his book on Steam
Tu.-bines pulblished in -!'-~9 gave expression (1) which is
an ernpii,i,~al formula for the loss due to thickening of
the blade edges-. A tfteoletical 'formlila for t-he edge
losses in straig~,-,--edged blading was given by G.Yu,
Stepa.nov. It is ir. good agreement with experimental. datta
but is ,e-.,-y to use bezaLise it requires
experimental deter=LnatJ.rn of tbe Pressure at t-he blade
edge. A ne-oi -tneo-re'Cioal soluticn of this problem is then
Card 1/3 il~
g ven, with refaren,,~e to the blading diagram of F--'v 1.

SOV/96-.59-6-5/
Loss Determlnatic.,_- in Durbine Blades -v.T-;t-q T.--.i,::k Outlet Edges
The outlet angle of the fi,_-Ar 1S, given bv t.,,.e approximate
empiri3al fo-mula C2~,. ExPressi-,n (3) is given fc)-?, the
effer,tive ;vl',~th c,'- +,-he -z;hroat between tfte blades. An
expressi,:)n _f.s then def-1:-;ed. ignoring ct!)mpressibiLity, for
z;jiz! tot'..'.I. ene.~-,gy iosses on. gc--nF! f:.Dm se,-;tion to 2-21
(see Fig -.", Expres:7.ion ~'5) is t'nen easlliy de-ri-'-;,-d for-
!..Ie value !;.'I -rha Graphs :~f the edge- loss as a
functic.-,11 of ths c,~,_tiet-edge UAL,:tkmessi and il-Itar-blade
gectretry ana ~,j.78Z! in. Fig .27 ea.--h c~~zr-79 corres-
ponds to a i~.arldc;ular va-.1zq nf the :,atic, of effec-tive to
theo-1-stioal th.roat Width. The dotted graph on Rig 2
T11 ordei -
-o checic the
a;-:~'uraf3y cf zu%la a comparLsor). was made between
an.-I, cal.3-: late,-,' dara for a auMbS'r Df bladle
e 4'17eo 2,.1
pr r) f J_ I e s .The regults of thz- cal,_.~aiaticias ar g-L
Figs L _-.na 5. and ara bpiefly dls.~ussedf. It is
considered ti lat in all cases the agresm-ent betvaan test
Card 2/3 and calculated. dall-a. is sat-isfa-~tDr"y'. Moyeove-,

sov/96-59-6-5/22
Loss Determination ir, Turbine Blades with Th4ck Outlet Edges
fornrula (5) explains the observed dependence of the edge
loss on the relative pitch of the blading.
There are 5 figures and 2 Soviet references.
ASSOCIATIONs Moskovskiy energeticheskiy institut
'Mos3ow Power Institute)
Card 3/3

SOV/96-- I'll -14 /'-
I :-- cf
AUTHORS- Deych, M. Ye_ Doctor of Techrii-cal Sciences.
Zaryank-in, A. Ye,,, and Sherstyuk, A. N, Candidates
of Technical Sciences -
TITLE: New Designs of Nozzle Blading for Supersonic Speeds
PERIODICAL. Teploenergetika,, 1959, Nr 11. pp 611-68 (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,, but the efficiency falls
off rapidly when the conditions are cha.-riged. This will
be seen from curve 1 of Fig 1 which gives proflie
losses as function of Mach number for e-_,manding nozzles
type TS-2V,, At the design condition of Mach 1.6 the
losses are only 10%, but at Mach 1 they become 3.1%,
Normal nozzles with contracting channels work well only
at moderate supersonic speeds; see, for example, cijxve
4 in Fig 1, Methods of reducing t-he losses at
supersonic pressure-drops may be evolved from the
formulae for the chan-e 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, conservat,,_,on )f ener-gy and

SO V/96 -- 59-11 -14112-1 2
New Designs of Nozzle Blading for Supersoni: Speed-s
0 -
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 chari,-.e of direction
of flow in the skew sccbion of t-1he rioz.,.le -at -ouperson-ic
pressuro, drops, ari(l formula i.-- deriv(--,d.,
If an experimental relationship between th,:- velocity
ratio and pressure ratio is used, formula (2) is very
accurate. The accuracy is evident from FiE 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 operatine-
_~ cond.Lt`ons., For this case
formula (2) may be used to cJetermine r-he relationship
between the velocity coefficient ai-Ld the pressure ratio,
as seen in Eq (3). The comDarisoa of" theoretical and
experimental results given in Fig 4 confirms the good
C3
a:rreement. This a-reement was obt-ained without detailed
~D r-_1
(Card 2/4 a-nalysis of the nature of flow -in the blading., Hence,
G11(

SOV/96-59-11-14/22
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 back3 of the new shape should

66570
SOV/96-59-11-14/22
New Designs of Nozzle Blading for Supersonic Speeds
be used for guide vlanes 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 riinzier blades
should have a curved back in the skevi section, There
are 6 figures, 2 tables, and 2 Soviet references.
ASSOCIATION: Moskovskiy energeticheskiy institut (The Moscow
Power Institute) Vr
Card 4/4

30244-
S/14 5/60./ 0001/002/10121020
6. ~12 1.9 D221//D302
AUTHOR: Shers tvuk, __A_1_1-f_-~~Ilaladi date of Technical Sciences
TITLE: Caiculating speeds in rotors of radial turbines
PERIODICAL: lzvesiiya vysshikP uchebnykh zavedeniy~ Mashino-
stroyeniye, no. 2, 1960, 124 - 1115
TEXT: The author proposes a simpilfied method of calculating the
speed of flow by reducing the three-dimensional problem to two di-
mensions. Three problems of practical interest are auoted. The
fi.rst c-oncerns a rotor with straight blades (Fig- i). Dotted li--
nes represent t-he curviiinear part of the blades calculated by
,_usual methods when Coriolis forces are insignificant. Tile flow in
,he main part.- of the channel can be considered as taking place in X
L
Mellid-Lona.. sec-LiLns, An elementary vo-Lume dv Js considered, on
vvhi,~~h 'rhe fo_-ioviing forces are actinc-: Centrifugal in the rel_~%tive
centri~7*'_,gal in the transfer motion and force tha-i is -oro-
71, JC ed "ly the __Zference of pressures. The Dublication merrioned nro-
v a. - e sthe so-Lutiolyl 0. s;oeea 0,-_.st.--_1h,!'-_on as -,er

2
wnere w a is the speed a* -joint A; other members being ralios of
slze parameterz, ozo thc iemen-u, The author --ites the graph of
_L V
speed ratio- It shouid ',e rer.,iemibered thl-c speeds at different meri-
dional seztions differ from each other due to various speeds wac
is included to sapport this view. The expres-
mf_~:hemat -,:~a, ana,yss
L - - L
slons are -,,alad for the flow of corpDre~~sible non-viscous fluid,
Aaaalytical, equa-,_,~ons are given for a non-compressible fluid, They L/
toge-.her with the above mentioned expressions determination
--f speed= in a-11 se,_-tlonz, except the small sections of inlets and
Outlets 3f 'he channels, The bame method can be applied for calcu-
wLth any s,'iape of b1ades; the equations, however,
are z.,~ comp-L --red, In -the CenerL.' base, is expedient to limi t.
InIz by d-7-- 'he avera6ed -:-,-,eeds in the uer-i-oheral direct-
-termining
-7, r
__ , A d:_fferentaai equat-:Lon %;h_-c,_- dete.=,nes the absenne of mD--
,ions aiong tihie orthogonals h (Fig. la)9 is worked ou-: in a aiml-
Card L~ I/ ~~

30244
5/145/60/'000/002/012/020
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. 'When the disc and
ring are flat then the flow in the rotor can be considered as plane
parallel, thus reducing the problem to two dimensions. Liathemati-
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 investigite 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 instance, 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: Moskovski energetticheskiy institut (Moscow Power
InstituM
SUB1.1ITTED: December 15, 1959
Card 3

S/021+/60/000/02/022/031
E19VE155
AUTHOR: Sherstyuk, A.N. (Moscow)
TITLE., On the Determination of Losses in qurbine Blading' when
the Angle of Attack is Incorrect
PERIODICAL: Izvestiya kkademii nauk SSSR, Otdeleniye tekhnicheskikh
nauk, Energetika i avtomatika, 1960,Nr 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 for compressibility, and

S/024/6o/ooo/o2/022/031
E191+/El 55
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
derive 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 are
changed. Some idea of the accuracy of formula (5.2),
assuming a constant correction factor, may be obtained
Carld 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~

S/024/6o/ooo/u/022/031
E194/EJ55
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 determiration of the velocity factor.
There are 5 figures and 3 Soviet references. 60
SUBMITTED: November 9, 1959
Card 3/3

69384
S/129/60/ooo/06/001/02.2
0 E073/E535
AUTHORS: Silayev, A.F., Fedortsov-Lutikov, G.P. and Sheshenev,M.F
Candidates of Technical Sciences
TITLE: Properties of Castingsdof the Steel 12Kh1lV2NMF-1~
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'V

6938h
S/129/60/000/06/001/022
E073/E535
Properties of Castings of the Steel 12KhlIV2NMF-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 followst homogenization at 1090 + 100C;
normalization at 1050 + 10OC; tempering at 700 +-10*C
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 Al-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
additions (curve a), for material without any additions
Card 2/4 (curve b) and for material with Ca additions (curve B) X

i6.1 ~''7
69384
S/129/60/000/06/001/022
E073/E535
Properties of Castings of the Steel 12KhlIV2NMF-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 6?OOC; 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 fractlired at 6100C
after having been stressed for 1011 hcurz~ with a stress
of 15 kg/mm . Fig 5 shows a plot of the creep limit
of steel at 6100C for steel containing --_-.-aly 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/129/60/000/06/001/022
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 nonuniformity 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 properties:
a6oooc kg/mm2 a61o0c 9 kg/mm2 ; Cr 61o0c 2
drlo5 10 drl05 ~ n'l-lO_5=5.8kgAm
(dr = do razrusheniya - to failure).
There are 5 figures, 3 tables and 3 Soviet references.
ASSOCIATION. TsNIITMASh
Card 4/4

s/o96/60/000/07/012/022
E194/E455
AUTHORS: Sherstyuk, A.B,, Candidate of Technical Sciences,
Zaychenk7o-, Ye.N., Ignatlyevskiy, Ye.A. and
Sokolov, A.I., Engineers
TITLE: An Investigation of Inlet Pipe Nozzles for Centrifugal
-113
Compr!~ssors
,
PERIODICAL3 Teploenergetika, 196o, Nr 7, pp 56-59 (USSR)
ABSTRACT- The design of the inlet pipe influences the efficiency
of a compressor in two ways. Firstly, losses in the
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/E455
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

s/o96/60/000/07/012/022
E194/E455
An Investigation of Inlet Pipe Nozzles for Centrifugal Compressors kV
be determined experimentally. There are 4 figures and
3 Soviet references.
ASSOCIATION: MEI - NAMI (Moscow Power Institute and NAMI)
Card 5/5

SPERSTYUK, A.N.
Reply to G.IU. 5tevanov's remarks. Izv. AN SSSR. Otd. tekh. nauk.
1 Ji-Ag '(I. (FURA 14.9
Fnerf,,. i avt-)m. no.4:216
(Turbines)

s/143/61/000/002/OC3/006
-t-1 1/0 A20VA126
AUTHORS: Sherstyuk, A. N., Candidate of Technical Sciences, Sokolov, A. I.,
_~n__gineer
TITLE: Determination of the efficiency coefficient of the diffusion grids
from experimental data
4-
PERIODICAL: Energetikalino. 2, 196L 93 - 96
TM: The authors derive the formulae for determinarzq the efficiency coef-
ficient of a straight or radial diffusion grid from experimem al data. Graphs are
submitted which simplify the calculations considerably. Experiments were made on
straight compressor grids (profile packages) which led to tne method of determin-
ing the coefficient of losses described in this article. There are 2 figures and
2 Soviet-bloc references.
ASSOCIATION- Moskovskiy ordena Lenina energetip-heskiy ins-ritut, kafedra paro%rykh
i gazovukh turbin (The Moscow Order of Lenin Power Engineering Ins-
titute, D-nartment of Steam and Gas 'Nrb1nPq)
S U BM =-- M) Febr-aary 26, 1960
Card 1/1

1:h -; SHERS , A.
TRUSOV, S.M., kand.te' n.nauk TYUK N., kand.tekhn.nauk
Calculation of the field of velocities in a h7draulic torque
converter. Izv. vys. ucheb. =-v.; energ. 4 no-7:107-11-4
il 161. (MIPA 14:7)
1. TSentraltnyy nauchno-issledovateltskiy avtomobilInyy i
av-tomotornyy institut (for Trusov). 2-. Noskovskiy ordena
Lenina energeticheskiy institut (for Sherstyuk).
(Hydraulic machinery)

ZARYPI[KIN, A.Ye.., kand.tekhn.nauk; SHERSTYUK, A.N., kand.tekhn.nauk;
ZATSEPIN, M.F.,, inzh.
ZKperimental characteristics of Francis-tjpe tarbines.
Teploenergetika 8 no.6:37-41 Je 161. (MIRA 14-10)
1. Moskovskiy energeticheskiy institut.
(Turbines--Testing)

9 3
wv 0
"-62,
e U 1'.- u.'E; :,I'-
f L) Li i C-L c
01, 3~j-a-
n ,
t: CL
Cs Of Z;'L 7
L'. C C 0 U
y 10; -L,'-

102)
3 C-

t:L
0 o
~,4-4

SHF.HST'fUK, AX., kand.tekhn.nauk, dotsent
Calculation of the characteristics of radial turbine stages.
Izv. vys. ucheb. viv.; energ. 5 no.2.'59-66 F 162. (MJRA 15:3)
1. Muskovakij ordana Lenina energeticheskiy institut.
Predstavlena knfedroj parovykh i gazovy'kh tiu-bin.
(Dirbines)

A (1/62/000/00VOGI./009
Z 1 it/ Z '15 "1
Z,--.ryancin, A.Ye., Candic:ate of Technical Sciences,
A-"'T. , Candic!ai:e of Technical Sciences,
Zatsepin, i- Engineer
vi~'~Vs of increasino- the efficiency of .-ilxed flow-
tur')ines
D 1 C.' LTenlloenerZretil~.a, n,- !962, 52-35
atios k_7 Lo 1-k~) Jciencv of
At lov., rressure r, che eff-
flov., turbines is around which it is important to
incr-'3a_-~O because sl-'.Itll gas turbines of this type are i,.ridoly used.
the ratio of tne blade vidth to diameter is belour 0.05
losses occur at discharge from the nozzles and runner
_11,1 ~IUC to disc fr-iction. Nozzle efficiency can be increased by
profilin,-, that isz,-iachinin- tI,.(_- bl'ndu wizli a twist in it,
-;_.4C:-' 1-orl"Ices the -,;-)eed and final prez;sure drops in the region of
i curv,-iture of 1--.a~i flov-,. flov.,ever, in some cases
-1 , the lo- es at sul-so, ic speeds
._:ieridional I)I-ofililli, w4ilz5L reducing s S U i, -1
;~,.,-,y increase them at supersonic spoeds anifi whilst potc'.-itiltillY Very
advantal-cous, th;a subject requires mucia furtlier experimental study.
Card 1/3

i.:a 3, s on c r ea s ~- n -c- El 94/Z14 54
TCTI L' 0 r certain conditions the use of profiled s;-rou(ling in an
L,,,rbine increased the efficiency by 4,L. 1-11ion the
Llades are very wide the spatial distribution of flow becorles
and under unfavourable conditions, although the flow -is
convergent, Ithere may be divergent regions in the runner
~Tli thi_- disciorL;e velocity distribution -.ia, be very irregular,
L
pz'.rtlclil~irly i..-hen discharge velocity losses are high.
I-uide vanes are usually designed to ensuy-e s. e
ret,uisitc change in cross-scctional area, but it is also important
I -I a~ C Th e
t:iev Le s:I-iooth and with gr. dual ch, n-es of curv. tur
r~lnn,_~r bl~idcs Loo should 1-ave very f.-radual changes of curvature
not 'have straight sections w-liich car. give rise to zones
-r-ent flo,.-,,. Runner friction losses :iav be reduced by
'ivo - L
ncroa5ing the pressure drop in the sta,.-e. Tl-.e value of the
a 1 at which the flow breaks away de-~onds mainly 0'. thL
of hl~,.t'es and reiati-vely liztle on ti-le twist of the
c1lischar,,,,e or tho shzipe of the guide. DJI',qchar7,e
velocity losses may be high in a radial-axial stage even -,;nder
de6ign conditions and, therefore, the velocity of discharge should
C'.1 1, (~ 2 / 3

s/o96/62/000/005/001/009
Sc:;~:e of incrcasin~; ... E194/E454
1, - - -ertc '.~ in, tlc. subsecuent di"user sectJon. ~-hc
.-o If
to cit.::osphere a diffuser can reduce the
the runiler so increasing the icti~al stage ,eat drop
st;~,e efficiency. Axially sy:-.-i:!iotrical di.ffusers
',~(-vorld tile 2-11111ler arc best btit tile disc,-,ar~-c i.~j often
tlll(! C;Ull di'CL,isers orwrat-.e well. under uniforni flow
hest. Fo.- Lnst~-kncc,, iln Pr-actlcal- tests
-ia n -k -I
'SC-17 WaS found better t1l a co-.iicl one altiough
6i,-itic -~csts showed them to have equal perfor:-,iance. There are
i ~,, t i r es .
~36GCIA'-'I(;'N: Voskovslkiy ener.getiches'~:iy institut
('~.'oscow Po,...rer En.-ineering Institute)
cacd 5/3

(lbskva)
Approximate calculation of aero,'-nn,-nzic cascades. lz-v.AH SSSF..Otd.tekh.
nauk.1-t-kh. i mashinostr. no-5139-45 S-0 162. OMMA 15 -.10)
(Ca3ca6s (FluicL dynamici)) -- --'

38996
s/o96/62/00 0/007/001/002
E191/E435
AUTHORS: 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;ntinuity 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 approximate
formula for obtaining the second approximation streamlines fr-om
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/096/62/000/007/001/002
Contribution to the determination E191/E435
successive approximations.but only-for a turbine stage with
50"j' reaction and a 'small 6riation*' of the axial velocities along
the blade length. A metfiod~eliminating successive approximations
but valid in the general casl' is given by the present authors.
The simplification has been achieved at the cost of two
assumptions: 1) the shift of the streamlines is assu med to follow
a sinusoidal law; this as:umption is equivalent to an absence of a-
shift at the root and the iiptof the blade and a maximum shift in
the middle; these conditions,prevail when the blade length is
constant; 2) the distortion of the axial velocity field in the
radial direction is sniall. These assumptions are formulated
mathematically and substituLed;'into the basic equations of flow i.n
a turbo-machine. The analysis gives a straightforward
computation sequence for the abtual velocity. The case of a
multi-stage compressor designe4 with equal stages is specially
considered. In this instance, the ratio of the blade length and
the width of the stage is the parameter which governs the
curvature of the streamlines. ; A numerical example is given
together with a graph in which-the axial. velocity components,
Card 2/3

I.Y4016860 BOOK EXPLOITAT ION
Zaryankin., A. Ye.; Sherstyuk, A. N.
Loir-pc-nar radi-al-axial turbines 0a dial I no-osevy*ye tarbiny* maloy moshchnosti)
Moscow,, Mashgiz, 1963. 248 p. Jllun., biblio. Errata slip inserted. 3000
copies printed. Reviewer: Professor G. S. Zhiritskiy; Managing ediotr:
C.
N. M. Zyugin; Publishing house editor: Engineer N. M. Paleyev; Technical
editor: A. F. Uvarovz; Proofreader: Ye. K. ShIll-unova; Cover artiat; Ye. V.
Deketova.
TOPIC TAGS: radial turbines, radial-axial turbines, lav-power turbines, turbina
stage, centripetal turbines, centrifugal turbines, turbine design, aorodynamic
theory of turbines
PUIRPOSE k%D COVERAGE: This book, is intended for engineers and turbine 5pecialists,'
conce;rned -iith 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-axial-flaa
turbines arc presented. Special attention is Tpaid to single-stage lovi-power
radial-ey.4C;1-flow turbines, vhich have found wide application in rocent years.
Card 1/6

AI!4016860
The book is based on the theoretical research of the authors and of other Ihissian
and foreign specialists. It contains e=erimental material, basically that of
the authors, on the testing of nozzle apparatuses,and turbine stages and the
influence of their goometry oh the efficiancy of stages. This book represents
one of the first attempts to systematiza the theory of radial-fIcyl turbines,
and contains only aerodynamic-design problerris asse.-Uted with rrdial-flovr turbinese
Encireer IS. F. Zatsepin helped prepare paragraph 43, Chapter VII, and, together
with Engineer Yu. N. Dineyev, assisted with the experimental work. Engineer
L. B. 7rolov %ras responsible for the development and application of the measure-
r-ent. aDDaratus.
TABM- OF CONNTSWITS-
Forwuord 3
Ch. i. Certain infonDation from aerodynamics
1. Equation of conservation of energy 8
2. Equations of motion (plane-parallel flow) 11
3. Equations of motion in natural curvilinear coordinates (axially symmetric
and plane-r-arallel flow) 15
Carc2/6

A"016860
/. Design of plane and axially sy:-,r.--tric airvilinear channals - - 17
5. 111-2thod and example of designing a curvilinear channal 21
Ch. !I. Nozzle apparatuses
6. Straight and radial grids 26
?. Zhukovokiy'3 theorem for a radial grid 28
S. Dcsigning the shape of nozzles for subcritical velocities in the case of
flow toward the center - - 34
9. Separation of a gas in the oblique section of nozzles in tha case of super,
critical velccitirs - - 39
10. :I~ozzles for supercritical velocities in the case of flow. toward the center
43
11. Effect of the thickness of the outlet edge of shapes on the value of-the
velocity coefficient - - 46
12. End losses in radial-turbine nczzlos 49
13. Optimum width of radial-turbine nozzles - - 57
14. Experimental investigation of radial-turbine noL,-,,'-;-:- 60
15. Geometric and aerodynamic characteristics of test shapes - - 64
Ch. Ill., Radial-turbine impellers
16. Rotating radial grid 83
Card 3/6

IM4016860
I . Equation of energy for a radial-turbine impeller 89
.7
18. Impeller with cylindrical blades 91
19. Impeller losses in the case of nonrated attack angles 97
20. Disk lorses - - 105
Ch. !V. Radial--cuKial-turbine impellers
21. Thapellers with blades with double cur.7atilre 109
22. Approxiznate determination of velocitits "n an impeller with blades with dva-
ble curvature. Derivation of the fLndamental differential equation - - 11-1
23. Determination of velccities in the impeller, Direct and reverse problems -
- 115
24., Delsigniing the shape of the meridian section 123
25. Simplified method of designing the shape of impeller blades 132
26. Desiigan:Lng the shape of impellers with a given velocity field 139
27. An impellerwith nonrated operating conditions 142
Ch. V. Experimental investigation of high-speed radial turbines
28. Statement of the problem - - 145
29. Autornodal flow in turbines - - 14,7
30. Description of experimental turbines of the radial type 149
32. neasuring apparatus 155
Card 4/6

I.Y4016860
'112. Experimental method and treatment of test rtsults 165
Ch. VI. Sin.gie-stage radial turbincs
33. Radial-axial and centripetal turbines 170
34. Determination of Dindamental over-all dimensions of a single-staga turbine -
- 172
35. Detai-led dasign of a single-stage turbine - - 178
36. -Saraple design of a radial-axial turbine - - 184
37. Design and construction of single-Stage, radial turbines 187
Ch. VII. Characteri..-ties of a singla-stage radial turbine
38. Statement of the problem. Fundamental sLaplifications 195
39. Degree of reaction of a stage 198
40. Turbine efficiency - - 205
1+1. - Gas consumption through a turbine - - 210
Characteris"ics of a radial-axial turbine in standard coordinates 215
4.3.,,Experiniental characteristics of single-stage turbines - - 216
4,/. -Effect of radial clearance on the efficiency of a radial-axial turbine - 231
4.5. Effect of diffusers on the efficiency of a radial-axial turbine 241
Literature 241
Card C/6

AIJAO16860
SUB CGDEE: AP, PR
OTHER: 007
SUB-"!T',ED: 2DApr63
DATE ACQ: 17Jan64
INR REF SOV: 056
Card 6/6

S/179/63/000/001/017/031
E031/E135
AUTHOR: Sherstyuk, A.N. (moscow)
TITLE: -on- the ~calculation of blade cascades for subsonic
velocities
PERIODICAL: Akademiya nauk SSSR. 'Izvestiya. Otdeleniye
tekhnicheskikh nauk. 'Mekhanika i T-.ashinostroyeniye,
no.1, 190631 138-14o
TEXT: The approximate method for calculating blade cascades
for an incompressible fluid, described in an earlier paper of the
,author (Ref.l: Izv.AN SSSR, 0TNj Energetika i avtouiatika, no.5,
1962) is-generalized to the case of a gas flow. The essential
point is the calculation on the rrean value of (ctg P)/e (where
p is the angle between the relative velocity vector and the
cascade generator, and is the gas density);
t
ctg dh
)M t 00
0
Card 1/2

On the calculation of blade cascades... S/179/63/000/001/017/031
E031/EI35
Subscript [too" refers.to flow for upstream of the cascade.
The mean value is determined by the method of successive
approximations.
There is 1 figure.
SUBMITTED: September 7, 1962
Card 2/2

S/281/63/000/002/002/00,3
E191/E135
AUTHORSi Stepanov G.Yu., and Sherstyuk A. N. (Moscow)
Contribution to the problem of determining the losses
TITLE;
in plane turbine cascades at off-design entry angles
PERIODICAL% Akademiya nauk SSSR Iz
vestiya. otdeleniye
tekhnicheskikh nauk. Energetika I transport, no.2,
w,;7 1-963, 210-213
ITEXT.; A formula given earlier by A.N. Sherstyuk (Izv.AN SSSR91
IOTN, Energetika 1 avtomatika, no.2, 196o) and discussed by
G.Yu. Stepanov (Izv. AN SSSR, OTNt Energetika i avtomatika, no.4, I
1961).expresses the profile losses.as a function of the entry and
exit angles and has empirical coefficients. Minimum losses
according to this formula, occur at the design entry angle only-
when this is 90%. The choice of the~coefficients depends on the
Idefinition of the exit angle and the choice of the design entry
jangle. If the exit angle'is defined by the exit throat and the
'blade pitch, there are several-methods for chdosingthe entry anglel',
Bone method is based-,purely on the blade shape (tangent to the mean.l.-
efines
line of the profile at the leading edge); another method d
Card 112

S./28i/63/000/002/002/00;3
Contribution to the problem of ...
E191/E135
a hydrodynamic angle which corresponds to the smoothest velocity I.:,
distribution. In the'case of the (TR-OA) cascade of the
MEI, the geometric angle is 22% and the hydrodynamic, about 17%.
Yet another definition is based on the entry throat and yields in
the example chosen a value of 18%. Finally, the minimum loss
angle can be defined. In the same example the latter is equal to
the geometric angle. In other cases, the difference may reach
Experimental data are compared with the empirical formula and it
is concluded that, although*agreement can be obtained by a choice
of coefficients, the geometric de:~inition of the design entry
.The precise definition should be stated
angle is to be preferred.
when experimental data are communicated. Empirical formulas are
always confined to a narrow,' range,of conditions.
There are 2 figures.
SUBMITTED: September 29,~ 1962
_j
Card 2/2

SHEF-STYUK, A.;L
Engineering method for cpdculating rectilinear channels.
Trudy MEI no.47.17-24 163.
Detennination of losses in rotating blades of radial plates
with actual entrance angles. Ibid.:25-30 (MIRA 17:1)

T -D~ *P-lbn, nauk, ~)rcf.c FTINGOF, M~N. ka-,j ~ -knn.
R Dy' E 'JS K TY V I
V ~ I d n k,~
KUYINOV. A ~G. 3 kand. -.ekhn. nauk? RWKNEV V.S. , kand. takhr.
I .,ekhn. nauk
naWk~ SHERSTYUK, A.N. , kandl. T
Concerning K.F. Shpitallnik's bcok "Semfgraphical methoJz ;',-r
determining the parameters nf air in a centrifugal compress,~;r
stage." Reviewed by V.I. D7-ftrfevekii and oLhers.
'reploenergetika I'll no.10.:9-3-95 0 164. (M-~RA 1-3.5'l-
skiy -!,~s ". 1 -1-1-1 t
TSenlral'ryy ardena Lenina nau2nno-iss-edcvate-l
aVlat,4 ya. finen-' P.I. Baranova (for Dm!-,!yev2kly,
- -onnogo motorostroyeni
Ftingof). 2. TSentrallayy aerog.-,drodinamicheakly '.ni3titu-. 1-meni
N.Ye. Zhukovskogo (for Kukinov". 3. Moskovskoye -,rysqheye '~.ekhni-
cheskoye uchilishche (for. Bek-nev 4. Moskovskl.y ordena Lenina
energetichesk-4y '-nscitut (for Sherstyuk).

L 22 ~trl(v)/i;WT(1)/E74T(m)E'tlP(k)/F~PA(bb)-~/T-2/EWP(w)/ (f)/ (V,) -pe-5/
- -1,55-65* EPAM t0 EWP
'Pf-h/j~w-4 AEDG(b)/AFJX(&)/ASDF-3ASDP-3AFTCA/AFTO(p) EM/WW
ACCESSION NR: AP5002-201 S/0096/65/000/oOi/0043/0047
AUTHORS: Sherstn A.-I, (Candidate of technical, sciences); Sokolov, A. I,
(Engineer); Lysenko) V. P. (Engineer)
TITLt': lhvestigation of axial-radial type compressors with blade,diffusers
SOU16CE: Teploenergetitca, no. 1., 1965, 43-47
TOPIC TAGS: compressor, compressor blade, diffuser, congressor efficiency,
blade 3ize, blade shape/ Nl 2 18 blade type, N 0 5 4 14 diffuser., N 0-5 1; 18
diffuser, N 1 4 16 diffuser
ABSTRACT: Results of experimental investigations with blade, diffuser-type
compressors are reported. The purpose of the investigation was to study the
effect of blade geometry on compressor efficiency. The flowing section of the
compressor is given in Fig. I on the 3nclosuros. The details of the blade geo-
metries (a total of 4 different types) are givon.in tabular form.: All except
N-1-9-18 blades were profiled. The compressor was operated at 25 .000 r.p.m:. and
T = 293K. Its efficiency was defined by
71a
Card

L 22155-65
~ACCESSION INR: AP5002201
where is the pressure ratio across the compressor and subscript H and K
correspond to conditions before and af ter the compressor respectively. The type
N-0.5-h-14 diffuser was investigated first by holding the number of blades z =:25.
but varying the mounting angle. The results showed a miximum efficiency of 81%
at CV, 3H - 160201 (see Fig. 2 on the Enclosures). The second test.was doneby
varying the number of blades. The optimum number was ZH m 25-28. The efficiency
of the compressor with N-0.5-4-18 type diffuser was less than the N-0*5-4-14
diffuser by 1.~%. Analysis of the ratio a,,./a., for these two profiled diffusers
(see Fig. 2) shows the limit a4/a3