SCIENTIFIC ABSTRACT GRIDCHINA, G.I. - GRIDINA, V.F.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R000516720001-9
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: January 3, 2017
• Document Release Date: July 27, 2000
• Sequence Number: 1
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT

GIZ B. 1 MMMHEV# A.
Imrgency urgieal aid in closed abdominal injurieB. Khinirgiia
15 no.9/107.924-927 162.
1. Iz Katedrata po fakultetska khirurgiia a urologiia pri.
VMI Mesh meditainaki institut) 0I.P. Pavlov" - Plovdiv.
(ABDCHINAL INJURIES) (DMGqCIES)

GINEV. Bojuj ZUNZOV Ivan
I
Biochemical and elsctr~pWysiological charges in commotio
cerebri. Xhirurgiia 15 no.9/101856-858 162.
1. Iz Katedrata po fakultetska khirurgiia s urologiia pri
VM1 [Viash meditsinski institut] "I.P. Pavlov" - Plovdiv.
( MAIN INJURY ACUTE)

KHAIDUDOVP L,, profe; AMMOV, Atqq- PANTEVAv L.;
Combined injuries bf'the abdown and pelviS. Khirurgiia 15
no.9/10:839-847 162.
(ABDOMINAL INJURIM) (PELVIS)

--qIlwp _~qq MISHEV" P..
On tuberculous disorders of the nrogenital system* Khirurgiia
15 no.11:1022-1024, -'62a
1. Iz Katedrata po fakultetska khirurglia s urologiia pri
VMI Mash zediteinskiAnatitut] OLP. Favlov - Plovdiv.
(TUBERCULOSIS UROGENITAL)

DrOwn J,"ukr.-rov,
Precancerou.3 diseases of' the -monutoh. Vop. onk. 9 no.11.-
31-17 '63. (M:EA
1. Iz kafedry fakulltetskoy kh.'rungii (rukovodituell - dotsent
Ya. Dobrev) Vysshego medit-31nskogo instituta Imeni lravicvap
Plovdiv, Bolgariya.

GINEV, B.
Chronic Invagination of the large intestine. Khirurgiia 16
no. 1:'"-?9 163.
1. Is Katedrata, po fakultetska khirurgiia pri VMI (Viseh
meditsinski institut] OI.P. Pavlov" - Plovdiv.
(INTUSSUSCEPTION) (INTESTINE LARGE)

-GRIEVA
Total renal rupture in closed abdominal injury. Khirurgiia
(Sofiia) 16 no.9:878-880 163.
1. Iv Katedrata po falcultetska khirurgiia pri %II "I.P.Pavlov*,
Plovdiv-.
4-

GITIF,V,B.; ZANZOV.,I.
Clinical value of caplllaroscopy in some surgical diseases. Folia
med. (Plovdir) 6 no.103-36 164
1. 11ohes medizinisches Institut "I.P.Pavlovl zu Plovdiv, Bulgarien,
T.,ehratuhl fur fakultatschirurgie und urologie (Vorstand.- Kand.
der med. Wissenschaft Prof. J.Dobrev).

G11141011 B') "liti"~n7f 11'.
(I,'; f~fnctlOnal. changeo In the cardia-,rancullar oystom and neutral
I'l-ketostarolds during extensive surgical interventionn. Khirur-
glift (Sofiia) 18 no.3:351-357 165.
1e V141, Plovdiv, Katedra po fakultetuka khlrurgiia (rukovoditel:
prof. IA. Dobrov).

GiNEV, B.
A cane of congenital anomaly of tho peritoneum. Y1,1rurglia
(Sofiia) 18 no.4;499-500 165.
I. Katedva po fa~ultetska k)iJrurf,,.IJa 8 urologila, Vissh
maditsinski InstItut, Plovdiv (rukov(.Altel - prof. Ia Dobrev).

PLOSKOV, D.; ANNLVV, T.; 'BEIM, KALEV, N.; KIM, G.; KIM, C. M.;
LI, C.S.; LI,Z.I.; PRMV, if.; SIMEONOV, L. -.-
Stionathorenetic surgical treatment of torpid infections with various
localizations in the light of 1. P. Pavlov's theory. Rhirurgila, Sofila
11 no.1:23-27; contd. 1958.
(INMTIONS, sur&
torpid infect. (Bul))

PIA)SKOV, D. ; AITDIMV, T. ; BRJJM, IU. ; _qINI YAIZV, N.; KIM DZHUH, KIM
E~~
CHN MION.; LI CHAN SO.; LI %ON I.; FjbITAOV, P.; sjmwNov, L.
Etiopathogenotic surgical treatment of torpid infection with various
localizations in the light of I. P. Pavlov's teaching. Xhirurgiia,
Sofia 11 n0.3:207-215 Mar 58.
(DaNCTION, surg.
in torpid infect. in various localizations (Bul))

BELOSUJDTSEVA, Ye.I.; GINEVICH, G.I,.-
- -
Continuous vapor-phase dehydrogenation of borneols to camphor and
the layout of equipment for it. Gldrollz.i leankhim.prom. 12 no-3:
15-17 '59. 'KIRK 12:6)
1. Novosibirskly khtnicheal-dy zavod.
(Borneol) (Camphor) (Dehydrogenation)

S416~~61~000100510061009
D 41 11
AqTHO R.S i Ginevi 0hq.G.I.; Artqmlyeva, L.A., Engineers.
TITLE- New' appa,ratus fo rvaporizing and mixing liquid organic com-
pound.s
PERIODICAL. Xhimicheskoye washinostroyeniye, no - 5, 1961, 45-46
TEXT: The articleedntains a detailed description of the design and opera-''
tion of a,new apparatus (Fig.., 2) for raixinp , nd vaporizing liquid organic
a
cbm~,ounds for which.G,I. Ginevich P.A. Artemlyeva and Ya. A. Toapnik have
obtained the author!a o6rtificate no. 129809 dated October 21, 1959.. The
apparatus is based on the-lay.or-evaporation principle and replaces the
bubbie-type. evaporator. which has..larger dimensions and is less efficient.
There are 2 f i gur e 9
3'
Card. 1/

New apparatus for
S/184/61/060/005/008/009
D041/Dl!3
Legend: 1 -- body of the apparatus; 2 -- boiy of the mixer; 3 -- sleeve
containing the thermo-couple; 4 -- steam cushioning appliance; 5 -- mixing
chamber; 6 -- protruded tube; 7 -- protruded tube; 8 electric valve;
9 pneumatic slide valve; 10 -- charging boxes; 11 con.tainers;
12 tube; 13 -- tube; 14 -- tube; 15 -- protruded tube; 16 -- protrudk
tube; 17 -- diaphragm; 16 -- flow meter; 19 -- pneumatic valve; 20 --
differntial pressure meter; 21 -- protruded tube; 22 -- vacuum gage;
23 -- control panel; 24 --m_protruded tube; 25 -- secondary device; 26 -- -
secondary device; 27 -- protruded tube; 28 -- protruded tube; 29 -- dif-
ferential pressure meter; 30 -- pipe; 31 -- pneumatic slide valve;
32 -- diaphragm. 33 exhaust gases from the adsorption columns; 34 -- to
the vacuum Pump; 35 alcohol; 36 -,- air.
V
Card 3/3

GINEVICH, G.I.; PREOBRAZIIENSKIY, V.N.; SPIRIN, V.V.
Continuous unit for milling aminoplastics. Plast.massy-no.ll--
58-59 161. (MIRA 14:10)
(Aminoplasties) (Milling machinery)

-GINEVICH, G.I.
Redesigning the absorption system of a formalin plant. Khim.prom.
no.8:710 D '59. (HIBA 13:6)
1. Novosibirskiy khimicheskiy zavod.
(Formaldebyde) (Plate towers)

GINE;VXCK,.Z.I.-.
Electric furnace for curing performs of fluorplast-4. Plast.
massy no.4:45-46 161. (MIRA 14:4)
(Plastics Industry-Equipment and supplies)

GINEVICH, G.I.; SKUE, G.I.; sHCHUGAREV, V.T.
Studying the process of continuous distilling-off of highly
volatile substances in the production of plasticisers from
dibutylphthalate and dioctylphthalate. Plast.massy no.3:64-
67 164. (MIRA 17:3)

NAKROKHIN, B.G.; SHIBANOV, G.V.1 GINEVICII, G.I.; OBRAZTSOV, A.I.;
"' NAXROKIIIN, V.B.; ITEMERG, Sh.M.;
MATROS, Yli.Sh.; SKUE, G.I.;
RASHRAGOVICH, Kh.D.
Oxidation of methanol to formn1dohyda an oxide entalysts.
Khtm. prom. 41 no.2:17-19 F 165. (MIRA 18W

CHEKIN, V.F.; GINEVSKAYA,-I.A.-,-
Modernization of eye instruments. Vest. oft. 73 no. 3:53-54 My-Je
,6o. (MIRA 14:1)
(EYE, I14STRUMENT-o AND APPARATUS FOR)

Gii,mVSKIY A.; KAREPFENKO, I.; FEPOROVIC., N.
Deliveries made by the Department of Technical Control
Must he of high quality. Podn org IS no. 3;140 Nr 164.

GIITP,VSKIY, A,S (Moskva)
" ~~?
Energy characteristics of presomic diffuser conduits. Izv.AN SSSR Otd.tekh.
nauk ne-3:152-154 Mr 156. 092A 9: 7)
(Gas flow) (Pipe--Hydrodynamics)

PHASE I BOOK EXPLOITATION SOV/6580
Solodkin, Yeflat YerremovieN and Aron Seqenovich'Ginevskly
Turbulentnoye ~echeniye vya2koy zhidkosti v nachallnykh uohaetkakh
osesImmetrIchnykh I ploskikh kanalov (Turbulent Flow of Viscous
Fluid In Inlet Sections of Axisirmetric and Plane Channels)
Moscow, Oborongiz, 1957. 55 P..., (Seriess Moscow.,
Tsentrallnyy-aero-gidrodinamicheskiy institut. Trudy., no. 701)
No,. of copies printed not giveno.
Ed.s Yu. 0. Za%harov,, Candidate,of Technical Sciences; Ed. of
Publishing Houset L.. I. Shiynfayn; Tech. Ed.: N. A.
Pukhlikova; Managing Ed.: Ye..V. Latynin,, Engineer.
PURPOSEt This book is intended for te6hnical personnel concerned
with fluid flow*
COVERAGEt The book disousses the flow' ~ of* viscous f1did In the
inle ection of ducts of various dross sections. In the case
of axisymmetrical, duct-, it Is shown that a better agreement
is obtained between the:calculatediand the experimental,results
ard 1/,3

Turbulent Flow.of-VIscoul (Cont. SOV/6580
by taking into a6count-the transverse 'Ourvature of the
-surface than by employlng the usual theories based on the
power or logarithmic law of velocity distribution in the boundary
layer, Howevers In the case of a plans duct, good agreement
between the calculation and the experiment is obtained
using the logarithmic law of velocity distribution. The
eharacteristice of a circular tube and a plane duct can be
considered as extreme cases of an annular cross-section
duct, No personalities are mentioned. Three Soviet and
three Germfn references are found In the text.
TABLE OF CONTENTSt
Ch I, Turbulent Boundary Layer and Resistance In the Inlet
Section of an AxIsymetrieal Divergent Duct with Zero-
Pressure Gradient 3
Ch 3:1. Turbulent Boundary Layer and Resistance in the Inlet
Section of a Circular Duct 26
0 ard 2/,B

AIV16094 BOCK EMILOITATIal S/0795
Solcdkin, Yefim Yefremovich; Ginevskly, Aron Semenov.ich
Turbulent flow of a viscous fluid in the initial sections of axially symmetric
and plane channels (Turbulentnoye techen1ye vyazkoy zhidkosti v nachalIny*kh
uchastkakh osesimetrichny*kh I plosk-11(h kanalov) Moscow, Oborongiz, 3.957.
55 p. illus. No.'of copies not given. Editort Zrakharov, Yu. G. (Candidate
of Technical Sciences)l Deputy editori lety*nin, Ya. V. (Engineer); Publishing
house editort Sheynfayn, L. I.; Technical editor: Pukhlikova, N. A.
Series note; Moscow* Teentrallny*Y aero-gidrodinaaicheskly~ institut. Trudy*,
no. 701
TCP3r, TAGS: turbulent flow,, viscous fluid, initial section, axially symmetric
channel, flat channel, velocity d-4.stribution,, circular pi tur lent boundaz7
pe) bu
layer., drug
PURPOSE AND COVERAM The flaw of a viscous fluld in the initial section of
channels of varicus cross section is an&3,y-.ed in this brochure.! It is shown that
V,

AM4016094
consideration of the cross-sectional curvature of the surface in the case of an
axially symmetric channel will give better agreement between experimental and
calculated characteristics than the usual theories utilizing exponential or loga-~
rithmic laws of velocity distribution In the boundary layer. In the case of the
flat channel, the logarithmic law will provide good agreement between calculated
and exverimental data. The characteristics of a circular pipe and a-flat channell:
can be analyzed as limit cases of a channel.of annular cross section.
TABLE OF CCNTEM:
L Turbulent boundar7 layer and drag of the initial section of an axially sym-
metric expanding channel with a zero pressure gradient 3
11. Turbulent baindRry layer and drag of the initial section of a circular pipe
26
1IL Turbulent boundary/layer and drag of the initial section of a flat chann*l
41
,-C,ard-.

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trARMUR AIR -4~ Ew

SOLODKIN, T9.Te.,IMnd.tekhn.nauk; GINICVSKIY, A.S.
- ~,
Determining characteristics of the turbulent boundary layer
and the resistance of long axiaymmetric bodies. Trudy NTO
sud.prom. 7 no.2:81-106 '57. (MIU 12:1)
(Stability of ships)

SOV/ I Z4-58 -I 1--- 1 ?695
Translation from: Referativnyy zhurnal, Mekhanika, 1958, Nr 11, p 109 (USSR)
AUTHOIt- Ginevskiy, A. S.
TITLE- Influence of the Viscosity of a Fluid on the Intensity of the Circulation
About a Fluid Foil in a Hydrodynamic Cascade (Vliyaniye vyazkosti
zhidkosti na velichinu tsirkulyatsii ~,,okrug profilya gidrodinami--
cheskoy reshetki)
PERIODIGAL: V sb.: Prom. aerodinamika. Nr 9, Moscow, Oborongiz, 1957,
pp 5-15
ABSTRACT: An investigation of the dependence on the fundamental geometric
parameters of a plane cascade of the ratio kr = r'/ rid'. i. e. , the
ratio of the circulation about a cascade foil of a viscous incompres-
sible fluid flow and the corresponding circulation of an ideal fluid.
It is assumed that the fluid foil differs only little from straight seg
ments. Equating to zero the total vorticity of the flow downstream of
the cascade is tantamount to equating the velocities at the outer bound--
ary of the boundary layer shedding from the fluid foil. Applying this
condition to the flow of an ideal fluid through a cascade of foils, the
Card 1/2 author obtains (with an accuracy up to the terms of 6?- order)

SOV/IZ4-58-11--12695
Influence of the Viscosity of a Fluid on the Intensity of the Circulation (cont.
k k V' -6 V 6N
-here k is a function of the solidity ratio and escape losses of the cascade, and
6v and 6N are the nondimensional thicknesses of the boundary layers shedding
from the upper and lower sides of the foil, respectively. The calculated values of
kr tend toward unity as the solidity ratio increases and the angle of escape
decreases. Using experimental data for compressor cascades consisting of solid
fluid foils with a shockfree entry, the author obtains kr = 0.86-0.93. The
results of the investigation, on the whole, bear a qualitative character.
L. G. Naumova
Card 2/2

1UTHORt FEDYAYEVSKIY,K.K.I.GINEVSKIY,A.S. PA - 2127
TITLE: The Computation Method of a Turbulent Boundary Layer in the Case
of the Existence of a Transverse Pressure Gradient (Setod rascheta
turbulentnogo pogranichnogo sloya pri nalichii prodollnogo
gradyenta davleniya. Russian).
PERIODICAL: Zhurnal Tekhn. Piz., 1957, Vol 27, Nr 2, PP 309 - 326 (U.6.3-R.)
Received, 3 / 1957 Reviewed: 4 / 1957
ABSTRACT: A simple approximated method for the computation of the charac-
teristics of a turbulent boundary player is described. For the pur-
pose of a simplification of the equations for the velocity profile
and the law of resistance not T, butf-T is represented as a poly-
nomial according to y-powers. At first the velocity profile is de-
rived in a turbulent 1~oundary layer. Next, the formula for the law
of resistance is derived and reduced to a form suited for compu-
tation. The significance of the constants X and o( is-mentionded. Both
are experimentally determined. For practical purposes'K- 0.4 and
c~ - 11,5 can be assumed. A diagram represents the law of resistance.
In the next chapter the impulse equations are integrated and it is
shown on this basis in what manner the location of the point in which
the liberation of the turbulent boundary layer takes place is de-
termined. Computed and experimental results were compared and were
found to be in good agreement. The computation method of the cha-
racteristics of the twodimensional turbulent boundary layer with
Card 1/2 essential transverce cross gradients of pressure is distinguished

PA - 2127
The Computation Method of a Turbulent Boundary layer in the Case
of the Existence of a Transverse Pressure Gradient.
by a sufficient operation capacity and makes it possible already
in first approximation, to determine the conditional thickness of the
layer as well as the value of the local friction coefficient and the
location of the point at which liberation takes place. The graphical
representation of the law of resistance obtained shows the possi-
bility of the ocourence of special states accompanied by a con-
siderable reduction of the local friction ceefficient. Prom this it
follows immediately that at certain relations and in the case of a po
sitive cross gradient of pressure conditions are created which
lead to the liberation of the turbulent boundary layer. (11 illu a-
trations and 2 tables)
ASSOCIATION: Not given
PRESENTED BYt
SUBMITTEDi 25.4-1956
AVAILABLE: Library of Congress.
Card 2/2

SOV/ 124-58-8-8889
T ran slation from: Referativnyyzhurnal, Mekhanika, 1958, Nr8, p80(USSR)
AUTHORS: Solodkin, Ye.YC
TITLE: The Turbulent Flow of a Viscous Fluid in the Inlet Portion of
Axisymmetric and Plane Channels (Turbulentnoye techeniye
vyazkoy zhidkosti v nachat'nykh uchastkakh osesimmetrichnykh
i ploskikh kanalov)
PERIODICAL: Tr. Tsentr. acro-gidrodinam. in-ta, 1957, Nr 701, 57 pp,
ill.
ABSTRACT: An approximate solution is offered for the problem of the
turbulent boundary layer and resistance in the inlet portion of:
1) An axisymmetric divergent channel having a zero pressure
gradient, 2) a circular conduit, and 3) a plane channel.
Attention is given herein to the matter of the influence exerted
by the transverse curvature of the channel surface on the vel-
ocity profile, the local friction coefficient, and on the other
characteristics of the turbulent boundary layer. The authors
considered that in the channel's inlet section the velocity is
constant and that the static pressure across the width of the
Card 1/4 boundary layer does not vary. Analysis of the differential

SOV/ IZ4-58-8-8889
The Turbulent Flow of a Viscous Fluid (cont.)
equations describing the mean stationary flow in the channel's turbulent
boundary layer revealed that near the surface (correct up to the terms of
the third order) the tangential-stress distribution across the width of the
layer obeys the condition r T = const = ro T0' Here r is the radius of a
fluid element in the boundary layer, r. is the radius of the channel cross
section, T is the frictional stress in the boundary layer, and T 0 is the
frictional stress a~ the cha2net surface. Taken together with the Prandtl
relationship T= P I (all/ay) , [ wherein P is the density of the liquid, 1 the
the turbulent mixing length, and (3u/ dy the mean -flow- velocity gradient nor-
mat to the channel wall] , this permits the evolvement of a formula for the
velocity profile in the turbulent boundary layer of an axisymmetric channel.
When r,-- , the formula reverts to the well-known logarithmic velocity
profile of the turbulent layer of a plate. In the in-imediate vicinity of the
channel wall the velocity distribution is arrived at on the basis of the hypo-
thesis which posits the existence of a laminar sublayer in which T= ~t i)U/Z)y 11
being the viscosity coefficient of the liquid). The resistance law is obtained
by equating the two velocity distributions at the boundary of the laminar sub-
layer. The thickness of the laminar sublayer is determined from the usual
relationship, 60= al v /v,, , wherein v=ji/p Tile calculations were
Card 2/4

SOV/124-58-8-8889
The Turbulent Flow of a Viscous Fluid (cont.)
performed on the assumption that the turbulence constants k, and CL I main-
tain values equaling the corresponding values for the case of a plate, narnely,
kl=0.392 and al= 11.5. As a result of integration of the impulse equation, a
determination is made, for different values of the Reynolds number, of the
aerodynamic characteristics of an axisymmetric divergent channel having a
zero pressure gradient, and an analysis is performed of the influence
exerted by the transverse curvature of a concave surface on the character-
istics of the boundary layer. It is demonstrated that because of the curva-
ture of the surface the velocity profile becomes less bulgy, which circum-
stance reduces correspondingly the coefficient of frictional resistance (as
compared with cases in which the channel is a flat surface). Moreover, the
influence exerted by a transverse curvature of the surface becomes espec-
ially significant when the ratio 6/ro approaches unity. The data obtained
are used to solve next the problem relating to the inlet portion of a circular
conduit. Here the*.influence exerted by the longitudinal pressure gradient is
taken into account'8nly in the impulse equation. By solving the problem the
authors arrive at the aerodynamic characteristics of the inlet portion of a
circular conduit, including the length of the inlet portion f6r.diffe rent- values
of the Reynolds number. When determined by this means, the length of a
circular conduit's inlet portion exceeds by a factor of approximately three
Card 3/4

SOV/ 124-58-8-8889
The Turbulent Flow of a Viscous Fluid (cont.)
its length as calculated from the velocity power profile (as per the Lattsko
theory), and exceeds by a factor of two its length as calculated with a loga-
rithrnic velocity profile (as per the Shablevskiy theory), but it does approx-
imate very closely the length obtained experimentally (by Kirsten). In con-
clusion the aerodynamic characteristics are calculated for the inlet portion
of a plane channel for a logarithmic velocity distribution in the boundary
layer. Inasmuch as a circular conduit and a plane conduit represent two
limiting cases of an annular-section conduit, the relationship found to exist
between the aerodynamic characteristics and the length of either type of
channel is depicted for both cases on a single graph. It is shown that, if a
channel's hydraulic radius is taken as its characteristic linear dimension,
the stated relationships will be virtually the same in the two cases, i.e., in
that of a plane and in that of a circular conduit, and that they may therefore
be employed to determine the characteristics of the inlet portion of an
annular-section conduit.
V.I. Yagodkin
Card 4/4

DOVZHIK, Sanuil Aeonovich; GINEVSKIT, A.S., kand.tekhn.nauk,red.; SHEYNFAYN, L.I.,
Izdatel'okly red.; MSTIGNET9VA, M.N.,tekhn.red,
[Designing blades of subsonic axial-fl(ror compreasors] Profilirovanig
loputok onevogo dozvukovop kompreasora. Moskva, Oborongiz. 1958.
138P. (Promyehlennaia aarodinamika, No.11) (MIRA 11:12)
(Compressors--Blades) (Aerodynamics)

YUDIN, Yevgeniy Yakovlevich; GIITEVSKIY,.A.S.., kand.tekhn.nauk, red;
SHEYRFATIT, L.I., izdatel'skiy red.; ZUDAKIN, I.K., tekhn.red.
[Investigation of noises in ventilation inBtallations and methods
for preventing them] Iseledovania shum ventiliatornykh ustanovok i
metodov bor'by a nim. Moskva, Goa. izd-vo obor. promyshl., 1958.
227 P. (Moscow, TSentralInyi aero-gidrodinamicheakii institut.
Trudy, no-713). (MIRA 11-4)
(Ventilation) (Acoustical engineering)

GINEVSKIY.--A.S. -
InTOBtigsting two BYstems for changing blading areas in ax1al-
flow compressor stages. From. aerodin. no.10:61-76 '58-
(MIRA 11:8)
(Compressors)

__. IV Y A.S.; SOLODKIN, Ye.Te. (Hoskva)
4--- -
Effect of lateral surface curvature on the characteristics of
the axieymetric turbulent boundary layer. Prikl.mat. I mekh.
22 no.6:819-825 N-D '58. (MIRA 11:12)
(Boundary layer)

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SOV/24-59-1-7/35
AUTHORS: Ginevskiy, A.S. and Dovzhik, S.A., (Moscow)
TITLE: -11Y-P~e~a ~e e~rmination cf the Pressure Loss in the
Rotating Vanes of Axial Compressors (Eksperimentallnoye
issledovaniye poter7 davleniya vo -irrashchayushchemsya
kolese osevogo kompressora)
PERIODICAL: Izve stiya Akademii Nauk SSSR, Otdeleniye Teklmicheskikh
Nauk, Energetika i Avtomatika,,1959;Nr l,pp 4r---52 (USSR)
ABSTRACT:
Card 1/5
In this paper, the results are described of
experimental investigation of the pressure loss in the
rotating vanes of an axial compressor at low
circumferential speeds., On the basis of measurement of
the total pressure by means of a radial Pitot rake
rotating together with the vanes., the structure was
investigated of the losses in the space between the
rotating vanes and certain quantitative data were
obtained which characterise -IL-he total map)Atude of the
complete presaure loss as well aB the distribution of
the losses along the radius within a wide range of
operating regimes. The work was performed on an axial
compressor cif 600 mm outer diameter, 300 mm inner
diameter, delivering air in ari axial-L direction. The vane

Experimental Determination of "he Pressure Loss in t-he hotiating
Vanes of Axial Compressors
profile was altered to give co-n-stanI.-I -circulation along
the radius; full details are gi-jen of the -vane profile.
Elleasurements of total head wei-, aide, using a Pitot rake
r, atinS Ath -Ij-he vanes and -.apa'.1e of ifleasuring pressure
, -, 18 different, radial positions simultaneously, i.e.
covering the space between the rcc)Ls ~2f the blades and
the casing. InSuffi-.ient detail is ffiven o.-If the method
of measurement, manomEter ---n,,-ier;tIj.Lrjns etc. The equipment
p i (,, . of t1l ''-c'
allaws a complete t u~?ii 10 v Isal pressure in the
region between the blades tc, ~e bu--tt u~ and the
measixcements are expressed in a n-3:i--ditnensio-al form.
A-PO = PCI - P02 is t;-b-p to-ral pressu-na in front of the
vane in relative motion; P02 is the total pressure
behind the vane.
2
&)0,,(
where is the a,-i.T- dens-LtY; VR -J-s the. c,Jr3umferential
Card 2/5 speed at tile outer -radiu.,-, of -t-rie wl-,eel; the mean value

'~OV/24-59-1-7/35
Experimental Deterraina ion of the Press-are Loss in the Rotating
Vanes of Axial Compressors
of the loss coefficient at
determined by means of the
,AH = 1 Ah (T )d(p
(PO ~
0
Card 3/5
a given radius, AH can be
following equation:
-~a k (3)
z
where k is the number of spaces between vanes. Thus,
the pressure loss coeffiaient for all radii for any
working condition is given by:
I
Ca
Z,5H 6H (r' ) ca l(r.)rdr6 ca -
S' uR
0
where ca is the absolute flow velocity in the vane.
Eq (5) expresses the flow rate ~3oefficient c~o and
for a series of c7o values the theoretical head HT
is calculated anda also the coefficient of the total
head. H. The Reynolds number, based on the relative flow
I

1~ 011/24-5~~/-1-7/ 35
Experimental Determination of the Pressure Loss in the Rotating
Vanes of Axial Compressors
velecity in the wheel, is 2 x 10 Fig 2 shows the
stiucttLre- of the heaA lr-,ss A h over the -~,-anss at
different; radii, ran.-ing from the -;iane tip to close to
the root.. Th-ere is much more j-a-_7istion in these extreme
regic,ns. Fig 3 shows polar plc.'s of -the head loss for
different working :~~onditiors. 0--,er most of the region
jah is praebinally zero tut- ixv,,reases in the space
between successive -janes due. to Irl-file 'Iess and friction
cf ai:? on blade surfaces. TI).Pr--- is also some loss over
the radial gap between -1-7h-; blade. tip aLd the casing,
while at tLe root sec-.til-a the pi:essl,,re loss is not only
due to fri-7ttion of the air r~n the hub surface but also
due to the two bourdarles formed by -the blades and the
hub with the assc~~iated secondary flcw icsses. A brief
discussion is gi-ven of the fact~:-j.~s influencing this
head loss, mainly concerned with t-',-,-e anr~-le of attack of
the blades and the bo-undary Fig 4
shows the of head lo,=-zs radius 2._n different
Card 4/5 woi~lking an attempt ig made to

SOV/24-59-1-7/35
Experimental Determination of the Pressure Loss in the Rotating
Vanes of Axial Compressors
divide up the losses which ccc-ar o-qer the vane. Fig 5
shows the total Z,6H divided into the le loss:
1~ end flow and secondary flow loss; 2~roufitput loss;
3 it is evident that the profile loss makes up
50 to 55% of the total. Fig 6 shows the efficiency
variation with working conditions. There are 6 figures
and 6 references of which 2 are Soviet, 1 English and
3 German.
SUBMITTED: 22nd August- 1958
Card 5/25

AUTHOR: Ginevskiy, A. S. (Moscow)
TITLE: Turbulent Trail-'and Stream
of a Longitudinal Pressure
struya v sputnom potoke pri
dw,rleniya)
SOV/179-59-2-5/40
in a Vol-tex Flrw with the Presence
Gradient (Turbulentnyye sled i
nallichii p-rodollno-c a-radiyenta
0 C~
PERIODICAL: Izveatiya kkademii nauk SSSR OTN Mekhanika i mashino-
stroyeniye, 1959, Nr 2, PP 31-36 (USSR)
ABSTRACT: An effect of the pressure gradient on the trail in a flow
around a rigid body in �~he aerodynami,,-al tube is considerable
(Fig la). Similarly, this effect can 'be noticeable in the
case of a stream (Fig 'L.'P). A method cif calculation of the
turbulence is described by the author, taking into account
the longitudinal pressure gradient, The equation of turbu-
lence in this trail or stream in this case will take a gen-
eral form (1) , where x and y - longitudinal and trans-
verse co-ordinates respectively, u and v - mean compon-
ents of the velocity along the axes x and y respectively,
tangent tension, density, p - pressure. The
Card 1/4

Ov/j
Turbulent Trail and Stream in a Vortex Flcjlv with th~~ Pre.--:Zence of a
Longitudinal Pressure Gi-adient
distribution of the tangent tension is Siven by Eqs (2), (4)
and 5). The last two expressions are subs ti 'Ju ted in the
Eqs R) and (7) which determine the, velocity in the tr-ail
(or stream) and at the boundary respectively. Tile simultan-
eous solution of both equations gives the expression (8). To
find the rate of an increase (or decrease) of the velocity
(Fig 1), the- formula (9) is derived for u ~ U 7 u 1 and
um = U 7+. uim . The velocity profile along the axis can be
derived from Eq (7), which can be written in the forms
Eqs (10) and (11). The latter can be integrated wlien the
relation (12) is determined (6' and 61' -- displacement
and loss of impulse, respectively). Then the expressions
(13) and (14) are obtained ( V,,., -- velooit-.7 of inflow,
811 - loss of impulse behind the body). Th-.~ ~-ocfft,_-ient of
W
body resistance, Eq (1-6) ( L -- characte-rio-U,.- linea-r- dimen-
sion), when substituted in the Eq (11), giveq ~h!~ final diff-
erential equation (17). Thie equation etin 6f-~ .-'Irtt..,_,grated in
the case of the longitudinal gi~adient wl'IC'~ft U - const , while
Card 2/4

JOV/17()-
Turbulent Trail and Stream in a Vcrfj-ey- Flow with the Pr-_Sence of a
Longitudinal Pressure Gradient
the relationship of 6 and u1IIq 0 oan be definad as Eq (18)
( z1 = r,XL for trail, Z 2 = 1/1/2p(~ fcr ovream), which,
when substituted into Eq (1?) gives the usual differential
equation (19). In the case of the trail, the exprpssion
(20) can be dr;;rIved froin Eq (19). The value of' 0 is found
experimentally. It can be detei~ianed from Eq.-, (121) and (22)
f or the trail. as P - 1/16 0. 19? and f rom Eqs (2-3) and
(24) for the stream as 0 - 0.035 7(- 0.11 The determina-
tion of the profile velocity can be SIMPLIA'Iiid when Eq (25)
is applied ( )t -- experilitental Wh 1(Al, together
with Eq (4), will give the relationship W). Fig 2 illus-
trates the ~,-omparison of the results obtained from the various
formulae: the rlirves 12 2, 3 were calculated from Eqs (9),
(26) and (28).~, 4 a-zid 5 - experimental paints fcr the plane
turbulent trail and stream, vespectively, 6 and ? - experi-
mental points for the. coaxial turbulent Lrail and stream,
respectively. The difference between the tlieoretical and
Card 3/4

3',') 7/! ~-)
Turbulent Trail and Stream in a Vortex Flow with the Presence of a
Longitudinal Preseure Gradient
experimental determination of the velocity profile can be
improved by a more exact approximation of the tangent ten-
sion, e.g. the Eq (28) can be used for the conditions (3)
and T expreosed by Eq (2'7). Tha.re aro 2 figures and
9 references, of which 7 are Soviet and 2' Qcrman.
SUBMITTED: August 22, 19~8.
Card 4/4

SO V/1-79- 59- 3-4o/4 5
AUTHORS: Ginevskiy, A. S. and Fedyayevskiy, K. K. (Moscow)
TITLE.- Some Laws of the Unsteady, Forward Motion of Bodies in
a Viscous Liquid (Nekotoryye zakonomernosti pri
neustanovivshemsya postupatellnom dvizhenii tel v
vyazkoy zhidkosti)
PERIODICAL: Izvestiya Alcademii nauk SSSR, OWelenive telchnicheskilih
nauk, Mekhanika i inashinostroyeniye, 1959, Nr 3,
PP 207-209 WSSR)
ABSTRACT: The interaction force X between a body and a liquid
can be defined as Eq ( I where e, 11 density and
viscosity of a liquid respectively, g gravity,
V and dV/dt - velocity and acceleration of a body,
L - characteristic linear magnittide, N Re - Reynold's
number, NFr - Froude number, N W - dimensionless
acceleration characterizing the relationship of forces
of inertia, Eq (2). The actual relationship of
f1(N Re' NFr'NW and f 2(NW) is determined by the shape
of a body and by the character of the motion and flow.
In the case of laminar motion of a sphere in a viscous
Card 1/2 liquid, the coefficient of resistance can be shown as
Eq (3) or as Eq (5) in a general case (L - radius of the

SO V11 79- 5 9- 3-40/4 5
Some Laws of the Unsteady, Forward Motion of Bodies in a Viscous
Liquid
sphere). The motion in this case depends on the initial
condition, Eq (4), where the ratio N Rh INWcan be found
from Eq (6). Experiments were carrie out by the
Leningrad Ship Building Institute, where Acx was
investigated in relation to the parameters N Re and NW.
Fig 1 illustrates the results obtained for
L cx (N Re ) and Ac x(NW) determined for the types of motion
characterized by the load P. Fig 2 shows the experimental
points of AC x(N Re INW). Fig 3 represents the results of
the experiments for various velocities and accelerations,
It is evident from the experiments that in order to
determine the dynamic properties of similar motions,of a
body in a viscous liquid, the ratio N Re INW or N W should
be considered in addition to N Re and N F~'
There are 3 figures and 5 references, 2 0 which are
Soviet, 2 English and 1 Italian.
SUBMITTED: November 12, 1958
Card 2/2

POWDKIN, Te.Te.
Aerodynamic characteristics of the entrance region of a ring-!shaped
pipe with turbulent flow in the boundary layer. From. aerodin. no.12:
155-167 '59. OGBA 13 ; 1 )
(Pipe-AeroOnamice)

SOLODKIN, Ye.Ye.; GIMUSKIY, A.S,
Affect of initial unsteadiness in the flow on characteristics
of diffusion channels. Prom. aerodin. no.12:168-180 159.
(MIRA 13:1)
Orluld dynamics)

GINWSKIr -&___
Integral methods for solving problems of a free turbulence.
Prom.aeradin. no.15:47-71 '59- (KM 13:8)
(Tarbulence)

AVDUYEVMCIY, VHevolod Sorgeyevich, doteent: DANILOV. Yuriy Ivanovich,
dotsent; KOSHKIN, Valentin Konstantinovich, prof.; KUTYRIN,
Igor' Nikolayevich. d)tsent; MIKKAYLOYA. Militse Mitrofenovne,
dotsent; MIXHIM. Turiy Sergeyevich, dotsent; SERGELI,
-:Ng Sergeyevich, dotsent; GINNYgIYp A.$., kand.tekhn.nauke
red"; S MA # B.A., izdat.red.; ROZHIN, V.P., tekhn.red.
[J~iieementale of heat transfer in aeronautical and focket
equi~w6ntl Osnovy teploperedachi v aviatsionnoi i raketnoi
tekhnika. Pod obahchei red. V.K.Koshkina. Moekva, Goo.
nauahno--tekhn.izd-vo Oborongiz, 1960. 388 p.
(MIRA 14:4)
(Rockets (Aeronautics)) (Airplanea)
(Artificial satellites) (Heat---Transmission)

r- v
PHASE I BOOK EXPLOITATION SOV//.820
Ushakov, Konstantin Andreyevich, Professor, Iosif Veniamenovich Brusilovskiy, and
Aleksandr Romanovich Bushell
Aerodinamika osevykh ventilyatorov i elementy ikh konstruktsiy (Aerodynamics of
Axial-Flow Fans and Elements of Their Structure) Moscow, Gosgorte1fihizdiLt,,
1960. 421 p. Errata slip inserted. R,OOO copies printed.
Ed.: Konstantin Andreyevich Ushakov, Professor; Ed. of Publishing House: G.B.
D'yakova; Tech. Eds.: S.Ya. Shklyar, and Z.A. Korovenkova.
PURPOSE: This book is intended for workers of scientific research institutes and
planning and design institutes of the ore-mining industry, and may be used by
the personnel of other organizations concerned with the design and operation Cf
axial-flow fans.
COVERAGE: The authors describe a modern method of the aerodynamic calculation of
axial-flow fans and critically review the design of mine-ventilating machines.
Their method of profiling bladed rings is said to be a synthesis of the theory
of two-dimensional cascades of airfoils, testing data, and of the generalized
results of various systematic experimental investigations carried out by the
C a-r d_1_/r8_ - -

Aerodynamics of Axial-Flow Fans (Cont.) SOV/4820
authors at the Tsentrallnyy aero-gidrodinamicheskiy institut (Central Aero-
hA'rodynamical Institute). Individual chapters were written as follows:
K.A. Ushakov, Introduction, See. 3 and 6 of Ch. III, Sec. 4 of Ch. VI, and
together with A~.R. Bushell, Ch. XII (except Sec - 3); I.V. Brusilovskiy, Ch. I
(except Sec. 4), Ch. II, Ch. III (except Sec. 2,3, and 6), Ch. IV, V, VI
(except See. 4), Sec. 3 and 4 of Ch. VII, Ch. VIII (except Sec. 4 and 5), and
Ch. X. (except Sec. 3); A.R. Bushel', Ch. VII (except Sec. 3 and 4), Sec. 4
and 5 of Ch. VIII, Sec. 3 of Ch. X, Sec. 3 of Ch. XII, Ch. XIII and Ch. XIV;
A.S. Ginevskiy, Sec. 4 of Ch. 1; A.A. Dzidziguri, Ch. IX; 1.0. Kersteny Ch.
T15M.V-:"r6f~snikov, Sec. 2 of Ch. III. No personalities are mentioned. There
are 107 references: 87 Soviet, 11 German, and 9 English.
TABLE OF CONTENTS:
Foreword 3
Introduction
Ca=d-k/l~--

Aerodynamics of Axial-Flow Fans (Cont.) SOV/48210
PART I. AERODYNAMICS OF AXIAL-FLOW FANS
Ch. 1. General. Information From the Theory of Fans and Cascades of Airfoils 15
1. Bernoulli and Euler equation 15
2. Geometric parameters of a oascade of airfoils and flow parameters 22
3. Zhukovskiyls theorem 29
Aerodynamic characteristics of two-dimensional cascades of airfoils 39
Ch. ii. Th:ory of Axial-Flow Fans 57
0 or
1 to 57
2: 1 diagram of a one-stage fan NA + K + SA [guiding vanes + rotor +
l diagr
~
z evan
noz vanes] 64
M
3. Multis ge axial-flow fans 75
Ltis ge
er_
4. Counter- ow fans 81
Coun%t
Ch. III. Influence'Vf Air Viscosity. Efficiency Coefficient. Fan's Charac-
teristics 86
1. Air-vi~do6ity. uAdary layer. Reynolds number 86
ar
2. Profile and secon losses 91
3. Numberof blades 105
1 ~
4. Efficiency coefficient the cascade and fan 110

Klm2k, US--k, 5-13 61.
P.4-2952
5A
253. 5_1,. T. L N, ,~1-, :~Illf%..,i- of C-t--'
th. or
254. T. L. Fr-~'~ma, On F-t Tr~afer Im rl~ in t~, Ltlet P-t
of a Ibt
255. G. Soluttcr of ~~ P-blc~- 6"1" ;'-tie C~av-'.:~.5
1.
~
by
256. L. K. 5 folutio-- of Sc= P~ob'.~ of !4-,t'.cn of h

257. S. L. D~tk--, On-Cnaf~-~~! 7r,".1c.=,tic. of

258. of Fmtlr~: or ptct~- wd-.-
,
A-eU=
259. 1. R. ,Mkk, a-Issi,ity of
260. T. S. Tl=f~*,, V. M. F. R. -toary or R-ner-*l=

261. E. 1. Thu XW.I! of Elat Tr~~fer M--h tte

AC--tA
262.

263. e. md p- t, or Thl.-I

26.%. L- S. - E~t Mhss t 'ai=-. ?r- -d
265. Y.. V. L.;-~, R-t md t 71~- of' C.-

2-67.

26B. V. 1. X. Eh. llbr~gloo~, S. i.

269. A. A. C~ th. n--- or TW.- -a of r.!-,
(TrA stalwa P-o-b7=-T-

D234/D308
UTHOI
RS: Dovzhik, S. A. and Ginevskiz.-A. 13.
ri -rT- E
Pressure losses in blade rims of an axial infrasonic
comoressor
SOURCE: Hoscow. TsentralInyy aero-gidrodinamicheskiy insti-tut,
Promyshlennaya aerodinamika. no. 20, 1961. Osevyye
dozvukovyye kompressory statsiona.-nogo tipa, 5-56
T-.-:'XT: The results are given of an experimental investigation of
pressure losses in the inlet (directing) device and in the working
wheel of the compressor. The structure of pressure losses was stu-.,-
L
died at stream velocities c a = 40 - 60 m/sec; the'values of loss
coefficients for the directing device were plotted against the ra-
dius, the axial velocity and the Re number; the power coefficient
and the full pressure coefficient of the working wheel against the
radius and the flow coefficient. On the baziQ of these results
formulas determining separate components of the.losees are impro-
S/632/61/000/020/001/008
Card 1/2

S/~32/61/000/020/001/00&
Pressure losses in ... D234/D308
ved and more accurate values are found for coefficients occurring
A. method of constructing a pressure characteristic of a
staisre is aejcribed; characteristics of several single-stage com-
pressors determined with its aid are compared with experimental
caaracteristica. It is concluded that the method is suitable as
a first approximation. A. I. Morozov and several others are men-
tioned for their participation in the study, G. Yu. Stepanov for
discussion, L. D. Kochergin and Yu. N. Kurzanov for designing part
of the equipment. There are 41 figures, 4 tables and 23 referen-
ces.
Card 2/2

S/262/62/000/008/005/022
1007/1207
AUTHORS: Blokh, E. L. and Ginevskiy, A. S.
TITLE: The laminar flow around a cascade of circles anti its use in solving hydrodynamic problems
PERIODICAL: Referativnyy zhurnal, otdel'nyy vypusk. 42. Silovyye ustanovki, no. 8, 1962, 22, abstract
42.8.121. Collection "Prom. aerodinamika", Moscow, Oborongiz, no. 20, 1961, 89-136
TEXT: A tentative solution is given for the case of flow around a cascade of near-circles; the deviation of the
actual resulting contour from an ideal circle does not exceed 0.6y. of the radius, even for the limiting case
when q = I (q is the ratio of the circle diameter to the distance between the adjacent circles); for q = 0.8 the
deviation is less than 0. 1 %. The authors also give an exact solution for the flow around a limiting cascade of
circles which permits the accuracy of the above tentative method to be estimated for the whole range of
variation of the ratio q. With q = 1, the error in determining the flow velocity is 1.63 Y.. There are 23 figures
and 15 tables.
[Abstracter's note: Complete translation.]
Card 1/1

S/632/61/000/020/005/008
D234/D308
~'UTHORS: Belotserkovskiy, S. M., Ginevskiy, A.'S. and
Po-lonskiy, Ya. Ye.
TTTL~-'; ~erodynamical forces acting on the profile grating in
non-stationary flow
SO'URCE: Noscow. TsentralInyy aero-gidrodinamicheskiy institut.
Promyshlennaya aerodinamika. no. 20, 1961. Osevyye
dozvulkovyye kompressory statsionarnogo tipa, 137-167
T----'X'2: A method o-Lc* computing the aerodynamical characteristics,
being a -eneralization of the method offered by one of the authors
in a previous publication, is described. The general case is con-
sidered in which the profiles vibrate in an arbitrary (but equal)
manner and are deformed at the same time. The only assumptions
made are those on which the linear theory is based. The solution
is constructed as a linear combination of vortex chains of arbi-
trary stagger and step; the intensity of associated vortexes and
the basic kinematic parameters of the grating varying harmonic-
Card 1/2

Aerodynamical forces acting ...
S/0'32/61/000/020/005/008
D234/D308
ally with time. Formulas for the forces and moments acting on the
,grating are derived and the method of numerical computation on an
electronic compater is described. Graphs of characteristics are
.L L U
g4 ven for a widetrange of grating parameters and Strukhal's num-
ber /-Abstracter's note: Name transliterated-7 for a grating con-
sist-ing of plates. There are 22 figures.
Card 2/2

S/r32/61/000/020/007/008
D234/D308
AUTiORS: Ginevskiy, A. S. and Solodkin, Ye. Ye.
TTTLIE: Hydraulic resistance of ring channels
SOURCE; Moscow. TsentralInyy aero-gidrodinamicheskiy institut.
Promyshlennaya a-erodinamika, no. 20, 1961. Osevyye
dozvukovyye kompressory sta 4- sionarnogo tipa, 202-215
U
TEXT: The authors give an approximate solution of the problem of
3-vabilized -t;urbulent flow in pipes having ring-shaped cross-sec-
vion, for arbitrary values of the ratio of external to internal
-d`us. ',,;'ell-',nown solutions for a circular pipe and plane pipe are
obtained as limiting cases. Values of empirical constants are de-
termined. The agreement with experimental data is found to be satis-
.L.actory. The opinion that data processing with the aid of hydraulic
dia:.ieter eliminates the effect of the shape of cross-section, is
proved to be incorrect. There are 12 figures.
Card 1/1

40771
S/124/62/ooo/ooq/ooq/o26
AOO1/A1O1
AUTHORS: Dovzhik, S. A., Ginevsk1Y,__A._S-.-
TITLE: Pressure losses in blade crown of the axial subsonic compressor
PERIODICAL: Referativnyy zhurnal, Mekhanika, no. 9, 1962, 35, abstract 9B220
(In collection: "Prom. aerodinamika, no.-2011, Moscow, Oborongiz,
1961, 5 - 56)
TFJT: The authors present the results of an experimental investigation of
losses in the blade crown of the guidance apparatus and impeller; the investiga-
tion was carried out on an experimental compressor at low subsonic velocities.
Radial and pitch distribution of losses'was investigated for several variants of
blading of the guidance apparatus and impeller. Profile losses, secondary and
end losses are analyzed. The published empirical formulae for determining 17osses
of various types are critically reviewed and compared with experimental data
available. The following formula for determining the sum of the end and secondary
losses in the guidance apparatus and impeller is recommended at conditions below
separation:
Card 1/2

S/124/62,/ooo/ooq/ooq/o26
Pressure losses in blade crown of... AOOI/AIOI
,1 2 c-
2 COS T
k + ~b = i'=h mk + mbcY r, cos3 1~-,
where E is blade elongation differing from Howell's formula by the values of co-
efficients mk and mb (it is recommended mb = 0.016 L 0.019 independent of R and
Mk = 0.016 1 0.022 for conditions self-simulating in' R; a more precise selection
Of mk depends on additional conditions). The material obtained enables the
authors to propose a method of approximate determination of the pressure charac-
teristic of the stage, which agrees satisfactorily with results of testing stages
of axial compressors of various types at conditions below separation. Numerous
graphs of experimental results are presented. There are 23 references.
N. A. Kolokol'tsov
[Abstracter's note: Complete translation]
Card 2,/2

BLOKH, E..L.; GIIEVSKIY A*S
--=I -_,_I
Free from eddies Iflow about a circular cascade and the use of
this flow in ca-Iculating fluid-dynamic cascades. Prom.aerodin.
no.20:89.-136 *61. (NURA 14:12)
(Cascades (Fluid dynamics))

S/262/62100010111013/030
1007/1252
AUTHORS Rclotserkovskiy, S. M.,Gincvskiy, A. S. and Polonski , Va. Yc
y
TITLE The effect of aerodynamic forces on a cascade under nonsteady flow
PERIODICAL Rcferittivnyy zhurnal, otdcl'nyy vyptisk. 42. Silovyyc tistanovki, no. 11, 1962, 37, abstract
42 11.175. (in collection Prom. acrodynamika, M., Oborongiz, no. 20, 1961, 137-167)
TEX7 , I he principles are outlined of a method for computing the aerodynamic characteristics of a flat-
plate cascade. The general case is described of spontaneous vibrations of The cascade about a certain mean
position- To obtain tbc nonsteady aerodynamical characteristics of the cascade, dimensionless functions
were determined for the components of the inductive velocities of adjacent vortices The boundary con.
ditions in the problem under consideration are equality to zero of the normal component of relative velocity
al each point of the profile. For an approximate solution the vortex layer, continuously distributed over the
profile, is replaced by a number of adjacent vortices. The procedure for calculating the cascade on the "Strela"
(Arrow) electronic digital computer is described. The requircd number of adjacent vortices is dictated by
t-he requirements of computational accuracy. Solution of one variant of the problem takes about 5 minutes
Dependence of the coefficients of rotational derivatives on the spacing and depth of the cascade is shown-
Card 1/2

The elliect of.
S/262/62/000/011/013/030
1007/1252
and a marked discrepancy is noted between these results and the data for a single proffie It is also noted that t
for a ipacing factor above 0.5, these coefficients are practically independent of the Stioulial ntl[Dtk-r /./"'
(Abstractor's note, Complete translation.]
Card 2/2

3/124/62/000/008/009/0,'o
1006/1242
AUTHORS: Belotscrkovskiy, S.M., nnd
Polonskiy, Ya.Ye.
TITL3: Lerodynamic forc-; rtctin- on a net of profiles
in nin ste:idy flow
PERIODICAL. A~infer,,tivnny 7,hurnal, Vekhanika, no.8, 1962, 29,
abstr,7ct 8B176. (In collecti-on: Prom. aerodin.,.mika,
no.20, M., Oborongriz, 1961, 137-367)
Md: Incompressible nonviscous !low past a net of thin
profiles (pLates) is considered, The profiles exec,ite oscilla-
-tions with equal ph-ise, find can be deformed sim~)Itaneously. Each
profile is replnced by a 5ystem of continuously distributed
Card 1/4

311.2 4,/6 21000100R,"00910 30
1006/1242
LarodynamIc for(,,(,.,i acting
vortices with a inten:-~ity. T11 Ljjf~
linear Iframework of the j-,rob1p;:t iA is ~Issumed th!~t the vortex
sheet lenving, the profijti~~ iaintaJn3 ,.n invariable i)r)::it;i'on ,-,,ith
respect" to the o:icillatinr- net. Th(! ijrobl;~rr. -is .3,)lved wiTieric-11y,
and for thiB purpose the contiwtott.-~ vortex sheet --lone-- thr~ profile
contour is replaced by.,q discreet number of j,)jIlf.~d vortices. The
determination of' the cirulation amplitude is reduced t,) thp solu-
tion of a system of linf--~r algebraic e(ILIAtion-1. Thp equation co-
efficients are functions of the net parameters and of the -trou-
hall number. The coefl.-icients of' lift and moment of the profile
are determined by the, formulae
C, z (.1 ~ ("ti #, CA r1%
IMz t IVItA 41. 1 Q i~ hi L,~L
there CYOO and m7,00 - the coefficient of lift and the plogit-rit
Card 2/ 4

3/124/62/000/008/009/030
1006/1242
Aerod,ynnmic forces -ictinig.
correspon(ling to ~itendy ilow part the net, respectively. '2hp-
other uerm:i c-)nt,-iiu coefficienc:. oi rotation derivatives lorres-
pondin_- tr) th(i rate oL. ch.,n,;e ol' angle- of attacb., R , the profile
rotation, w, tend it.,; deformttion, a . Specia.1 care.- of identical
pure rotational oscillKtioils and pure oscill,-~t ions
without deiormntion are considered. ,'o*rmulae -ire obt-i.ined. oonnec-
tinr the. -,mplituden of the lift and moment coeffici-at~~. C.' Jild
hl.+ and the p1ruse shifts ej , and 6, with the co~:.f.L'icli-tnt,; of
A
rot:,.tion derivntives. The ch-n,,,e of the --ngle of attack,/A40-
under the iniluence of a chain of inLtinl vortices in a quasi-
steady case of purely translutional motio*n of the profiles in
determined. A numerical C!,lculatiin of aerodynamic chn-racteri.-tins
of' a net of plates is performed on the electronic dij-,ital computer
.I'Strelall accordine to the formulas obtt~ined, for values of consis-
tency e - b/t (b- chord, t- pitch of the net) of 0.25, 0.591.0,
1.5# 2.0 and Strouhall numbers OY 0.5v 1.0, 1.5s ~..O ~_nd
Ci*rd 3/4

Sll~, 4/6 2/000/009/00 9/0 30
1006/1242
Aerodynamic force.-, actinf.j,,.--
StL~ggf,r w1gle p iii tUe ra..,be 0 - 600. ..~or o the result-.nt
curves coincide with curves ior ---i single oucillating plate. It
is shown that the coefficients of rotn.tion derivvtives of the
profile in the net -rt, essentially different frot-ii the copfricients
of a single profile and at low comi-,tencieE; th~-,y depend stron&ly
upon the Strouh.-ill w1mber.
All the coefficientj of iorceo -~nd
inoment at r ;, 0.5 are practically independent of the Stroah,~ll
nwnber. The considerud coefficients of rotntional deriv-,.tives '-I.re
practically illLlepwident of the angle of' attack: ,,, = 0 - 100. The
phrise !;hift of the lift coeffici,-nt &j attains values of the order
of 20 -509 --t Stsotthall numbers q = 1 - 2 and T, - 0.5, whereas
the moment coeficient phase shift LL is smill. At C, = 0, 0.
CRbAricter's f1dic . tL',"Pide-
Card 4/4

GINEVSKIY, A.S.; SOLODKIN, Ye.Ye.
Hydraulic resistance of annular,channels. Prom.aerodin. no.20:
202-215 '61. (MIRA 14:12)
(Pipe-Hydrodynamics)

BELMSERKOVSKIY, Bergey Mikhaylovich; -01MV4IY., Aron Semenovi I-
-q
MWMKIX 'rakov Yefimovich; SUVOROVA I.A. red.; FUkA-'j
N.A. IKOVA
- , tekhn.red.
(HYdrodynamic theory of cascades; aerodynamic power and moment
cbaracteristice of cascades of thin Profiles] Gidrodinmicheskaia
teoriia reshetok; silOvYe i momentuye aerodinamichtskie
kharakteristiki reshetok tonkikh profilei. 140skva., Gos.nauchno-
tekhn. izd-vo Oborongii,, 1962. 124 p. (Promyshlennaia
aerodinamika, no,22). (KM 15:8)
(Cascades (Fluid dynamics))

FEODOSIYEVt V.I., doktor tekhn. nauk, prof., red.; _R~NEVSKIY,___A.S.,_,,,
kand. tekhn. neukj, red.; KURBAKOVA, I.P.p red. 1-zd--v--a-,-
NOVIK, A.Ya., tekhn. red.
[Some problems ir mechanics]Nekotorye voprosy mekhaniki; sbornik
statei. Moskva, Oborongiz, 1962. 203 p. (MIRA 15:12)
(Mechanics)

Viktor Mikhayl*vich; CGI'A4-1, X ;.'., k,ind. tekhn.nauk,
'THEYN IN 7
retsenzent; GALITSKIY, Yu.11., inzn-, retBenzent; ~INEVSKIb-
kand. tekhn. nauk red.; M01MOVA, F.B., red.f,-----
A.S.y 9 z, va;
OIMHKINAY V.I.,, tekhn. red,
[Weight and transportation efficiency of passenger planes)
Vesovaia i transportnaia effektivnost' passazhirskikh sa-
moletov. Moskvn, Oborongiz, 1962- !$62 p. (MIRA 16:10)
(Airplnnab)

GINEVSM. A.S.
Turbulent nonisothermal jet flows of a compressed gas. Prom.aerodin.
nd.23. 11-65 3622, SMIM 16.1,)
(Jeta-Fluld dynamico) (Turbulence)

GTITEVSKIY, A.S.
Radial slot jet flowing out from an annylar source with a finite diameter.
Prom.aerodin. no.23:72-79 262. (1,1L.A 16:4)
(Jets-Fluid dynamics)

GIINEVSKIYY A.S.
Turbulent jet flows with return currents of the fluid. Prom.aerodin.
no.23:80-98 162. (IVJU 16-4)
(Jets-Fluld dyga4ica) (Turbulence)

ACCESSION NR: AT30OZO66 S/2632/62/000/023/0107/0118~
AUTHORS: Ilizarova, L.Lj Ginevskiy. A*Se
-------------
untercurrent flow
ITITLE: Experimental .investigation of .a jet in co
SOURCE: Moscow. Tsentrallnyy aero-gidrodinamicheskiy institut. Promyshlen-I
naya ae rodinamika, no. 23, 196Z. Struynyye techeniya, 107 - 118
1TOPIC TAGS: aerodynamics, hydrodynamics, gas dynamics, fluid dynamics, jet, 10
jet flow, countercurrent flow, counterflow, incompressible flow, Pitot-Prandtl
.1
,tube, wind-tunnel test, null reading, null method, null-reading method, dynamic-
1pressure head, static head
':ABSTRACT: The paper reports the results of an experimental investigation of the
,aerodynamic characteristics of an axially- s ymme trical jet in a countercurrent flow
iwithin a numerical range of the parameter m (ratio of the free-flow countervelocity
~divided by the primary-jet velocity at the nozzle exit). of from 0 to 0.4. Velocity (V)
band pressure (P) profiles are obtained in the "initial" mixing region (surrounding
~.the central core of the jet) aftd the "main" mixing region (farther downstream) of
.such a jet, also the dependence of the lengths of these regions on the parameter
,The experiments were performed in a closed wind tunnel with an open working
!Card I/ Z
Z i

!A'CC_ E_,_S__S1ON NR: AT30OZO66
Isection (f4O-mm diam). Velocities from 13 to 14 m/sec were employed. The jet
!nozzle (10 and 19 rnm diam) was carefully aligned with the direction of the local I
ifree flow. Jet velocity: 120-150 m1sec. Three types of Pitot-Prandtl tubes with 3i
component heads and T-shaped heads were developed and employed to explore the
!complex flow in the mixing sheath between the counterflowing jet-core and Wind-
tunnel flows. The various types of head employed are described and pictured. A
~disk-shaped static head is also described and depicted. The pressures and magni-
'tudes and directions of the iocal velocities were measured by a single head which
Jwas transported and positioned by a precision coordinate -locator device. All
I
!measurements were done by the null method, that is, all readings were performed
1
;by equalizing the pressures in the two branch tubes of a U-shaped manometer. The
iresults of the measurements are portrayed graphically, and it is shown how the
'1ength of the initial region of the jet is determined as a function -of the ratio M.
,also the length of the "torch," which is the sum of the lengths of the initial and the
imain mixing regions of the jet. Orig. art. has 1Z figs., I tbl., and 1 eq.
ASSOCIATION: none
SUBMITTED: 00 DATE ACQ- OlMay63 ENGL: 00
;SUB CODE: Al NO REF SOV: 003 OTHER: 000
Card 2/Z

_~,~W,VSKIYt. A.S.; MOROZOV, A.I.
Effect of the radial and circumferential irregularity of the flow
on characteristics of stages of an axial-flow compressor. Prom.-
aerodin. no.24t63-73 162. (MA 160)
(Compressors-Aerodynamics)

GINEVSKIY A.S. (Moskva); SOLODKIN, Ye.Ye. (Mool-va)
r---- n.~ -
Effect of the transversal surface curvature on the characteristics
of an isothermal axisymmetric turbulent boundary layer of a
compressed gas. Izv.AN SSSR.Otd.tekh.nauk.Makh.i mashinoBtr,
no.1:99-110 Ja-F 163. tkundary layeA) (MIRA 1622)

GINEVSKIY, A.S. (Moskva)
Approy-imate motion equations in problems of the theory of turbulent
jets. Izv.AN SSSR.Mekh. i mashinostr. no.5:134-140 S-0 163.
(MIRA 16:12)

GOHLIN., Samuil Markovich; sLEZIIIGER, Isaak Isayevichj GINE'VSKlY)
A.S., red.
(Aeromechanical measurements; methods and instruments]
Aeromekhanicheakie izmereniia; metody i pribory. Moskva)
Izd-vo "Nauka," 1964. 720 p. (MIRA 17:8)

PUTYA"
TvIllk red.

IL 38543-65 EWT(I)/ErNP(m)/bVA(d)/_F_0 WISIM(I I- Pd-I
~ACCZSSIOH HRt, AP5010080- UR/0170/65/008/004/0540/05451
IAUTHOR_t GinevksL -A.- S_,
1TITLEs Calculation of hydraulic resistance its chennels with and wi th-11
out flow separation
!SOURCE 1 -1
oxhanerno-ftxicheekly zhurnal- v. 8 no, 4, 1965,,-54o-54S
TOPIC TAGS: hydraulic.resistance. channel flow, flow separation. axi-
)Symmetrical channelt 'plane channel, diffusor
ABSTRACT: The,.aqthor.dLscusses an.approach to the calculation of the
mmetrical and plane channels in which fluid
,hydraulic reaLstance.in aicisy
!flow with and without separation-ta-kes place* Among pr6blams dILecusse'd
lare flows in diffusors, rectilinear stabilized flow in constant cro:s..j
!section channelag stabilized flow in curvilinear channels, and flow
channels with a potentiat-core, The author mentions 27 recentLy pu
lished papers in some of which he found some arroneoun ideas and can-
fused terminology. orig. artv hast 6 E*rmulass [AGI ;:7_:.
_,~14.,ASSOCIATIONI. none

L 11830-66 EWT(1)/EWP(m)/FCS(k)/EWA(1)/EWA(d) GS
ACC NR. 'AT6001364 SOURCE CODE: UR/000OA5/000/000/0189/0202
AUTHOR: Solodkin, Ye. Yd.'(14oscov); _Ginevskiy, A. S. Moscow)
ORG: None
TITIE: Turbulent nonisotbermal flow of a viscous compressible gas in
the inlet sections of axisynmetric and flat expanding ebannels witb a
null pressure gradient
SOURCE: Teplo- i massoperenos. t, 1: Konvektivnyy teploobmen v
odnorodnoy arede (Heat and mass transfer, ve 1: Convective beat exchange
in an homogeneous medium)* Minsk, Nauka. i tekhnika, 1965, 189-202
TOPIC TAGS: fluid flows bydrodynamloss friction coefficients boundary
layer theory
ABSTRACT: In the inlet section of a channel the velocity, the tempera-
tures tbe-Mach number, and other flow parameters are distributed uni-
formly over the channel cross section. As the distance from the inlet
section increases# a boundary layer arises due to the affect of viscous
forces on the walls of the channel and there is an isoentropic flow core
at parts of the section located nearer to the axis, It is assumed also
that beat transfer affects the velocity and temperature distributions

ACC NR1 AT6001364
0
only within the boundary layer. It follows that the velooitys tempera-
ture, Mach numbert and other flow parameters remain constant across the
channel in the flow core* Flow in the boundary layer is assumed to be
turbulent* The article proposes to solve the given problem taking into
account the effect of the transverse curvature of the surface on the
axisymmetrical turbulent boundary layer, There follows an extended
mathematical development based on the foregoing assumptions, Rbsults
of the calculations are exhibited in the form of curves showing the
change in the local coefficient of friction resistance along the exist
the length of the initial section of the channel under various oondi-
tions, and change in the local beat transfer coefficient along the axis.
Orig, art* has*. 30 formulas, 6 figures*
SUB CODE: 20/ SUBM DATE? 3lAug65/ ORIG REF: 003/ OTH REPI 000
jW

L 24
49-66 EWT(1)/EWP(m)/ETC"(t)/E F(n)--~2ftWG(m) A d)/gWP(j ZT
ACC NRt
SOURCE CODE:
AT600692k uR/oooo/65/ooO/000/0377/039116~t
EWT (a) -1*M/GSAM
AUTHOR: Ginevskiy, A, S.
ORG: none
TITLE: Heat and mass transfer in a nonisothermal turbulent gas jet of
variable composItion In a 00-d rectional str9am
SOURCE: Teplo- I massoperenos. t. II: Teplo- I massoperenos pri
vzaimodeystvii tal s potokami zhidkostey I gazov (Heat and mass transfer
v. 2: Heat and mass,:.transfor In the Interaction of bodies witb liquid
and gas flows). Minsk, Nauka I tekbnIka, 1965, 377-391
TOPIC TAGS: best transfer, mass transfer, turbulent jet, gas dynenicz~
ABSTRACT: Theomarlhematical development starts from the differential
equations of continuity,. momentum, energy, and mass tranz-fer for
averaged steady state plane or axisymmetric isobaric motion of a two
component gas mixturelin a turbulent boundary layer:
qlyf) -0;
(P UY +
(3y
du 1 (2)
Card 1/3 Y,

ACC N'h AT6006924 0
& dH I' a
U - +
th (3)
P
P

az C'(Yq')_.
M)
ac
3AeC16
g OU a's 1h+p,
P, dy 2
e Ob

P Di Or. (5)
V

az
P

V +
(hi.- hs) Vi
Y
P, N;
9C

"
H=h+ P, P',
D
~2 p
j
Xio 7 are coordinataaof a rectangular (j 0) or cylindrical (j 1)
coodinate system; u. v are the components of the velocity along the
x and y axes; f is the density of the gas mixture; b is the beat content;
H is the total beat content; z is the mass concentration of the sub-
stance of the jet or one of its components; D Is the coefficien
t t of
cam 2/3

W.~
,rM,",

ACC NRI AT6006924 0
reciprocal diffusion;9 is the coefficient of turbulent transfer-A
Is the coefficient of turbulent beat conductivity; Pt is the turbu&nt
.Prandtl number; P is the diffusion Prandtl number, c' ia the specific
best capacity of 9be gas mixture at constant pressu'reV, T is the absolute
temperature, The remainder of the article is devoted to a. mathematical
solution of the above system of equations. The calculation method is
said to be applicable to the solution of a wide range of problems in the
theory of turbulent gas jet.s.' Orig. art. has: 53 formulas and 5
figures.
SUB CODE: 20/ SUBM DATE: OgNov65/ ORIG REF: 004

Eva ( 10-1) (m
ACC NRs
SOUPCE CODE: U
AUTHOR: Ginevakiy,_A-_~. (Moscow) lo~
ORG: none
TITLE: Calculation of the*transition section of a turbulent jet 3
SOURCE: A11 SSSR. Izvestiya. Mekhanika zbidkosti I gaza, no- 3, 1966, 59-67
TOPIC TAGS: turbulent jet, axisymmetric flow, transition flow, flow profile
ABSTRACT! An approximate calculation method is developed for the transition sections
of plane and axisymmetric turbulent jets in a co-moving stream. It is shown why
earlier methods, based on differentiation between the initial and final sections are
not applicable in the transition (mixing) region. The velocity profiles obtained by
this method in the transition region turn out to be the same for plane and axisyrtv-
metric jets, and can be used to calculate the variation of the jet parameters along
the stream axis by using the set of integral equations connecting the angular mome
and the energy. Limiting parameters are defined under which the results coincide wi+U
the velocity profile of the main section of the turbulent jet. It is concluded tbw;,17
in first approxization. the external boundary of the transition layer is straight and.;.
is a continuation of the outer boundary of the outer section. The method Is then
demonstrated to be suitable for a determination of continuous velocity6-profile defor-
mation in the transition region. Orig. art. has: 8 figures and 33 formulas.
SUB CODE: 20/ mmm DATE: olmr65/ ORIG REF: 003/ OTH REF- 002
h~'
04

L V,71,~-4X, 1Jp1c) F'-W~
ACC NR--
AP603011.3
SOU11CE CODE: UP/01421/06/000/004/0081/0688
AUTHOR: Qinevskiy. A. S. (Moscow); Ilizarova, L. I. (Moscow); Shubin, Yu. 14.
(Mos cow)
ORG: none
i TITLE: Investigation of the microstructure of a turbulent jet in it wake TLo-w
SOURCE: AN S.SSR. Izvestiya. Mekhanika zhidkosti I gaza, no. 4, 1966, 81-88
TOPIC TAGS: fluid mechanics, wake flow, turbulent jet, jet flow, wind tunnel,
boundary layer equation
ABSTRACT: The microstructure of the main part of an axisymmetric turbulent jet in a
wake flow is investigated experimentally over a wide range of tile wake parameter
m = u6/uo (0.04, 0.21, 0.4, 0.52), where ti6 - is the velocity of wake flow and uo is
the mean velocity at tile nozzle exit. Measurements were made wLth "Disa Elektronik"
apparatus (a constant-temperature anemometer) '~~incltiding two amplifiers and a
correlator. The velocity profiles of three compon;nits of fluctuating velocity and
Reynolds qres~Lwere measured In tile main part of tile jet. The values of the mean
velocity and LWO components of fluctuating velocity were measured at a large number
of points on tile jet axis. The measured profile s of Reynolds stress are compared
with corresponding profiles calculated from an experimentally determined mean
velocity profile by means of turbulent boundary layer equations. The correlation
,Card 1/2

ACC"'NRt AP6030113
I coefficient of lonpiturlinal coinponentr, of fluctimtIng, w-lociry !r. one section of rhc.
JeCuras measured for two valuch of in an(] Lhe varfaLlon of Lhe fritepyal sicalu of
turbulence across the jet was determined. The results obtalned here tLlu,,;LraLu, tile
effect of the parameter m on the charactcrisLIc.; of a titrimlent Jet Im wake flow.
Orig. art. has: 7 figures and 19 formulas. AB
SUB CODE: 20/ SUBM DATE: 271-'eb65/ ORIG REF: 005/ 01*11 REF.- 006/ ATD PRFSS:
5074
_Card -2/2-JS

1, 071166-67 EWP(m
ACC NRs A%W5�4_
1) FDN/W' W1JWA-,2
SOURCE CODE:
AUTHOR: Ginevskiy, A. S. (Candidate of technical ociencea)
ORG: none
17
0
TITLE: The method of integral relations in the theory of turbulent jet flows
SOURCE: MoBcow. Tsentrall ~ aer
_~o-~idrodinamichoskiy inatitut. Promyshlennaya
aerodiria-miki~, no. 27, 1q6P1Y�Struynyy.e techeniya (Jet stre-a__m-s),_ 5-30
TOPIC TAGS: turbulent flow, turbulent jet, turbulent mixing, approximation method,
isothermal flow, boundary layer
ABSTRACT: An isothermal, turbulent, plane, axisymmetric jet is investigated
using Karman--type integral methods. Both the initial and main flow of the jet
are analyzed as the jet issues into a wake whose speed is either slower or faster
than the jet speed. Also investigated are expanding and converging flows of a
radial-slot type jet. The Golubev integral relation for the plane or axiWJmMetric jet
is given by
~(?1j(1j11+1_11k+1)y.1dy=k(k+1) T11 �-yJdy.
Oy
0
(k=O, 1, 2,..., oo)
The analysis starts with a plane tdAulent_Jd*t-where the jet speed u 6 is either
Card __ 1/4