SCIENTIFIC ABSTRACT GARKUSHA, A.V. - GARKUSHA, N.G.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R000514320019-6
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: November 2, 2016
• Document Release Date: July 19, 2001
• Sequence Number: 19
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT

32017
S/587/60/029/002/004/008
On the problem of taking ... D203/D-/,-)2
b) M lis 2 CosklB 2
M1isB=sin 2"-'l B2 (P2
---=.L- (10)
rBKT
(@2
C) C1z Clu r = [sin2c(JB+ CO82CClB 2
7,-ZB = 'r-',UBr.B rB2
The variation of the outlet angle for these cases is compared gra-
phically forC( 1B@ 200;T = 0..96 and K = 1.33. The discrepancy in the
Card 3/5

On the problem of taking
32017
S/58 60/029/002/004/008
D203YD302
value of Mi is at rB = 2 and is highest for case (a). It amounts to
9% and results in 5 to 6% 1088 of reaction. A comparison of flow
with losses to the ideal flow is made in
KT
sinoC, sinGCj is
Thus, knowing angleCy, for the ideal flow, angleo(,j for the flow Vr
with losses can be found. To find the variation of velocity in the
clearance it is then pufficient to solve Eq. (4). A similar problem
arises when a blade is designed with angles different from the the-
oretical ones. The solution of Eq. (4) is then reduced to finding
x
F(X) f(x)dx
a
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32017
S/587/60/029/002/004/008
On the problem of taking D203/D302
with f(x) given in tabular or graphical form. This method enables
radial variations of T and K T to be taken into account without ex-
tra complication.The effect of nozzle losses on the flow parameters
in the clearance is also given graphically forq 1B 7- 200,T= 0.96
and K = 1.33. There are 5 figures and 6 references: 5 Soviet-bloc
and 1 non-Soviet-bloc.
V_K
Card 5/5

S/096/61/000/004/003/007
E194/E255
AUTHORS: Fedorov, M. F., Candidate of Technical Sciences and
Garkusha, A. V., Engineer
TITLE: The Influence of Guide Blade Width on the Character-
istics of Turbine Stages
PERIODICAL: Teploenergetika, 1961, No. 4, pp. 3?-41
TEXT: Diaphragms with narrow guide vanes are widely used in
turbines although little work has been published to confirm their
advantages. The possibility of improving the turbine efficiency by
using this kind of diaphragm is generally based on considerations
applicable to individual blades, usually without allowing for
factors that alter the structure of the dynamics of the flow in the
gap between the rims when the width of the guide vanes is reduced.
In the Turbine Laboratory of the Khar'kov Polytechnical Institute
an investigation was made of various stages having a constant ratio
of mean diameter D = 475 mm to height -9 of guide vanes D/4 - 19.
The guide vanes were of three widths, B, and the len6th-to-breadth
ratios were 0-305; 0.61 and 1.22. Profile type C-1 (S-1) was used.
All the guide vanes were made up with the same nominal flow area
CF,.rd l/ 5

S/096/61/000/004/003/00't'
E194/E255
The Influence of Guide Blade Width on the Characteristics of Tur-
bine Stages
reckoned from the dimensions of the channels between blades at the
narrowest sections. Each set of guide vanes was tested with three
runners of different flow area, which was achieved by altering the
angle of installation of the blades and keeping their number the
same. The runner blade profiles were Type T-1-25-21, the relative
pitch was 0.664 and the blade height 28.5 mm. The ratio of the
flow area of the runner blades to that of the nozzles for runners
Nos. 1, 2 and 3 was 1.48, 1.76 and 2.04, the values being chosen tc
obtai'u positive, mixed and negative stage reaction over the height
of the blades. The tests were made on an air turbine illustrated
schemattcally in Fig. 1. The discs contained no pressure-equaliz-
ing apertures. Further details are given about the experimental
conditions. Fig. 2 is a typical curve of test results of stage
efficiency (allowing the discharge velocity energy to be dissipat-
ed). The efficiency is plotted against the velocity ratio for
runner No. 1 with three different sets of guide vanes whose length-
to-breadth ratios were 1 - 1.22; 2 = 0.61; and 3 = 0.305. It is
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S/096/61/000/004/003/007
E194/E255
The Influence of Guide Blade Width on the Characteristics of Tur-
bine Stages
seen that as the blade width is reduced the efficiency is increasec@
but the amount of increase depends on the blade breadth and on the
velocity ratio. The increase in efficiency that results from
making the blades narrower also depends very much on the values of
the clearance. Wheel No. 2 which has a greater ratio of area of
runner blade to that of nozzle blade. In this wheel there is zero
reaction at the mean section only when the guide vanes are
relatively broad. As the breadth was reduced, the degree of
reaction became negative over the whole height of the blade. With
a runner of this kind it should be borne in mind that with broad
and medium blades the stage works with leaks tinder the shrouding,
and if the blade is narrow air may be drawn into the gap between
the rims from the space beyond the wheel at the blade periphery.
In the case of runner No. 3 the relative areas of runner blades
and nozzles were such that the runner always worked with negative
reaction over the blade height. In this case the efficiency with
wide blades is higher than for runner No. 2 and there are indica-
tions that the use of still more negative reaction would invert
Card 3/5
7777777@@ Zt-

S/096/61/000/004/003/007
E194/E255
The Influence of Guide Blade Width on the Characteristics of Tur-
bine Stages
the previous influence of blade width on stage efficiency. The
results of the efficiency investigations show that for a stage
with small positive reaction at the blade roots the nozzle blade
length-to-breadth ratio should be increased to 0.6-Oz8. The
efficiency is thereby raised by 1-5-2% and reaches its highest
value. If the reaction is mixed over the height of the blade
narrower blades may be used. The test results also show that
whilst on transition from wide to narrow blades the reaction at
the periphery diminishes considerably, that at the blade roots
alters comparatively little. Thus, the main cause of the change
in reaction at the periphery is the influence of the breadth on
the radial pressure gradient. There are 9 figures and 4 Soviet
references.
ASSOCIATION: Kharlkovskiy politekhnicheskiy institut
(Kharlkov Polytechnical Institute)
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S/096/61/000/OC4/003/007
E;194/E255
The Influence of Guide Blade Width on the Characteristics of Tur-
bine Stages
Pi I
PjjC. g. CxCM,,l JIpOTOIIIIOA -12CTH"
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P83.11141MIX YAMIIICIIHHX IMIlPaIMMOLURX -101?atOX AJIJI
KO.'IeCA A 1.
f1b = 1,21; 2 - 0.61: 3 - 0.3M.
Card 5/5

S/262/62,'OZO/017/001/003
1007/1207
AUTHORS: Fedorov, !tnd Garkusha, A.V.
TITLE; lnvestiC.@tion of the flow pattern in the gap
between -the blade rows, and energy losses in the
turbine stnge no77.les eLt varying chord S17e.9 of
stator blades
PERIODICAL: Referativny 7hurnal, otdellnyy vypusk. 42. [e-mail]
ustanovki, no. 17, 1962, 23, abstract 4217161
("Tr. Kh:%rlkovsk. politekhn, in-ta" 1961, 180-191)
TEXT. InvestijiLions were carried out on a single stage
air-turbine with a rotor diameter Dmean- 475 mm, no7zle blade
lenith 1 - 25 imil and with the following stage parameters: 1/b - 1.2;
1.22 i Os*61 and 0.305; t/b 0.758; --@l= 11031!; Fbl/Fnoz = 1.48 and
1.78 with Mos - 0.36 rind Re bcl/q = 5@8; 2#9 and 1.45. 10. Here
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S/262/62/000/017/001/003
1007/1207
investiSation of the flow pp.ttern...
b and t chord and pitch of' stator blades; @@el = flow divergence-
angrle; F area of blade and no7zle openin- cross-section. The
U
ma,giitude 3 - 3/b of the closed section of the gap between
the blade rows, was il,;o changed during the invest iTit ions. The
profile of no-7,71o (stn.tor) blades was C-1, of rotor blades T-1-25-21.
The ratio u/co (peripher:il to isentropic velocity) corresponded to
the maximum stame-efficiency. As shown by the investigation results,
the static pressure p, at the external radius of each chord, some-
what increases with the increase of @3 - It .1, . The curves')3 ). =
= C//- calculated according to the actual values of Clu
and _@O only, slightly depend on b !t-- > and P3. The pressure
brr:idient, ineasured alon,, the radius increases with the chord si7,e,
A
and with 1/b = 0.305 npproaches The discrepancy
r
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S/262/62/000/017/001/003
1007/1207
Investigation of the flow pattern. . .
between the predicted nzic. me:-@sured values of the presSUre gradient
may be explained by the -ippearance of radial-acceleration elue to
flow twisting. The ma..,--nitude of PL at the blade root almost does
not depend on the value of b. The degree of peripheric reaction
in the st- jes with narrow stator blades is smaller than in the
case of broad blades. The flow divergence angle oe-, in the flow
core and :,-t all values of l/b, F3 Find Fbl/Fnoz is close to 119
which is in 6ood agreement with data on flow about a flat cascade.
At the disc periphery and with a stage with 1/b 1.22, the angle
0(@ decreases by 2-30 whereas with a 1/b ratio 0.305, it incrjeases
by 1-1.50. At a 1/b ratio = 0.61, the angle _)e.,appears to be dis-
tributed over the rodius as in the case of straight-blAde cascades.
I@ all cases, the vplue C
/,,sharply drops at the surfaces that
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S/262/62/000/017/001/003
1007/1207
1nvestiSlition of the flow pettern...
limit the glow. '2he axial component C1. decren-tses almost over
the whole blade length with the increase in and particularly
sharp at all values of 1/b and 93 for cylin(frical walls. Despite
the favorable C-scade -reometry for the stall from the stator-blade
roots, the flow about them turned out to be laminar. The graphs
for the square of velocity coefficient @ 2 = f (r) are asymmetrical,
and almost do not depend on the degree of reaction and sta-e seal-,
ing. The no77le efficiency f2
6:- - w
Cl .@ - - calculated ith due
account of the dischar:;e velocity component, decreases with the
increase in 1@ , -_@@the more, the greater is the chord si7e.
with 63 = 0.05, and 1/b - 1.22 the nov,.zle efficiency is smaller
by 4.% than the cascade efficiency, and with a 1/b ratio u 0.305
it is smaller by 3oj4. The function has a maximum at
/A/ .
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3/262/62/000/017/001/003
1007/1207
Investi-ition of the I'low p!-kt tern.-. .
b/l = 1.5 for Q05 to 0.10. With the -incrense in @' the
Magmitude 01, the Maximum 2 drops and shifts toward smailer
values of b/1. The decrense of -the chord size does not lead to
a continuous incre-se of the no-7le efficiency. The chord size
oi' stator blades affects the stage efficiency by reducing the
norzle efficiency and the degree of peripheric reaction. There V
are 9 figures and 5 references. V,
@Abstracterls note: Complete translr@tion
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811'4,416210001OW10141030
1006/1242
@UVIOR:i s Fedorov, M.F. and Garkuohat A.V.
TITLEt The flow structure in inter-ring clearance and the energy
losses'in staGe nozzles of turbines,at various settings of
the guide blades
PERIODICAL: Referativnyy zhurnalj,'.,ekhanikc.k no.89 1962, 45, abstract
8B301. (Tr. 4arlkov3k. politekhn. in-ta, v.36, 1961, 180-191)
TEXT: An experimental investigation is undertaken of G oin;-lo-atagc
gas turbine with short bladest Dav/1 x 19 in order to determine the influence
of lengthening of guide vr-ne3j for which i/k = 1.22, 0.6-It and 0.305, on the
efficiency of the guiding system and of the stage as a whole. The investi-
gation showed thatt in contrast to straight cascades, where losses decrease
monotonLcally with increasing vane length, for ring-cascades a clearly defined
maximum is obserwed in the y- (6/1) curves at approximately b/f . 1. More-
Gard 1/3

S/124/62/000/008/014/030
1006/1242
The flow structure in inter-ring....
over, the absolute value of losso3 in ring-cascudo3 is remarkc-bly hieher
than in straight cascades. The authors see the main reason for these differ-
ences in the fact that in experiment *a with straight cascades the boundcry
layer at the intake is cut out with the aid of plates. This procedure, netura-
Ily did not take plece in 4ho stage teat. Measurement of flow parameters
inter-ring clearance has shown that the static pressure on the periphery da-
creaseG for narrow guide vanes, and the measured preasurc gradient In radial
direction doea not correapond to the value determined by numerical integration
of the differential equation of radial equilibetum which takes into account
the actual variation of peripheral velocity component and the density along
the radius but neglect; radial velocities. The construction of meridional
streamlines has shown that with narrow blades a considerable deflection of
streamlines towards the root section takes place. This permits equalization
of the pressure gradient along the radius and a decrea.,,e of the degree of
Card 2/3

S/114/63/000/004/002/005
A004/Al27
AUTHORS: Shnee, Ya.l.p Doctor of Technical Sciences, Federov, M.P.,
Candidate of Technical Sciences, 0, Engineer
TITLEz Selecting the closeeL axial olearance in the bandaged turbine
stage
PERIODICAL: Bner@gomashinostroyeniye, no- 4, 1963, 18 - 22
TIMCT: The authors present a generalized analysis on the various
factors to be considered in the oloced axial clearance in bandaged turbine
stages, based on tests with an experimental air turbine at the KhPI laborat-.
cry and on the generalized test results of some other organizations. Nine
tages with bandaged runners with different guide blade extensions were
rj
tested. A detailed table of the main design and test data of theXFM(KhPI),',
BV,TTJ(BITU) and IMH (TsKTI) turbine stages is given. The authora present
recomraendations on the.optimum clearance and state that, based on investig-,
ations carried out, it can be said that for stages with a small relative
extension of the guide blades it is expedient, from the efficiency of the
stages viewpoint, to choose minimum closed clearances. Z-xre axe 5 figs r 1 t5ble.
Card 1A

Af

ACC N;7: ;,-.,%"029662
-,, - -i.
.X S' nce, Y. 1.
.',Eiigincer; Dissertar,t);
030: Kharkov Polytechaical
institut)
SOURCE CODE.: Uit/0096/6t')/UL)Cj/OCII)/0071/0;~7,i
-ssor); Ponommarev, V. N.
(Doctor of technical sciences; Profe
Garkuaha, A. V. (Candidate of technical sciences)
Institute in. V. 1. Lenin (Kharkovskiy politekhnichaskiy
TITLE: On raising the efficiency of the after stages of turbines
SOURCE: Teploenergetika, no. 9, 1966, 71-74
TOPIC TAGS: turbine, gas turbine, turbine nozzle, turbine nozzle assembly, nozzle
assembly, conic nozzlej-.aant=b_-1;-, turbine stage
ABSTRACT: An investigation of the conical stages of a turbine, including stages with
a nozzle assembly of new design, shaped according to the conical surfaces is
i described. On the basis of the experimental results, the following conclusions were
made: a) the flow stream in the nozzle assembly of-the conical stage sharply differs
from that in the cylindrical stage. b) As a result of sharp difference of the
really streamlined sections in the peripheral zone of the nozzle assembly geometry
from the geometry of reference sections designed in conformance to the coaxial
cylinder surface, the flow in such stages is converging-diffusing, and in separate
c)
the
zones it is diffusing, which causes increased losses in the nozzle assembly.
reprofiling of the nozzle assembly in accordance with the conical surfaces approxi-.
Card 1/2 um 621.165-003.1-001-5

ACC NR: @26029862
mately replacing the flow surface, sharply decreases the energy losses in nozzle
assembly, some what decreases 'the losses in the rotor, ind significantly increases
the efficiency of the iihole stage. d) The proposed method of increasing the
efficiency by reprofiling the nozzle assembly in accordance with flow surface is
useful for stages with sudden opening of the flow area and any form of peripherally
limiting surface. Orig. art. has: 6 figures and 2 formulas.
SUB CODE:: 21/ SUBM DATE: none/ ORIG REF: 003
Card 2/2

GARKUSHL F.Y., otvetstvenayy za vypusk; MLLIZOVA, N.V., tekhnicheskiy
lt&i tdr
(Standard designs for construction of automobile roads] Tipovye
proakty sooruzhenii na aytomobilinykh dorogakh. Moskva, Nauchno-
tekha. izd-vo aytotransp. lit-ry. NO-7- [Reinforced concrete pipe
culverts with diametre of 0-5; 0175; 1.0; 1.25 and 1.5 a. load:
1-13 and NG-60; N-18 and NI-801 Kruglye zhelazobatonnve truby
otverstiam 0.5; 0.75; 1.0; 1.25 1 1.5 m. Nagruzki N-13 i NG-60;
N-18 i NK-80- 1954. 55 P. [Microfilm] (MLU 9:7)
1. Moscow. Gosudarstvannyy institut po proyaktirovantyu I isynkantyu
av-tomobillnykh dorog
(Culverts)

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