SCIENTIFIC ABSTRACT MERKULOV, A. - MERKULOV, I. A.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R001033610011-5
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: January 3, 2017
• Document Release Date: June 21, 2000
• Sequence Number: 11
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT

l8RKLVV, A. P.
"The Vortex Refrigerating Unit.'!
R;:tport submitted for the 10th intl. ReIrigeration Con_;,ress, CoperLliagen,
I
19 August - 2 September 1959-

IS
I MOLOV, A. P. (Assist. Prof. Tech. 3c.)
"Method of Designing Wind Cooling Devices."
report presented at the 13th Scientific Technical Conference of the Kuybyshev
Aviation Institute, March 1959.

25(2) SOV/29-59-1-15/26
AUTHOR: Merkulov, A., Candidate of Technical Sciences
TITLE: Vortex Refr!6,,e:-, (Vikhrevaya kholodill naya kamera)
PERIODICAL: Tekhnika molodezhiq 19599 Ur 1, pp 24 - 24 (USSR)
ABSTRACT: On account of the investigations carried out, the Kuyby-
shevski aviatsionnyy institut (Kuybyshev Aeronautical In-
stitute~ designed the di2gram of a refrigeration chamoer the
working principle of which is shown on the drawing at the
side. It contains a whirling cooler as well as a heat ex-
changer. At first the compressed air from the main pipe is
cooled in the heat exchanger, anO then enters the whirling
cooler. From the whirling cooler it gets into the cooling
with products or machine parts, and from here it is sucl-ed
out into the atmosphere by means of an ejector. The hot air
current serves for sticking off the cold air current. Owing
to the operation of the e,ector, a vacuum is formed in the
cold air tract which leadB to an increased cooling effect.
At 5 atmospheres absolute pressure a cold air current down
to - 600C can be obtained in the cooling chamber. The vortex
Card 112 refrigeration plant is most simple, reliable, can be started

Vortex Refrigeration 21ant
SOV129-ig-l- l ~,,, 2(,
quickly and attains the necessary working conditions in a
very short time. Besides, it h~-a a remarkable pro,~erty: By
the use of tho hot air current, tempez-ature in the chamber
can be reduced and, on do-i!ir.A, incrc,,~scd UP to over 150()C.
The adjustment is done very quickly. There is 1 fi,-,,itre.
Card 2/2

14(1)
SL
3OY/66-59-5-2/35
AUTHORS: Merkulov, A., Candidate cf Technical Sciences
TITLE: Vortex Refrigeration Chami:~er
PERIODICAL: Khoi-odil'naya tekhrika, 1959, Nr 5, pp 8-12, (USSR)
AB3'TRACT - Zhe drawback of the vor-,ex rafrigeratOr Is its io-w efficiency. The
adiabatic efficiency if t-,-- best %rortex refrigerator which has
been test"ed is 0.235. Effi,~ier2y can only be raised by utilizing the
energy of the outflowing cold air current in straightening it out, by
regenerating cold and by ejecting the cold air by hot air blast, 11-7
cutting doom the length of the vortex zone and straightening the hot
air flow. These different pr,~cessez are described in the article and
analyzed. The theory developed by 'he author finds its application in
the design of a vortex chamber, the KhK-_3 which has been constructed
and tested; It has -the following characteristics: maximum pressure -
8 atmoopheres, torap8rature of compressed air 150C, minimum temperature
in cold chamber -70 C, con4w_mption of compressed air 2.2 cu m-minute,
size of the refrigerator 0 - 7,5 x 0 .9 m, weight 35 kg. The article con-
Card 1/2 tains a description of the design, features and operation of the

SOV/66-59-5-2/35
Vortex Refrigeration Chamber
refrigerator, which Is intended for use in laboratories, also for
thermic treatment of metal parts and instruments.
There are: I photo, 1 diagram, 1 graph and 7 Soviet references.
. ASSOCIATION: Kuybyshevskiy aviatsionny-y institut (Kuybyshev Aviation Institute)
Card 2/2

2 "0 2 ~I
"C) 0 3 '0 1 ""0 6 _~z z
S' 106
I 17,'B 10 1
a "/~)rtex '_'oolir.6- System
r a t i vn y z n!j rr, a I Kh' -,A~ a. no 1'~61 , 2~, 3, uh s trac t
"Dostizn. 1 .,adachi v proi z-ve i rrimmenenii
r,ar-An . ki-ve 53SR" 1960, 1 17 - 1 21z)
iffi-ienc-i of a vortex cooliag system
-at --r fGr regenerating the cold of the
c use a f~ exctang,
s ector ta ircrease tne pressure difference, and a
n e cc I f o w. 2h& dpparatus may be operated not
r t1l3o 'b:; a vacuum pump connected to the outlet
itui mav .9firve an altitude chamber.
a I c-_i ;.-A I i ri~~ th- ~ParatUS is SUE,, 3t d.
I ~:e e
~i t I or;

S/066/60/000/006/00,1/009
A053//AO29
AUTHORx Merkulov, A. . Ctvididule cf Technical Scien(-,es
TITLE; Vortex Thermostat
PERIODICAL: Kholodillnava tekhnika, 1960, No. 6, pp. 16-18
TEXTa In order to determine the thermo-physical prop~?rties of ob--
jects, a thermostat operating on positive and negative temperatures is 4n--
dispensable, Such a thermostat has been developed by the author and tested
in the Experimental and Designing Bureau for Vortex Apparatus of the Kuyby-
shevskiy aviatsionnyy institut (Kuybyshev Aviation Institute), The work of
the thermostat is based on the vortex effect of the energy division of gases.
In order to obtain negative temperatures in the thermostatic chamber. the
cold flow in the vortex pipe is used, and for positive temperatures the hot
flow. The thermostat is equipped, besides the vortex pipe, with a heat ex-
changer and an ejector, in the same way as in the vortex refrigerating cham-
ber. The article describes how negative temperatures are obtained by direct-
ing the compressed air flow in such a way that it is chilled prior to enter-
ing the vortex pipe. It leaves the vortex pipe through the opening of the
Card 1/4

89955
Vortex Thermostat
1S/066/60/000/006/004/009
A053/AO29
diaphragm, traverses faucet (8) and after cooling the thermostatic chambgr
(6) passes through faucet (2) and is drawn off by the e.4ector (1) which ope-
rates on the hot air flow of the vortex pipe. In order to obtain positive
temperatures, faucets (2), (3) and (a) are turned so that the hot air flow
passing through faucet (3) is directed towarl the spac-e surrounding thermo-
static chamber (6) which it. heats. Continuing through the heat exchanger
(7), the hot air flow heats the compressed air, after which it leaves through
faucet (2) and passes through the adjustable jet of the ejector, while main-
taining its pressure, which is required in the ejector to obtain the nE-3-
essary ejection rate from the jet., The temperature in the thermcstatir
chamber is measured by thermocouples with a millivoltmeter indicator having
a temperature scale. By changing the diaphragm of the vortex pipe, the range
of temperatures can be shifted toward either positive or negative tempera-
tures. The selction of the diaphragm, laxger or smaller, should be made at
the time of assembly, At stable pressures and even temperatures of dried
compressed air, the chosen temperature in the thermostatic chamber can be
maintained indefinitely within the limits of + 0.50C. The following tech-
nical --haracteristics of the vortex thermostat 8T ! (.VT-!), operating on
Card 2/4

Tortex Thermostat
S /0 6 6 ;'60,'CC 0
A05~1/029
'Iried compressed air are given: maximu;.q air pressure 2 atmospheres, tempe-
rature 20OC; lowest temperature of cold air flow -57 C; hii,,-heest tempera-
k,ure of hot air flow 140OC; volume of thermostatic.chamber 40 1;
refri gerating capacity 900 kcal/hour. The thermostat can also operate on
air which has not been dried, in which,case, however, there will be a loss
of temperature of 10 - 15 IL Being very simple in design and reliable in
operation, the vortex thermostat requires no qualifieE attendance. There
is 1 dia~;ram, 1 photograph, 1 graph arid 1 Soviet reference.
ASSOCIATION: Kuybyshevskiy aviatsionnyy institut (Kuybyshev Aviation Inst-
tute).
Card 3/4

89955
Vortex Thermostat
Card 4/4
S/066/60/000/006/CO4/009
A053/fi-029
Figure 1:
Arrangement of vortex thermo-
stat
1) ejector, 2), 3), 8) faucets
4~ connecting pipe,
5 cover, 6) thermostatic
chamber, 7) heat exchanger,
9) vortex pipe

3/124/62/000/008/013/030
1006/1242
AUTHORS: Merkulay) A.P.'and Kolyahev, V.D.
TITLEs '1~he advisability of using the vortex effect at hitch pressures
PERIUDICALs Referativnyy zhurnal, Mekhanika, no.8, 1962, 42, abstrcct
8B271. (Tr. Kuybyshe.vak-. aviatG. in-t, no.12, 1961, 275-282)
TEXT: An experimcntz.1 investiGation is conducted in a vortex tube
5 mm in diameter at preosure5 up to 50at. In the process of optimaji; cooling
it is shoun by oxtrapulvtion that a pres,.iure of 100 at represents the limit
of sensible application, since the vortex tube effect and the Joule-Tomson
effect coincide. The analysis shows the inadvisability of regenerative
systems at hif;h press-urea. In order to attaiin low tomperctures at a high
dWee of rarefaction, the use of multi-atage systems with uniform distri-
bution of rarefaction between Otae,00 iL3 recommended.
Card 1/1

S!263/62.'W) 01`19~005 010
1007 1207
AUTHORS Merkulov. A P and Kolyshev, N. D
TITLE Whirl-type hygrometer
PERIODICAL Referativnyy zburnal, otdel'nyy vypusk. 32, lzmeritel'naya lekhrilka. no 9, 1962" 38
abstract 32 9 242 (Tr. Kuybyshevsk aviats- in -0, no. 12, 1961, 283-289
TEXT Description is given of working principle and design of a whirl-type hygrometer with cold - -flow
temoval. designed at the Kuybyihev Aviation Institute (KuAl). The working principle is based on the condcn-
-iation method of dew-point determination. According to prelinimary tests the hygrometer work-q in a
temperature range tip to - 20"C at an input pressure of 6 atm and an input temperature of 20 C The tempera.
ture of the sensing element can be controlled with an accuracy of about 0 5 C, by regulating the input pressure
Relative humidity is measured in a range from 4 to 100',,) The time until the device reaches the given tempera-
ture is less than I min. The hygrometer described is for air and gas humidity measurement and control in text-
tile-conditioning shops. in laboratories, drying and chemical industries. etc
jAbstracter's note Complete translation.)
Card 1/1

ME4~=VAlA , kand. tekhn. nauk; IVANOV, S.M., red.;
RAYITIN, I.T., takho. mod.
(Tamed tornade]Ukroshchennyi simerch. Moskva, Izd-vo "Znanie,"
1963. 30 P. (Novoe v zhizai, nauke,tekhnlke. IV Seriia: Tekhnika,
no-3) (MIRA 16:2)
(Vortex tube)

MMLOV, A.P.. kajod.tekhn.nauk
L,ov-temperatuxe AKhK-l and DKhK-1 refrigerating units. Khol.tekb* 40
no.2:77-78 Ja-F 163. (MRA 16:3)
(Refrigerators)

MERKULOV, Aleksandr Petrovich
[Labor and automation)
izdat, 1963. 129 p.
(Automation) (Labor
Trud I avtomatika.
and laboring classes)
Moskva, Prof-
(MIRA 16:11)

AUMORS1. Kerkuloy
0 A*-?#so X01yahows No Do
ORG t ~ Joint Scientific-Technical Conference on Problems of the Mechanics of Id uld and
Ja U am
Gas (Kjistovaya naucbno-tekhnich skaya nrerentsl~a- po voprosam M
TITLE% Experimental verification of the interacting vortex hypothesis
SOURGS.: Kuybyshev. ATiatsionrq7 institut, Trudy,9 no, 15., pte 2j, 1963. Doklady
kustovoy.nauchno-tekhnicheskoy ko-9-arentaii po voprosaa mekhaniki shidkosti i
gaza (Reports of the*Joint scientific-technical conference an problems of the
mechanics of liquid and gas)t 205-214
TOPIC TAGS* vortex flow, compressible flew, heat transfer.9 experimental methods
pressure distribution,# sWersonle flow
ABSnAUCTs As a direct extension to the s6nior author's previous work (Kuybyshev
aviatsionMyInstitut,, TruAy. No. 15. pt.2~p 1963), an experimental verification was
mad* of the th=7~ on interacting vortices."S~M analysla indicates that the rressure
distributions in the free and induced vortices are given ruspectively by
:P= I
1P.=N[1+-!C2
Cum 112

ACC ~.NRt AT6003088
Whereas the towerature distribution In the Induced flow yields
L Ts + -2
T*
1+ 2
The apparatus consists of an exit nozzle (tangential),, a vortex tube, a vortex
generator, and pro'bes,such as static pressure ports and thermocouples to imasurs the
total temperaturej As predicted analytioal3y, the experiments show the presence of
two vortices in. the nozzle section such that under critical conditions the peripheral
free vortex becomes supersonic and the measured value of the minimum pressure ratio
7r* 04,,15 isvery caose to the calculated value. Sindlarilh the temperature drop
nearthe vortex center is found to agree well with the analytic prediction. The
authors .: conterd- that this teebnique can be used to geherate high vacuum refrigeration
units without the need of ejeotors or heat exchangerse Orige art* has: figures,
7 formulass and tablei,-:
SUB CODEt 20/ SUBM DATEa none/ ORIG REF: 001
c~,d 2/2

AXX NRF-MQW6'P~~~~
AMOR: AWbilov, A. P.
F2
40int, Scient
'ORG: ific-Technical Conference on Probleaw of the Mechanics of Liquid
And Gas (Pstovaya, nauchno-tekhnicheakaya konferentsiy& po voprosam mek~----
TITLE: Hypothesis of vortex Interaction
SOURCEs ~uybyshe4.' Aviatsionnyy institute TTudy, no* 15s piloam 2, 1963. Deklady
:'kustovoy nauchno-tekhaicheakoy koaCerent3il, po vaprosam aeWwWd zhidkosti i gaza
(Reports of Me Joint scientific-technical conference on problem of the mechanics of
liquild and gas)# 197-203
TOPIC,TAGS: vortex flow, pressure distributions compressible flow, isentropic flow,
Mach wimber
ABSTRAM The behavior of direct current and countercurrent, vortex flows is
Investigated analyticaUy, In the direct flow case the tangential nozzle is assumed
to have a small axial velocity u relative to the tangential velocity V. The
potential vortex distribution is assumed to be given by the equation
va a conot* It, in shmm that wAer these conditions there wdst two isentrapic
vortices,,. one a free peripheral vortex and the other an induced central vortex such
that the radius of the inner vortex relative to the outer vortex can be given by
Card 112 A

L.14969,~66
7
ACC NRt AT6W3_OFT
0
+
\1 Tel 2
where 7r, - P (P and PO are the static pressures oa the periphery and the axis
revIactively) TRe Uml=, ialus of r2 is given by
2
VAW. -I Y
,in the countercurrent case the nozzle-ead of the tube is partially closed with a
ceatral circular hole.. and the axial velocity distributioa Is given by
U1 !~~&Fj(a + Crt - c
The mass flow rate is calculated froax
M,
R X-1
(1+ 2 M,~ Y~,
which in turn can be used to estimate the mass fraction of cold core flow In the two-
vortex countercurrent flowo Orig. art* bast '21 equations and 4 figures,
30 GODS& 20/ WBM DAM none/ OHM WS 0051 OTH REF s 003
Card 212 yw~-

ACCESSIONN'R: AP4029011 S/0143/64/000/003/0074/0087.
!AUTHOR: Merkulov, A. P. (Candidate of technical sciences)
TITLE: Hypothesis of vortex interaction
SOURCE: IVUZ. Energetika. no. 3. 1964, 74-82
TOPIC TAGS: vortex, vortex interaction, vortex tube, counterflow vortex tube,
straight through vortex tube, vortex interaction hypothesis. turbulent flow.
turbulent flow theory
ABSTRACT: A new hypothesis of the interaction between vortices is advanced
which "does not contradict the previous hypotheses but makes it possible to
analyze the most "efficient scheme D:r a counterflow vortex tube and a
vortex vacuum pump. The essence of the new hypothesis is that the static
pressure on the periphery of a free vortex is always higher than that of a forced
vortex; hence, the peripheral layers acquire a 6peed in the directioa of the hot
end of the vortex tube (the throttle). At a certain radius, the static pressure
comes to a balance; the axial velocity of this layer is zero. At smaller radii, a
Card 1/2

ACCESSION NR: AP4029011
reverse static-pressure gradient is formed; it increases considerably toward the
axis, creating axial velocities toward the diaphragm. The diaphragm-bound axial,
layers are accelerated by the increasingly strong peripheral vortex and form
a core obeying the law of rotation of a solid body. The core flow is essentially
turbulent . Its turbulence makes the core isoentropic . Thus, at the nozzle
cross -section, there are two isoentropic vortices. the peripheral free one and the
central forced one . This pattern can be observed in both ... the counterflow
and the s tr aight -through schemes . Formulas describing the above hypothesis
are developed. It is claimed that some experimental datmare in good agreement
with the above hypothesis. Orig. art. has: 2 figures and 32 formulas -
ASSOCIATION: Kuyby*ahevskiy aviatsionny*y institut (Xuyby*shev Aviation
Institute)
SUBMITTED: 03Apr63 DATE ACQ: 30Apr64 ENCL: 00
SUB CODE: AP NO REF SOV: 006 OTHM: 004
Card 2.12.

MERKULOV, A.P., kand.tekhn.nauk
Apparatus for freezing and iong-term storage of
Kholetekh. 42 no.2:43--45 Mr-Ap 165. (MI RA 38:~)
1. Kuybyshevsk-ly aviatsonnyy irstit~jr,.

t 46884-66
ACC NKs
AR6028066 SOURCE CODE: UR/0285/66/000/005/0022/0022
AUTHOR: Merkulov, A. P, Kolyshev, N. D.
4
TITLE: Velocity distribution over the height of the nozzle of a vortex tube
SOURCE: Ref. zh. Turbostroyeniye, Abs. 5. 49, 106
REF SOURCE: Tr. Kuybyshevsk. aviats. in-t, vyp. 22, lc)65, 178-1.84
TOPIC TAGS: --ortex tube, velocity profile
ABSTRACT: Results are given of an investigation of velocity profiles over the
height of a nozzle at the intake of the vortex tube at various ratios of total prEssures
in front of the nozzle and on the axis of the vortex. The experimental unit is
(fescribed and the procedure presented. [Translation of abstract] [AM]
SUB CODE: 21
Corti I / I UDC: 621-515. 001. 5

MERKULOV, A.V.
Consolidated hydrochomical croas section of the Mukhanovo
fieli. Izv.vya.ucho'h.zav.; neft' I gaz I no.11:9-14 '58.
(141 RA 12: 5 )
1. Groznonakiy neftyELno7 institut.
(Mukhanovo region--Oil field brines--Analysis)

HERKUMV, A.V,
Some features of the hydrogeology of the Romashkino-14innibayevo and
Mukhanovo deposits. TnIdy GNI no.21A68-172 159. (141PA 14:5)
(Volga-Ural-.-j~jjjon-Oil field brines)

MERKULOV, A.Y.; KOTSAREV, I.Yu.
Hydrochemical sections of the Karabulak-Achaluki and Zamankcul
oil fields. Geol.nefti i gaza 6 no.801-36 Ag 162.
09RA 1519)
1. Groznenskiy nauchno-issled)vatel'skiy neftyanoy institut.
(Chachen-Ingush A.S.S.R.-Water, Underground-Composition)

VASIL'YE:V, V,M,i ME.RKU,-LOV,,--L-,!,
New data on -.he o" *.he Kara lbulak-Achall--~ .1,
Neftegaz, geol. i geofiz. no.-~19~-21 1611.
1. Groznenskiy neftyanoy nauchrto-llssledova,~ellsk-,y '-nsl.-',Iut.

the
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23705
AUTPOR: Merk7alov, A.V.
AOO11A1Ol
TrIPLE: Observations with a statical spectroheltograph -in 19~1`9
PERIODICAL- Referativnyy zhurnal. Astronomfya I Geodeziya, no. 4, 1961, at.-
stract 4A459 ("Solnechnyye dannyye", 1959, no. 8, 94 - 95)
TEXT: Trie author describes the continuation of works on improvement of a
statical spectroheliograph (R?,hAstr, 1%q, no. 11, 9015) and observa,,11oni performed
with it. D~ie to replacement of the objective by one with a longer focus, diameter
of the Sun's Image became eqiAal to 133 mm. Slit dimensions are 100 x lll~ mm. The
air gap of the Interferometer JS 0.17 mm which corresponds to the pass band width
0.3 A for line ff(~_. Observations were condi_Ac'~.ed In the III order of the grating,
exposure was 0.05 - 0.1 ser: for the disk and 0.5 2 sec for prominenLes. For line
D the pass band was 0.4 A, and exposure time 1 2 sec. Spectrograms In line HN,
o~ a filament, flare, simspots with facula fields, and a prominence, are presented.
is pointed oiit that observations are possible in the region of wavelengths
shor-.er than ~L 17,600 at chmiging the covering of the Interferometer, At the existing
Card 1/2

23705
3 IC,3V6 A~o4lc,3613 z,P
Observations with a statical spectroheliograph in 1959 AOGI/AIOI
Syst-am cf fine extension of' the interferometer, the acoura,,~y in mpa,~-ir-~ments
radial velocities amounts to 15 - 20 kin/sec, which ean be ruised se,,Pral tlrr,,L-.s
some Improvements. Short exposure duration makes it possihie to rc-,,.,)r,d rlnemato-
graphically chromospheric objects.
Ye. Makarova
IrAb3tracter'.c; note: Complete translation]
L
Card 2/2

PEMWV 9 A.V.
3tatic spectrobeliograph. Part 2. Telescopic interferometric
monochr- r. Izv.GAO 21. no.4:17-34 160. (MDA 14: 1)
(Manochromators)

14ERKULOV , A.V. -
Some new modifications of the F4Lbry-Perot interferometer and
their astrophysical applications. Parts 1 and 2. Izv.GAO 21
n0.4135-72 160. (MIRA 11,:1)
(Interferometer)

~ERKULOV, A.V.
Time of the cvolu~irn of the Upper Cret-acp~ova oil a!A, gap ' .
Geol. nefti i gaza 8 no.12%61-63 D 162. !\YIFA IPZ)
1. Groznenakiy neftyanoy nauchno-i8sledovatellskiy Inatitut.

KlU -L,G'
Criteria f(,,'
reservoirs Ly
th~- 6hec i ie! n. lrru.-,
y ri~' 'l,yag! :1

MERDIM, A.Y4.;-)C"OV",V, A.L
Ton years of the Yalta Scientific Society of Roent.--enologists.
Vest. rent. i rad. 36 no-4.86 JI-A 361 (1411U 15:2)
(YALTA--JUDIO&IST~)

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MERKUIDV, B.A.
New method of protecting screw threads. Metallurg 9 no.4:39
Ap 164. (MIRA 17:9)
1. Vyksunskiy metallurgicheskiy zavad.

CHUBUKOV, A.A., -Jnzh,~ KAGAN- I.L., '-nzh,-, GALADZHEVA, M.Ya.9 inzh.;
KP-kVTSOV; E,M_ !-ERKTU~OV, B.A.. -!-,zh.
'rhe 05IJ-12 au';amat,~ welrle" for welding g"r-lh jol`nts. Svar.
proizv. nc.4.',17--)g Ap 165. , 18!,6')
1. Rosto7skiy-ria-Donu nauchno-iss.',-edo-iatc-~lsk-'Iy
tokhno'log~.!- maiihiriostroyen'-ya.

MMKULOVJ~ D.M., inzh.; MERKUIDVA, G.M., inzh.
Assembly of precast reinforced concrete arches from the lee.
Transp.strol. 12 no.10s20-21 0 162. (KIRA 15212)
(Krasnoyarsk-Bridge construction)
(Bridges, Concrete)

M, RKULOV,,D.M.., inzh.
Flow of small constantly running streams without forrAtion
of layers of ice at bridges and vines. Trantio. otroi. 15
no.Ll:/,1-43 N 165. 1 (M-1 Fjk 18: 11 )

" 1,
I i '.
fl~i(zlbloi" , .1. .
36705 - K Voprosu C, f~--"Lic~" 10 - -' '--- - - 4- . 1.~- ".- -,an.
I r: , J I ~ , w- - ~
f~s b
I
In-Ta. VYP. 3, 1949 S- ',"9-109-
SO : Ifetopis, "'hulma-11ruy'kh Vol. -,-)U, 1'.0311,~Ia,

S/148/60/000/008/011/018
A161/AO29
AUTHORS: Fominykh, I.P.; Volodin, Ryazantseva, V.N.
TITLE: Speeding up the Annealing of Malleable Cast Iron Modified by Boron
and Bismuth
PERIODICAL: Izvestiya vysshikh ucheL-nykh zavedeniy. - Chernaya metallurgiya,
196o, No. 8, pp. 153 - 159
TEXT: At the Go&ovskiy avtozavod (Gor1kiy Automobile Works), where malle-
able,cast iron had been modified by boron and bismuth (Ref. 7), the annealing
time had been out from 60 to 35 - 36 hours (annealing in electric 25-t chamber
furnace). The Tullsklj kombaynovyy zavod (Tula Harvesting Combine Works), aided
by Tullskiy mekhanicheskiy institut (Tula Institute of Mechanics), utilized the
Gor1kiy works experience and attempted to obtain malleable cast iron with raised
strength on account of the predominating perlitic component. Cast iron V4-45-5
(Kch-45-5) used for the experiments had the following composition: (in%): 2.45-
-2.8 C; 0.9-1.3 Si; 0.45-0.65 Mn; not above 0.12 S; 0.15 P, and 0.07 Cr. It was
smelted in a cupola furnace and superheatqd in an acid electric furnace. The
powdered modifier consisted of ferro-silico-boral (an alloy of iron-ailicon-boron-
Card 1/5

S/148/60/000/008/011/018
A161/AO29
Speeding up the Annealing of Malleable Cast Iron Modified by Boron and Bismuth
-aluminum, with 5-15% B) and metallic bismuth, and was placed in a paper bag and
held-into the metal jet during pouring into the ladle; 0.003-0.004% B and 0.002-
-0.003% Bi was used (of the metal weight). Parts for a new machine were cast
from modIfied cast Iron. The parts and specimens were annealed in laboratory
nff-ll (PN-11) chamber furnaces. Three microphotograph sets show the structure
of the initial and of the modified cast iron (a and b, Figs. 1,3,4). It was stat-
ed that boron and bismuth refined dendrites; the modified iron contained a conskil-
ably higher quantity of carbides; it was assumed that cementite of modified iron
contained less carbon and hence had other properties than usuallviz. lower stabilt-
ty, which had been proven by I.F. Xurtov et al. (Ref. 7); graphite grains were
refined. Five different annealing process versions we.,re tried to study the de-
composition rate of primary cementite in the first stage of graphitization. It
was considerably more intense in modified cast iron than in the initial cast iron.
Cementite of modified nast iron was less stable at ~11 temperatures between 850
and 1,0500C, and the metal had a high tendency to chilling at usual and higher
Si content. The finally chosen annealing schedule is shown in Figure 6, with a
total time of only 8 hours. It produced malleable cast iron with a tensior.
strength not below 45 kg/mm2 and an elongation of 5% and more only when the boron-
Card 2/5

s/i48/6o/0oo/oo8/oia/0i8
A161/AO29
Speeding up the Annealing of Malleable Cast Iron Modified by Boron and Bismuth
-bismuth modifier w~Ls.used. The exp6rimental results fblly confirmed the data
obtained by I.F. Kurtov (Ref, 7) and N.G. Girshovich (Refs. 2,8) and proved that
addition of boron and.bismuth greatly.speeds up the annealing of malleable cast
iron and improves graphitization but has no marked effect on strength. The
author points out that in American practice high-strength cast iron with lowered
plasticity is
used very extensively,,and suggests the application of such cast
iron with an ultimate strength which is higher by a factor of 1.5. There are 6
figures and 8 Soviet references.
ASSOCIATION: Tul'skiy mekhanicheskiy institut (Tula Institute of Mechanics) and
Tullskiy kombaynovyy zavod (Tula Harvesting Combine Works)

3/137/6 4/003/00-1/065/0,459
A006/A101
AUMOR: Merkulov, F. N.
TITLEt The effect of quenah-hardening temperature on mechanical properties
of some new stamp steel
PERIODICAL: Referativnyy zhurnal. Metallurg-iya, no,3_.1961, 11, abstract, 3179
("8b. tr. Tullsk. mekhan. in-ta", no.15, 1960, 84-94)
TEET The author 1nvest1gated the affect- of -high quenching- temperatures on
the meehanioal properties.,of -two grades of stamp steel, 5)(HT(5KhW) and 5KH&
(5KM), canteining- in G 0.55-0-56; Mn 0.63-0.464; Si 0,28-0,31; Cr 0.87-1.07,
-N-i 1.5-1.56. Improved mechanical 'properties 0including..a., were abseried at.a..
quenching temperature' rais4d-up to-880 - 900 C as compared to cowrentional tempom--
tures~,as,high a.T.,840--.8600(3. It. was-establish d that -a-r1re of temperature from
840 -.ta-W& caused higher hardness, a09 66, and t after -tempering -at 450,
5C3 and 6GO0C. The steels offer high stability of the hardened structure against
tempering and ehow approximately equal meghanical properties at both room and
elevated temperatures of tests (100 - 600 C) . 5KhNT steel is less bard than 5KhNV
steel but shows higher plasticity.and ductility. 5KhNV steel is highly resistant
Card 1,12

The effect of quench-hardened temperature ...
S/137/6I/000/0031/065/069
A006/A101
to deformation and heat and can be recommended for the manufacture of large-size
dies. To improve the properties of the steels the quench-hardening temperature
should be raised to 880 - goo0C,
T. R.
[Abstractor's note; Complete translation.]
Card 2/2

S/137/b 1/000/"3A2~~69
A006/A 10 1
AUMORi Merkulov,-- F.N.
TITLE% Investigation of the hardenability of 5YHT (5KhNr') and 5 X H B
(5KhNV) die steels
PERIODICAL: Referativnyy zhurnal. Metallurgiya, no-3, 1961, 44, abstract 3D344
C'Sb. tr. Tullsk. mekhan. in-ta!', no.15, 1960, 95 - 99)
TEXT: The hardenability of 5HhNT and 5KaW die steel's was determined by
butt hardening on standard specimens with subsequent determination of hardness
(840.and 88OuC heating temperature) and by the method of distributing the hardness
over the section of a die cube of 34Ox34Ox_34O mm dimensions after quench har-den-
ing from 830, 860 and 8800C under conditions approaching practical ones. With
quenching temperatures increasing from 840 to 8800C, the hardenability of 5KhNT
and 5KhNV steel increases. The deep hardenability of these steels at the 8800C
quench hardening temperature excludes the application of repeated'quench hardening
of dies after reconditioning of the worn out piece. A.B.
[Abstracter's notel Complete translation.]
Card 1/1

,9/123/61'/ooo/olo/boq/o16
A004/A104
AUTHOR: Merkulov, F. N.
TITLE: Investigating the abrasion wear of forging and pressing dies
PERIODICAL% Referativnyy zhurnal, Mashinostroyeniye, no. 10, 1961, 7, abstract
1OV40 ("Sb. tr. Tullsk. mekhan, in-tar, 1960, no, 15, 136-144)
TEXT: The author describes the results of Investigations carried out at
Tula plants to study the effect of the initial hardness of dies, their complexity
and operation conditions on its abrasion. Dle-forgiZ* was effected In te6 t dies
on forging hammers with the dropping part weighing 1-3 tons and on 1,500-ton
capacity crank presses (MKP-1500). The forgings were made of the steel grades
40, 45, 50 and 40)( (~OKh) . Prior to die-forging the blanks were heated in flame
furnad-es up to 1,150 C. As lubrio&nt an NaCl solution with 5% NaNO was used on
the forging hammers, while a mixture of machine oil and graphite w used on
the presses. It was found that up to 60% of the dies get out of order because
of abrasion wear. Above all the projection bridge and the contours of the
narrowest edges of the operating hollow of the die are particularly subjected to
abrasion. The hardness of the dies has an essential effect on their wear. The
Card 1/2

S/123/61/000/010/009/(.-,16
Investigating the abrasion wear ... A004/A104
author presents a nomogram for the selection of the die hardness depending on the
groove depth and the die volume. An overstated weight of the dropping part of
the hammer accelerates the die wear. The abrasion wear of dies can be reduced
by efficient lubrication, elimination of scale, strict adherence to the tempera-
ture range of forging and appropriate selection of hardness and the dimension of
the burr grooves. There are 8 figures and 2 references.
Ya. Golombik
[Abstractor's notei Complete translation]
Card 2/2

zORKUMV, G. - KOVALICHUK, I.; PUGODWKIN. P.
Expansion of large-blocir construction In Krivoy Rog, Sevastopol,
and Kadiyevka. Stroltoll no.5:10-12 My '59. (91RA 12.'8)
1. Instruktor peredovyl-ch motodov truds Ukrainskogo Instituta
Orgetroy (for Merkulov). 2. Hachal'nik uchastke. No.2 Upravleniya
nacballnika rabot No.191 (for Kovallchuk). 3. GlavMy inzbener
tresta Kadiyev-prowhilstroy (for Pugolovkin).
(KrIvoy Rog--Apartment houses)
(Sevastopol --Apartment houses)
(Kadiyevka--APartm-int houses)

MERKULOV, G. A.
A short course in cnt!-cloFico-histolOFiC tecbrii-.,,,~es. Leninrrq~ jc~l. I:!.- -

KMULOT, G.A.
~.-Ii4
Application of dyeing substances of Taccinito myrtilus in p&,thological
and histological techniques. Arkh. pat., Moskva 14 no.4:93-94 July-
Aug 1952. (CLIQ 231-2)
1. Of Leningrad Sclentific-Reaearch Institute for Disegaes of the lar.
Throat, Nose. and Speech (Scientific Supervisor -- Prof. V. I. Voyachek.
Active Member AHS USSR).

MMKULOV, G.; STERN, P.; AMAREK, V.
Effect of benemid on PAS excretion; in a case of pulmonary
tuberculosis with diabetes Insipidus. Tuberkuloza, Beogr.
8 no.2:106-109 Mar-ADr 56.
1. Gradska poliklinika i Farmakoloski Institut Medicinskog
fakulteta Sarajevu.
(TUBERCULOSIS, PUL40NARY, compl.
diabetes insipidus. off. of probenecid on PAS urine
excretion (Ser))
(DIABETES INSIPIMS, compl.
tubere., pulm *h off. of probenecid on PAS urines
eXeretion (S.r
(PARA-AMMOSALICTLIC ACID, in urine
excretion inhib. by probanecid. in pulm. tuberc. with
diabetes Insipidus (Ser))
(URINE#
PAS, excretion inhib. by probenecid in pulm. tubere. with
diabetes insipidus (Ser))
(PROMMID, off.
inhib. of PAS urine excretion in pulm. tuberc. with
diabetes insipidus (Ser))

XlRXULOV.,Qr,i- v 4drayevich, professor; MIKHAYLOV, S.S., redaktor;
gori,
- --' `Oii ; --;'K-, redaktor
[Course on techniques in pathological histolog7l Kura patologagisto-
logicheakoy tekhniki. Izd. 3-e, i6pr. i dop. [Leningrad] Goa. tzd-vo
mad* lit-ry, Lanlngradskoe otd-nio, 1956. 261 p. (NLRA 9:10)
(HISTOLOGY, PATHOLOGICAL)

&
Uwv.
Rk 4Z Dr. (Saraj-vo
Pulmorzri manifestations of scleroderma. Tuberkuloza, Beogr. 9 no.l:
L11-41 Jar-7eb 57.
(SGLMOM-d'A. manifest.
lungs (.3er))
(LUIGS. in var. dis.
seleroflgrm. mnnifest. (Serl)

MERKULOV, Grigoriy Andreyevich, doktor; CHISTOVICH, D.N.p zasl. deyatel'
M.S.., teklm. red.
(Course in pathohistological technique] Kurs
cheskoi tekhniki. 4 izd. Leningrad, l/ledgiz,,
patologogistologi-
1961. 339 P.
(KIRA 15:3)
(MSTOIMO PATHOLOOGAL)

ACC NRt AP7001200 (A) SOURCE CODE; UR/0407/65/000/05-/009"/0097
AUTHOR: Grodzinskiy, E. Ya. (Moscow); Merkulov, G. V. (Moscow)
ORG: none
TITLE: Formation of conic surfaces by electrochemical machining
SOURCE: Elektronnaya obrabotka matcrialov. no. 5-6, 1965, 93-97
TOPIC TAGS: electrochemical machining, metal machining
:ABSTRACT: Cone formation on a cylindrical or prismatic billet by electrochemical
process is considered. The billet is first immersed in
electrolyte and then gradually withdrawn (see figure). A
Workpiece purely empirical method yielded barrel-shaped cones and:
anode low accuracy in the final size. Hence, the present article,
tries to establish mathematical relations between the
Wjal
athode machining parameters and the required cone vertex angle
and also tries to rnap out principal features of necessary
t. equipment. A final formula for the rate -of -withdrawal is:
sulator 2.3. Ti - U where 3 - electrochemical
equivalent of electrolyte;
.1 (2f +lg Y) *
2 2 current efficiency. Ole;

ACC NR3 AP7001200
!U - interelectrode voltage; electrolyte conductivity; j - specific weight of billet
Imaterial; oc - cone vertex angle; 1. - interelectrode distance; y - vertical
icoordinate. The formula permits proportioning various parameters in such a way
',that the cone generatrix is a straight line. The development of a semiautomatic
Imachine for handling up to 10 billets, 0. 5-8 mm diameter, 30-800 mm long is
imentioned; voltage used, 12-18-24 v; current, up to 300 amp. A machiaing error
;of 0. 0 1 -0. 05 mm obtained in experiments is claimed. Orig. art. has: 2 figures and
21 formulas.
';SUB CODE: 09 SUBM DATE: none
Ccrd

AtC NIGH601671.3 SOEMC& CODFos U
TT/WW/GW
AUTHORs Morkulov,_L.
_S&iginoer;-Designer; Chairman 6f the Rocket Section of the
All-
Union Miltt a on Astronautics).
ORG: Rocket Section#. All-Union Committee on Astronautics, P~~SAW. SSSR (Raketneya,
saktsiya# VaesoyusW konitet kosmonavtiki DOSAAF SSSR)
TITL&a The A 8 C of space,flights
SOURGEs Takhnika-mladexhil no. 19 1966t 22-23
TOPIC TAM spacecraft navigation, space oriantationt spacecraftj
spacecraft landing, spacecraft control,, spacecraft propulsion,
spacecraft guidance
ABSrRACTs _&acecraft g!4dance; control, stabilization# correction, decelerations
and landing sysif-emeare discussed. It is noted that the exhaust velocity of a
spacecraft is 2000 - /4000 zo/see'and that a parachute-landing engine system was
er
ployed in the soft landing of the ~Vq~khadw apacecraft)2The,engina was switched an
when the spacecraft was close to the Earth's surface so that It decelerated the drop
of-the parachute reducing the velocity to a negligible value at the moisent, of landing
Orig. art. hast 3 figures.
SUB COM 22j 23/ am DATEs none
Cmd

Fuji Title: K T-
Ae 7" tle t', r- i
Publis'iin,-- D..~.a
5j'o 1-3 i i n; -
ito-i'll. t f
ne
n e
Tevt D%ta
i6 i 1
S 7~ p
sc r;
,IP autho,
t e C.,
,In 'In-, d;
f. r
em s f
Zo fh&AV
Sam
pop

'all
~11~r--J 2/2
ej.
Text Data
loverw-, (ccrit. is
to cl:iLms c~f -Iiissi i's I)T.4
n t,",e
urpose: Bno'-let for n-~nujar -9
Scientific Ljl,-~rv wmisl( 3
Facilitic--s: A lar~7~, r~ljr~'-Or ~~U~, Sr,' ell
"In. ~Ussi,,,r 'lavic .-e
Lal, ry C
Avai -le D.

PHASE X TREASURE~ISLAND BIBLIOGRAPHICAL REPORT AID 612 - x
BOOK Call No.: AF6461TO
Author: MERKULOV, I. A.
Pull Title: JET AVIATION
Transliterated Title: Reaktivnaya aviatsiya
PUBLISHING DATA
Originating Agency: All-Union Society for the Propagation of Political
and Scientific Knowledge
Publishing House: "Znaniye"
Date: 1,,7 No. PP.: 31 No. of copies: 75,000
-,Editorial Staff: None
PURPOSE AND EVALUATION: This is a popular booklet written for the wide
circle of members of the DOSAAF, All-,Union Voluntary Society for the
Promotion of the Army, Aviation and ga*vy. It gives basic information
on various kinds of jet engines and a short outline of the history of
their development, which is represented as an entirely Russian'achieve-
ment. Engines described in the text are well known and dD not
represent any special interest.
TEXT DATA
Coverage: The author compares the possibilities of propeller-driven
aircraft with those of jet aircraft.. He explains the principles of
operation of: 1. Liquid propellant jet engines; 2. Ram-jets;
1/2

rs~:,;rj-iru WV i , A.
VARVAROV, ILA.; DOBROURAVOT, V.V.. professor, daktor fisiko-matamatichs-
skikh nauk; MXRKW4W I.A., inthenot-konstruktor; MTAPIV. A.D.,
"~F ; SThBMGYICH. K.P.. professor, doktor
laumat Sta
teklmichaskikh nauk; KHMTSAVICJi, Tu.S., kandidat takhnichookikh
nauk; SHTERNMID, A.A., laureat mashdunarodnoy pooshchritalluoy
premii po astronavtike.
3hroute to the stars. Tekh.mol. 22 no.7:1-7 Jl '54.
1. Predsedatell saktaii astronavtiki pri TSentrallnom aaroklube SSER
Imeni Chkalova (for Varvarov). 2. Zamestitell predeadatella nauchno-
takhnichaskogo komiteta po kosmichaskoy navigatail, saktaiia-astro-
navtiki (for Dobronravov). 3. Predsedatell nanchno-tekhnichookogo ko-
miteta po raketno;r takhnike, aektoila astronavtiki (for ?-tjjWluj.
4. Predsedatell nauchno-takhaichaskogo komitata po biologii koemiches-
kogo poleta, sektaiia astronavtiki (for Seryapin). 5. Chlen nauchno-
takhnicheakogo komiteta po astronomichealcim i fisichaskim proble m
(for Stanyukovich), sektaiia astronavtiki.6. F-redsedatell nanchno-takh-
nichaskogo komitata po radio-teleupravlaniyu (for Khlebtsevich), ask-
taila, astronavtiki. 7. Predaedatell nauchno-takhnichaskogo komitets
po koomichaskoy navigataii (for Shternfelld). sektaiis astronavtiki.
(Interplanetary voyages) (Space ships) (MM 7:6)

lakneyovich; KIPNIS, S. Ya., redaktor; ISLF.HT'Yv-VA. P.G.
takhhicheakiy redaktor.
[Cosmic rockets; from a lecture series "Modern problems In astro-
nautiesO (based on "Sunday lectaresR of the Polytechnical. Museum)
Kosmicheskie rakety; iz toikla. laktaii "Sov-remenrVe problemy
astronavtiki" (po materialam "Voskreanykh chtenitm Poli,-ekhni-
cheskogo muzeia) Moskva, lzd-vo 'Zaanie." 1955. 31 P. (Isesoiu-
znoe obahchestvo po rasprostraneniiu politichaskikh i nauchnVkh
znanii. Ser. 4, no-36) (KLRA 8:11)
1. Predesdatell nauchno-tekhnicheqkogo komiteta reaktivnoy tekhniki
T3entral'nogn asroklubs, SSSR Imera Chkalova.
(Rockets)Aeronauties))

BATJCV. Lev Konstantinovich; HOKULOV. Igor' Aloksoyevich; PLONSKIY, A.P..
redaktor; GAVRILOV, * ~, -- - " re --ktor
CRocket plane; jet aviation] Samolet-raketa; reaktiv-naia aviataiia.
Izd. 3-e. perer. Moskva. Goo. izd-vo tekhniko-teoret. lit-ry, 1956.
55 P. (Nauchno-populiarnaia biblioteka, no.39) [Microfilm] (M`LRA 9:8)
(Airplanes--Jet propulsion)

AID P - 4679
Subject USSR/Aeronautics - Space ships
Card 1/1 Pub. 58 - 5/14
Author Merkulov, Designer, Chairman of the Scientific and
Engineering Committee, Jet Propulsion Section (Aero-
nautics), Chkalov's Central Aeroclub, USSR.
Title Space rockets
Periodical Kryl. rod.,'7 4, 8-11, Ap 1956
Abstract The author passes in review the basic technological and
engineering problems presently facing the designers of
space ships, and outlines some of the current Soviet
ideas as to 'Che form and construction of the latter.
.3 designs and 1 sketch.
Institution None
Submitted No date

1. 11. , c-A] B"*-".'!-,", -7. K.
I
Rocket .irc--rcf 11- -plfblieh-,~6 11-Y ' iii- : --*S'2Y -- f Def crsc '.

PHASE I BOOK EXPLOITATION 330
Merkulov, Igor, Alekseyevich---
Gazovaya turbina (The Gas Turbine) Moscow, Gostekhizdat, 1957.
54 p. (Nauchno-populyarnaya biblioteka, vyp. 94) 75,000 copies
printed.
Ed. (title page): Kvasnikov A. V., Honored Worker in Science and
Technology, Prof.; Ed. 4nside book): Plonskiy, A. F.;
Tech. Ed.: Gavrilov, S. S.
PURPOSE: This booklet is written for publication in a series devoted
to the popularization of science and technology.
COVERAGE: The author is concerned with steam and gas turbines in
general. Only in the last 8 pages does he describe turbo-
jet and turboprops and give a few data on aircraft equipped
with them. He mentions a number of personalities working
in the field of the internal combustion engine. Those more
recently connected with the development of the gas turbine
include: Academician Stechkin, B. S., called by the
Card 1/6 author the creator of the modern gas turbine, who made an

The Gas Turbine
330
important contribution to the formulation of gas turbine theory,
in particular to the theory of bladed machines and to the
analysis of centrifugal and axial compressors; Professors
Ushakov, K. A.; Dnitriyevskiy, V. N.; Kholshchevnikov, K. N.;
and Kazandzhan, P. K., who did important theoretical and experi-
mental research in compressors; Member, AS, Ukrainian SSR,
Proskura, G. F., who worked on the theory of bladed machines;
Professors Zhiritskiy, G. S.; Kvasnikov, A. V.; Kirrillov, P. 1.8,
Shnee, Ya, I.; and Zotikov, G. P., who studied gas turbine
theory; Uvarov, V. V., who solved the problem of a blade of
constant efficiency along its length; and Antonov, 0. K., who
designed the passenger aircraft "Ukraina". This aircraft is
equipped with four turboprops, has a 600 km/hr cruising speed,and
is described as one of the most economical of its kind.
The author also gives some specific technical information.
For example the Len-ingradskiy metallicheskiy zavod (Leningrad
Metal Plant5 before the Second World War built a 100,000-hp
steam turbine, and after the war a 150,000-hp unit. The periph-
eral speed of modern centrifugal compressors attains 500 m/sec.
The pressure of the air at the outlet of the impeller averages
Card 2/6

The Gas Turbine
Card
330
2.5 atm., and Is 5 atmat the outlet of the diffuser. The
efficiency of centrifugal compressors does not exceed 70-75%,
when axial compressors attain 85-90% efficiency. Modern turbine
blades made of special alloys operate safely when the tempera-
ture of the incoming gases is 9000C. Research Is under way for
the application of ceramics to blade manufacture In order to
make higher operating temperatures possible. When powdered
coal is used as fuel, some salt particles 0.03-0-05 m.in diam-
eter are formed during combustion due to impurities. These
particles may damage modern turbine rotors which turn at 5,000-
10,000 rpm or even faster. The efficiency of modern gas turbine
plants is 25-30%. There are about 200 stationary gas turbine
plants in the USSR and their total power exceeds 1,000,000-hp.
In turbines of the Nevskiy mashinostroitellnyy zavodSNeva Machine-
building Plant in Leningrad) air is compressed to 4.6 atm,, the
compressor efficiency is 8 and the rotor turns at 5,000 rpm.
The gas temperature at the inlet of the turbine is 6001C and the
turbine develops 6,100 kilowatt. The compressor absorbs 4,0500
kw. and the available power Is 1,500 kw. The Leningradskiy
metallicheskiy zavod (Leningrad Metal Plant) uses larger gas
3/6

The Gas Turbine
330
turbine power plants: one of them has three compressors(large,
medium and low pressure) and two turbines (low and high pressure).
The high-pressure turbine develops 22,000 kw, of which 10,000 kw
are used to drive the high pressure compressor, so that 12,000 kW
is available for the generator. After the passage through the
turbine at 3 atm.pressure and 420*C temperature the gases enter
an intermediate combustion chamber, where they reach 6500C and
are used to drive the low-pressure turbine prclucing the 19,000
kw necessary to drive the low and medium-pressure compressors.
The overall efficiency of this arrangement Is approximately 25%.
If the temperature of the gases at the inlet to the turbine could
be increased from 600-7000C to 9000C, the efficiency would
increase from 21-'96 to 401,16". In the Kolomenskiy parovozostroitellnyy
zavod (Kolomna Locomotive Works) a 6,000-hp gas turbine locomotive
is under construction. Turbojet engines can work efficiently at
speeds of 3000 km/hour and altitudes of 25-30 km. A sketch and
diagram are given of a 13-3tage, 1/10 pressure ratio, two-
compressor, turbojet engine, which develops a 5,000 kg thrust
on fuel consumption of 1 kg fuel per second, and weighs 1,500 kg.
Card 4/6

The Gas Turbine
330
The following examples of jet propulsion efficiency are given:
1) a four-turbojet aircraft, 20,000-hp total power, 300 m/sec
speed, developing 14-hp per one kg of its weight, or 7 times
better than a piston-engine aircraft 2) a turbojet fighter
with triple compressors, 16-stage, 1/12.5 compression ratio,
and a 3-stage turbine, developing 7 tons thrust, with a 1,700
km/hr speed and 20,000 m.ceiling, 3) a 70-ton bomber with
4 turbojets and a total thrust of 14,400 kg, top speed of 1,100
km/hr, and an operational radius of 4,000 km. There are no
references.
TABIE OF
COWIENTS: Introduction 3
Heat Engines 3
How a Gas Turbine Works 11
Gas Turbine Power Plant 17
Card 5/6 From Gas Turbine History 25

The Gas Turbine
Gas Turbine in the National Economy 34
AVAILABLE: Library of Congress
Card 6/6 AC/vm
May 29, 1958

41 C, f~_ 1~ U L L, V
85-9-18/33
AbTHOR,~ Merkulov I,, Designer, Chairman of the Scientific Tech-
lea Tommittee for Jet Technology, Astronautics Section,
n
~
Central Aeroclub of the USSR
TITLE- Modern Jet Planes (Raketnyye Samolety Nashikh Dney)
PERIODICAL.. Kryllya Rodiny, 1957,q,Nr 9, pp. 17-19 (USSR)
ABSTRACT: The author seeks to give the readers a general idea of
the modifications which had to be Introduced in the con-
struction and the design of the planes In order that the
possibilities offered by the powerful modern engines be
better used. In that connection he illustrates his text
with 12 drawings showing various unspecified planes, and
offers comments on some characteristics of these planes.
The author's comments of conceivable actual Interest are
rendered here below: Jet fighter (possibly Soviet
fighter "Sukhoy"), Delta wing; weight at take-off - 13 t.,
length of the plane - 17 m.; wing span - 16 m.; gross wing
area - 85 sq.m. Two turbojet engines with 13-stage com-
pressors and 2-stage turbines. Total thrust - 7.4 t. Air
intakes situated at the sides ofthe fuselage. Maximum
speed (at the altitude of 15 km.) - 1150 km.A. Fj.A._ 4:
Delta wing single-seat jet fighter (the drawing recAlis
Card 1/4 the British fighter SK-53). Normal thrust of the turbojet

Modern Jet Planes (Cont.)
85-9-18/33
engine- 5 t.;augmented thrust - 7 t. The 16-stage axial com-
pressor, formed of 2 separate aggregates of 9 and 7 stages, in-
creases the air pressure 12.5 times. 3-stage gas turbine. Take-
off weight over 12.5 t., maximum speed - 1500 km. A. Fig. 5:
Jet fighter (the drawing recalls the US fighter F-104). A thin
trapeziform wing, with a very small aspect ratio. Wing span -
6.68 m. Width of the fuselage at wing-root - 2.10 m. The wing
Is made of one single metal plate; its leading and trailing
edges are very sharp. Length of the plane - 16.9 m. One turbo-
jet engine; thrust - 6800 kgs. The weight at takeoff - approxi-
mately the-same. The speed is about twice the speed of sound.
First test flights with the plane began in February 1954. Fig. 9:
Heavy bomber (the drawing recalls the US bomber B-52) * Weight -
170 t,. eight turbojet engines; total thrust 40 t.; maximum
speed - 1050 k-m. A.; range - 12,800 km. Crew of 9. The shoulder-
high wing has the form of an arrow. Fig, 11: Experimental ram-
jet f1ghter-Interceptor (possibly French experimental fighter
"Leduc"). Destined to develop speeds equaling twice the speed of
Card 2/4

Modern Jet Planes (Cont.)
85-9-18/33
sound, and expected to be able to intercept a modern bomber flying
at an altitude of 15 km. within less than 3 minutes, including the
.L necessary to prepare the takeoff, and to effect It. "Pres-
time
ently an object of intensive studies". Fig, 12: Experimental plane
(unidentified). All-metal.-_ One liquid fuel engine with 4 firing
chambers. Liquid oxygen and the alcohol are fed into the engine by
a turbine-actuated pump. The thrust can be controlled by succesive
switching-on of the firing chambers, each of which_develops a thrust
of 680 kgs. Full weight about 8 t.; maximum speed 1600 km.A. at
the altitude of 18 km. , and 2700 1cm. A. at the altitude of 24 km.
Duration of the flight with all the engines switched on-4.5 minutes.
Durin the test flights this plane had to be lifted to the altitude
of 7-9 1cm. by another powerful multi-engine plane. Rated apeed'.&t
the altitude of 21 Ian. - 2650 k7n. A. The same plane reached the
altitude of 27 km. A plane [it is not clear whether the author
speaks of the same plane or of another one] equipped with a liquid
fue-1 engine has presently developed the speed of over 3000 km.A.
As far as the thrust power of liquid fuel engines 18 concerned, the
author, speaking in very general terms about -the developthents In this
field, indicates that at present 1 kg. or fuel consUmed by jet en-
gines In 1 second 15 supposed to develop;a thrust of,-approximately,
Card 3/4

M.-Aern Jet Planes (Cont.)
85-9-18/33
250 kgs,, and he mentions the figure of 400 kgs per kg./sec. as a
goal which shall be reached sometime. 12 drawings.
AVAILABLE:
Card 4/4
Library of Congress

25-9-15/40
AUTHM Merku%ov, I.A., Chairman of the Technical Committee of Jet
En ineering of the Central Aeroolub of the USSR
TITLE: A Prominent Scholar (Vydayushchiysya uchenyy)
PERrODICALs Nauka i Zhisn', 1957'.2) 9. P 32 (USSR)

ABSTRACTs On the occasion of the 100th anniversary of K.E. Tsiolkovekiyls
birthday, the author recalls the great merits of this pioneer of
space flight and rocket engineering. More than fifty years ago#
Tsiolkovskiy established already the theory of space flight by
means of a jet-powered flying apparatus and proved the possibility
of launching rockets and their return to earth. He foresaw that
propeller driven planes would be succeeded by those equipped
with jet engines. The present development of jet and rocket
engineering in the USSR is mainly based on Taiolkovskiy's theories
and led to the construction of the jet airliners "V-10411 and
"TY-1.1.0" constructed by Soviet engineers under the supervision
of Academician AjN. Tupolev. Artificial earth satellites will
be the next stage in the development of flight engineering.
There is one figure.
ASSOCIATION: Nauchno-tqkhnicheskly komitet reaktivn t khniki Tsqntra
oilno
F ' go auo~M
MR ~JcUntgajtechnieal Committee o:rJii Magineering o th7e Ce r ro-
elm we
&Err : Library of Congress

TOKAREV, F.T., isobrotatel', Gerov Sotsialistichookago Truda; SHIRMOV, I.T..
izobretatell v oblaisti stroy-materialov; FMOVSKIY, G.I., professor.
dolctor takhnichaskikh nauk; SHMOV, I.P., novator stroitel'noy In-
dustril; CMEBT. H.S., novator; KGTOVA, S.A., novator, brigadir
pryadillshchits; WGIN. H.L. isobrotatell, inchener; SLITOCHUM, F.P.,
ratsionalizator; RM &A.. lcobretatell, konstruktor dvigatelay;
mr~' v oblasti kino; KHTX TSIVICH, Yu.S., lzo-
XOSKATOV, N.V.. I o ratatell
bretatell, kandidat tekhnicheskikh nauk; SHCHADIIA)V, V.L. ratsiona-
lizator-naladchik.
"Inventor" has a pround ring to it! Tekh. mol. 25 no-3:1-3 Kr 157
(MIRA 10:6)
1. Deputat Verkhoynogo Soveta SSSR (for Shirkov). 2. Machallnik tsekha
zavoda imeni Sergo Ordzhonikidze (for Chikirev). 3. Fabrika imenj
Kalinina (for Kotova). 4. Termitnostrelochnyy zavod (fer Login). 5. Za-
vod "Kauchuk" (for Slivochkin).
(Inventions)

PHASE I BOOK EXPWITATION 1066
IftrXulpy ekseLn~. rman Engineering Committee of the Chkal(;v
,-162r' A~_ _S!j,_Phai Jet
Central Aeroclub of the USSR
Iskusstvennyye sputniki - torzhestva idey K.E. Tsiolkovskogo (Artificial Satellites,
the Triumph of K.E. Tsiolkovskiyls Ideas) Moscow., Izd-vo "Znaniye", 1958. 68 p.
(Series: Vaesoyuznoye obshchestvo po rasprostraneniyu. politicheskikh i nauchnykh
znaniy. Seriya IV, 1958, no. 8-9) 75,000 copies printed.
Sponsoring Agency: Vaesoyuznoye obshchestvo po rasproatraneniyu politicheskikh i
nauchnykh znaniy.
Ed.: Islankina, T.F.; Tech. Ed.: (hibin, M.I.
PUITOSE: This book Is intended for the general reader.
COVERAGE: The author of this popular booklet cammemorates the centennial anniver-
sary of the birth of the late Soviet scientist K.E. Tsiolkovskiy and eulogizes
his a&ievement in establishing the fundamentals of space flight. He presents
a brief biography of K.E. Tsiolkovskiy and a historical review of the devel3p-
ment of Soviet jet aviation and rocket technology, glorifying the Soviet science
Card 1/2

Artificial Satellites (Cont.) lo66
in launching Sputnik I and Sputnik II. A brief description of instrumentation
and some qualitative data is given on Sputnik II. There are no personalities
mentioned. There are 23 Soviet references.
TAME OF CO S:
Scientific Achievemedt
Life of the Scientist
Liquid Rocket Ebgines
Jet Aircraft
Rockets
First Artificial Satellites
Bibliography
AVAIIMLE: Library of Congress
Card 2/2 IS/sfM
1-7-59
7
13
i8
31
42
53
70

pnu I BOOK MMIDITATION 1029
Merkulov, Igor' Alekseyevich
Polet raket v mirovoye proatranstvo (Rocket Flight Into Outer Space) moscow,
Izd-vo DOSAAFY 1955. 87 P. 40,000 copies printed.
Ed.: Vasillyev, A.A.; Tech. Ed.: Andrianov, B.I.
PURPOSE: This book is intended for the general reader.
COVERAGE: The booklet describes briefly in popular form the problems of celestial
mechanics, the problems of rocket engineering and other basic concepts in the
development of artificial satellites. The author emphasizes the leading role
of Russian and Soviet scientists and inventors in the development of rocket
techniques based on K.E. Tsiolkovskiy's ideas concerning outer space flights.
A-11 quantitative data., however, is based almost exclusively on existing and pro-
posed American projects. No personalities are mentioned. There are no references.
TABIE OF CONTENTS:
On the Threshold of Flights Into Outer Space
Card 1/2
3

Rocket Flight Into Outer Space 1029
The Great Scientific Problem 5
Reaction Engine 10
Atomic Energy in Rocket Engineering 18
Rockets 21
Rocket Trains 27
"Ethereal Island" of Tsiolkovskiy 30
Rocket Flights 31
Design Projects of Artificial Satellites 41
Itineraries and Duration of Outer Space Flights 53
Cosmic Ships 60
First in the World 67
AVAILABLE: Library of Congress
Card 212 IS/Sfm
1-7-59

26(114) PEASS I 13DOK UPWITATION MV/2543
AkAdml7a nAUk SSSR. Laborstnriya 4vigateley TZ,
TOOV171L. lonstrunslya, raschot I Ispytanlys dwigatelay Tnutronnego
01101*4111Y& (Theory Design: CalLulation, and ?**tin f Internal
1958. 91704 P. (Sarlent
Zzd-vo AN 333ft
C
b
ti
t
N
l M
oscow
om
us
on
,
o
ora
Its' ?rUdY, v7p. 4) Irrata slip inserted. 3,000 copies printed.
Zd- Of Publishing Mauve: V.K. Klannikov; Tech. 54.z T.A. Pru:akova; F_
WitcriLl Doardt N.D. Apashav, Doctor of Technical Science .
Zagr7"kin, Candidate of Technical Sciences, Yu. B. avirldov,
Candidate or Technical Sciences# 3.2. XzrantLeov, zagincer, and
&Q. Yovgrarov, 19nZinser.
FMLR=z This book is Intended for workarn of scientific ronearch
z
)
zaa
, do-
iDAtItUtOM, students of schools of higher education (vu
Olga bureaus, and to promote exchange of experimental Information
On Me thermod.-aalics of Internal combustion engines.
COTMUM: This collection consist& of 14 articles based mainly on
research work done by the author In 1955-1956. Part I IS devoted
Wcrx=g Processes in San turbine power plants arld to th*o retl_
r:
aam experimental wark conaactod with Investigation or the flow
,
of 90800. Part XX contains article* on the Investigation of pro-
am&"& In piston engines. Part III deals with the avAAUr0U4ftt of
high temperatures of gas@*. The caLlection Is number 4 Of the
Transactionior the chains Laboratory of the Academy of 3clanose,
USSR. No parocnalitica are,mentioned. There am no references.

t
I. and R.I. Tumanov Ldecoazod). Calcula Ion of
u
-
"
ift
7 _ Rest
ocess With changing
h. in an AdiabUrc r
N
'Aft
R
Capacity Taken Into Consideration 32
Us equation obtained of the adiabatic curve of a gas with
ahanging heat capacity and Ito graphiaal representation mak,
possible a rapid and very exact calculation of the gas chnrac-
terlstlas of air and the combustion products of ki~oscnc.
Changes of temperature in the adiabatic process are from 200
to 2,500.IL There am 3 Soviet references.
5 MLIrakov N F. end I.I. Sem*.q9_t_P=blemv or the Then" of
Ub1aid a Poorly Streamlined
body 44
The author states that t7:.probl:: Is very compll~atad, and
=7 be 49fined by a comp &Tat of hydrodynamic di-frorentlal
equations and by chemical Kinetics and diffusion. Thin ar-
ticle ocnaiders only stationary processes in which the fields
of Components -of velocity vectors, pressures, density, *to.,
41" 0017 functions Of thr�e-discablonel coordinates and are
independent of ties. In these conditions It in no longer
necessary to roriullate the Initial conditions. lixperl.ents
show that the flame stabilication in well achieved by poorly
tremallned bodies (stabilizers). In thin cane, the circula-
Ion zone behind the stabilizer to the Ignition Source. Them
:
am 6refarence.z 4 Soviet, And 2 Zngllsh.
_J~Z_ Calculation of Hydraulic Losses In the Flow
a ones In Beat Exch"gors Thmugh Channels or Lengthwise
Through Pipes 52
The article consists of two parts. The r1rctprooonts a
Miled for ealculating gas characteristics for Any. system of'
a" In the cutlet free a heat exchamror based on beat
tranerer data. Part two provides a method for calculating
gas characteristics far flows through circular pipes in hant
exchangers. It In possible to daterulne by the second method
the gas characteristics in the outlet without making a full
-beat calculation And without knowing the length of pipes, And
In special OAS** without knowing the diameter of pipes.
It is also possible to determine the'lq number directly In
Obe outlet And Inlet according to the given hydraulic re-
sIstAnce without making a heat calcuiation. There are 2
Soviet references.
v

r MERKUWV. I.A.; TUMANOV. R.I. [deceased]
- -
CaMlating the parameters of a gas in adiabatic process tak-ln-- into
consideration changes in heat capacity. Trudy 4--b.dvig. no.4:32-413
158. (MIRA 12:11)
(Thermodynamics)

14~bEll W,26~1 )
A erkulov, I. Engineer 507/29-56-11-5/28
TITLE: Automatic Airplanes
(samolety-avtomaty)
PERIODICAL: Tekhnika molodezhi,1958, Mr 11, PP. 5 - 7 (USSR)
ABSTRACT: This is a scientific article written on the basis of foreign
magazine publications and intended for the lay public. No
detailed sources are given.The article describes the various
propulsion methods used in modern aeronautics,automatic and
remote control,as well as the use of unmanned planes in actual
life. There are 6 figures.
Card 1/1

4-' f
PHASE I BC-(--;K EXFL0I1LAm1 ION Sov/4693
Nekhozhennymi tropaml Vselennoy (Untrodden Paths of the
Universe) Moscow. Izd-vo -"Pralrda,~' 1959. 63 P.
(Series, Bibllote~a 'Komsomol,3koy pravdy,' no. 11)
131,000 copies printed,
Ed- V. Kukushkin; Tech, Ed.~ T. Novikova.
PURPOSE. This popular science booklet is -Lntended f or the
general reader.
COVERAGE- The booklet .4 artlcles dealing with
early and recent efforts D.na q-.,compl12hments in space
exploration. Though popu-~ax ,-n ---,tyle, the articles are
written by leading Soviet s~,i-?nt.tsts in the field. The
sontributions of K. E. to space science
are briefly presented. space rockets,
future space craft, and c-F,-r-atn pertinent engineering
problems are disau3sed, No pz:~rsonalitles are mentioned.
No references are given.

Untrodden Paths of the Ur-iverie SOV/4693
TABLE OF CONTENTS-
I. ASSAULr.,7 OF THE SKIES
.'Merkulov, 1. [Deputy Chairman of Aatronautlice Section
'~-~or,He--fft"r&i Aero Club of 44-~he USSR] He Showed the
Way to the Stars 7
Pokrovskly, G. I. (Doctor of TeLtinical Sciences], and
P. P. Parenago, (Corresponding M~~,mber of the Academy of
Sciences USSR). A Dream Become-= a Reality 10
Chernigovskiy, V. N. [Correspond--ng Membe.- of the Academy
of Sciences USSR). Man Will Conquer Spa~le 11
Stanyukovich, K. P. [Doctor, ef" Te~thnical 3ciences]. The
Third Gigantic Step 16
Blagonravov, A. A. (Academiclan), A Flight Into the
F ut * Lz.,, e 20
-G-~2~4

ISAKOV, Fetr Kuz'mlch; KaNEITSKIT, Viktor Pavlovich; LUTSKIY, Valariy
Konstantinovich; RMOPORT, Tamara Lyudvigovna; DMORRATOV,
V.V., prof., ratsenzent; YMIN, F.A., prof., retsenzent:
Mm V, I.A.. retsenzent; ILITASHMEO, S.M., kand.takhn.
nauk. ratsen'-sa'at; VARVAROV. N.A., retsenzent; PANTZZM.
V.G.. retsenzent-, GLUKHOT, Y.V., retsenzent; GORODMSKIY.
L.M.. red.; FURMAN, G.V., tekhred.
(Artificial earth satellites; 100 questions and answers]
Iskaostvennyo aputniki zemli; 100 voprosov i otvetov. Pod
red. V.P.Kaznavokego. Moskva, Obahchestvo po rasprostra-
neniiu polit. i nauchn.znanii. 1959. 95 P. (MIRA 12:6)
(Artificial satellites)

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