The combined effects of inlet purge flow and the slashface leakage flow on the film cooling effectiveness of a turbine blade platform were studied using the pressure-sensitive paint (PSP) technique. Detailed film cooling effectiveness distributions on the endwall were obtained and analyzed. Discrete cylindrical film cooling holes were arranged to achieve an improved coverage on the endwall. Backward injection was attempted by placing backward injection holes near the pressure side leading edge portion. Experiments were done in a five-blade linear cascade with an average turbulence intensity of 10.5%. The inlet and exit Mach numbers were 0.26 and 0.43, respectively. The inlet and exit mainstream Reynolds numbers based on the axial chord length of the blade were 475,000 and 720,000, respectively. The coolant-to-mainstream mass flow ratios (MFR) were varied from 0.5% and 0.75% to 1% for the purge flow. For the endwall film cooling holes and slashface leakage flow, blowing ratios (M) of 0.5, 1.0, and 1.5 were examined. Coolant-to-mainstream density ratios (DR) that range from 1.0 (close to low temperature experiments) to 1.5 and 2.0 (close to engine conditions) were also examined. The results provide the gas turbine engine designers a better insight into improved film cooling hole configurations as well as various parametric effects on endwall film cooling when the inlet (swirl) purge flow and slashface leakage flow were incorporated.

References

References
1.
Han
,
J. C.
,
Dutta
,
S.
, and
Ekkad
,
S.
,
2012
,
Gas Turbine Heat Transfer and Cooling Technology
,
CRC Press, Taylor & Francis Group
,
Boca Raton, FL
.
2.
Goldstein
,
R. J.
,
1971
, “
Film Cooling
,”
Advances in Heat Transfer
,
F. I.
Thomas
, and
P. H.
James
, eds.,
Elsevier
, Amsterdam, The Netherlands, pp.
321
379
.
3.
Bogard
,
D. G.
, and
Thole
,
K. A.
,
2006
, “
Gas Turbine Film Cooling
,”
J. Propul. Power
,
22
(
2
), pp.
249
270
.
4.
Han
,
J. C.
,
2013
, “
Fundamental Gas Turbine Heat Transfer
,”
ASME J. Therm. Sci. Eng. Appl.
,
5
(
2
), p.
021007
.
5.
Langston
,
L. S.
,
1980
, “
Crossflows in a Turbine Cascade Passage
,”
ASME J. Eng. Power
,
102
(
4
), pp.
866
874
.
6.
Langston
,
L. S.
,
2001
, “
Secondary Flows in Axial Turbines—A Review
,”
Ann. N. Y. Acad. Sci.
,
934
, pp.
11
26
.
7.
Wang
,
H. P.
,
Olson
,
S. J.
,
Goldstein
,
R. J.
, and
Eckert
,
E. R. G.
,
1997
, “
Flow Visualization in a Linear Turbine Cascade of High Performance Turbine Blades
,”
ASME J. Turbomach.
,
119
(
1
), pp.
1
8
.
8.
Chyu
,
M. K.
,
2001
, “
Heat Transfer Near Turbine Nozzle Endwall
,”
Ann. N. Y. Acad. Sci.
,
934
, pp.
27
36
.
9.
Simon
,
T. W.
, and
Piggush
,
J. D.
,
2006
, “
Turbine Endwall Aerodynamics and Heat Transfer
,”
J. Propul. Power.
,
22
(
2
), pp.
301
312
.
10.
Burd
,
S. W.
,
Satterness
,
C.
, and
Simon
,
T.
,
2000
, “
Effects of Slot Bleed Injection Over a Contoured End Wall on Nozzle Guide Vane Cooling Performance—Part II: Thermal Measurements
,”
ASME
Paper No. 2000-GT-200.
11.
Zhang
,
L. J.
, and
Jaiswal
,
R. S.
,
2001
, “
Turbine Nozzle Endwall Film Cooling Study Using Pressure-Sensitive Paint
,”
ASME J. Turbomach.
,
123
(
4
), pp.
730
738
.
12.
Oke
,
R.
,
Simon
,
T.
,
Shih
,
T.
,
Zhu
,
B.
,
Lin
,
Y. L.
, and
Chyu
,
M.
,
2001
, “
Measurements Over a Film-Cooled, Contoured Endwall With Various Coolant Injection Rates
,”
ASME
Paper No. 2001-GT-0140.
13.
Nicklas
,
M.
,
2001
, “
Film-Cooled Turbine Endwall in a Transonic Flow Field—Part II: Heat Transfer and Film-Cooling Effectiveness
,”
ASME J. Turbomach.
,
123
(
4
), pp.
720
729
.
14.
Knost
,
D. G.
, and
Thole
,
K. A.
,
2005
, “
Adiabatic Effectiveness Measurements of Endwall Film-Cooling for a First-Stage Vane
,”
ASME J. Turbomach.
,
127
(
2
), pp.
297
305
.
15.
Thrift
,
A. A.
,
Thole
,
K. A.
, and
Hada
,
S.
,
2012
, “
Effects of Orientation and Position of the Combustor-Turbine Interface on the Cooling of a Vane Endwall
,”
ASME J. Turbomach.
,
134
(
6
), p.
061019
.
16.
Wright
,
L. M.
,
Blake
,
S. A.
, and
Han
,
J. C.
,
2008
, “
Film Cooling Effectiveness Distributions on a Turbine Blade Cascade Platform With Stator-Rotor Purge and Discrete Film Hole Flows
,”
ASME J. Turbomach.
,
130
(
3
), p.
031015
.
17.
Gao
,
Z. H.
,
Narzary
,
D.
,
Mhetras
,
S.
, and
Han
,
J. C.
,
2012
, “
Upstream Vortex Effects on Turbine Blade Platform Film Cooling With Typical Purge Flow
,”
J. Thermophys. Heat Transfer
,
26
(
1
), pp.
75
84
.
18.
Wright
,
L. M.
,
Blake
,
S. A.
,
Rhee
,
D. H.
, and
Han
,
J. C.
,
2009
, “
Effect of Upstream Wake With Vortex on Turbine Blade Platform Film Cooling With Simulated Stator-Rotor Purge Flow
,”
ASME J. Turbomach.
,
131
(
2
), p.
021017
.
19.
Gao
,
Z. H.
,
Narzary
,
D.
, and
Han
,
J. C.
,
2009
, “
Turbine Blade Platform Film Cooling With Typical Stator-Rotor Purge Flow and Discrete-Hole Film Cooling
,”
ASME J. Turbomach.
,
131
(
4
), p.
041004
.
20.
Liu
,
K.
,
Yang
,
S. F.
, and
Han
,
J. C.
,
2014
, “
Influence of Coolant Density on Turbine Platform Film-Cooling With Stator-Rotor Purge Flow and Compound-Angle Holes
,”
ASME J. Therm. Sci. Eng. Appl.
,
6
(
4
), p.
041007
.
21.
Papa
,
M.
,
Srinivasan
,
V.
, and
Goldstein
,
R. J.
,
2011
, “
Film Cooling Effect of Rotor-Stator Purge Flow on Endwall Heat/Mass Transfer
,”
ASME J. Turbomach.
,
134
(
4
), p.
041014
.
22.
Suryanarayanan
,
A.
,
Mhetras
,
S. P.
,
Schobeiri
,
M. T.
, and
Han
,
J. C.
,
2008
, “
Film-Cooling Effectiveness on a Rotating Blade Platform
,”
ASME J. Turbomach.
,
131
(
1
), p.
011014
.
23.
Suryanarayanan
,
A.
,
Ozturk
,
B.
,
Schobeiri
,
M. T.
, and
Han
,
J. C.
,
2010
, “
Film-Cooling Effectiveness on a Rotating Turbine Platform Using Pressure Sensitive Paint Technique
,”
ASME J. Turbomach.
,
132
(
4
), p.
041001
.
24.
Rezasoltani
,
M.
,
Schobeiri
,
M. T.
, and
Han
,
J. C.
,
2014
, “
Experimental Investigation of the Effect of Purge Flow on Film Cooling Effectiveness on a Rotating Turbine With Nonaxisymmetric End Wall Contouring
,”
ASME J. Turbomach.
,
136
(
9
), p.
091009
.
25.
Barigozzi
,
G.
,
Franchini
,
G.
,
Perdichizzi
,
A.
,
Maritano
,
M.
, and
Abram
,
R.
,
2013
, “
Influence of Purge Flow Injection Angle on the Aerothermal Performance of a Rotor Blade Cascade
,”
ASME J. Turbomach.
,
136
(
4
), p.
041012
.
26.
Matthew
,
S.
,
Goldstein
,
R. J.
,
Simon
,
T. W.
,
Shu
,
F.
, and
Chiyuki
,
N.
,
2014
, “
Effect of Swirled Leakage Flow on Endwall Film-Cooling
,” International Heat Transfer Conference (
IHTC-15
), Kyoto, Japan, Aug. 10–15, Paper No. IHTC 15-9600.
27.
Li
,
S.-J.
,
Lee
,
J.
,
Han
,
J.-C.
,
Zhang
,
L.
, and
Moon
,
H.-K.
,
2016
, “
Turbine Platform Cooling and Blade Suction Surface Phantom Cooling From Simulated Swirl Purge Flow
,”
ASME J. Turbomach.
,
138
(
8
), p.
081004
.
28.
Yu
,
Y.
, and
Chyu
,
M. K.
,
1998
, “
Influence of Gap Leakage Downstream of the Injection Holes on Film Cooling Performance
,”
ASME J. Turbomach.
,
120
(
3
), pp.
541
548
.
29.
Piggush
,
J. D.
, and
Simon
,
T. W.
,
2007
, “
Heat Transfer Measurements in a First-Stage Nozzle Cascade Having Endwall Contouring: Misalignment and Leakage Studies
,”
ASME J. Turbomach.
,
129
(
4
), pp.
782
790
.
30.
Piggush
,
J. D.
, and
Simon
,
T. W.
,
2012
, “
Flow Measurements in a First Stage Nozzle Cascade Having Endwall Contouring, Leakage, and Assembly Features
,”
ASME J. Turbomach.
,
135
(
1
), p.
011002
.
31.
Shiau
,
C.-C.
,
Chen
,
A. F.
,
Han
,
J.-C.
,
Azad
,
S.
, and
Lee
,
C.-P.
,
2016
, “
Full-Scale Turbine Vane End-Wall Film-Cooling Effectiveness Distribution Using PSP Technique
,”
ASME J. Turbomach.
,
138
(
5
), p.
051002
.
32.
Roy
,
A.
,
Jain
,
S.
,
Ekkad
,
S. V.
,
Ng
,
W. F.
,
Lohaus
,
A. S.
, and
Crawford
,
M. E.
,
2014
, “
Heat Transfer Performance of a Transonic Turbine Blade Passage in Presence of Leakage Flow Through Upstream Slot and Mateface Gap With Endwall Contouring
,”
ASME
Paper No. GT2014-26476.
33.
Lynch
,
S. P.
, and
Thole
,
K. A.
,
2015
, “
Heat Transfer and Film Cooling on a Contoured Blade Endwall With Platform Gap Leakage
,”
ASME
Paper No. GT2015-43301.
34.
Narzary
,
D. P.
,
Liu
,
K. C.
,
Rallabandi
,
A. P.
, and
Han
,
J. C.
,
2012
, “
Influence of Coolant Density on Turbine Blade Film-Cooling Using Pressure Sensitive Paint Technique
,”
ASME J. Turbomach.
,
134
(
3
), p. 031006.
35.
Chen
,
A. F.
,
Li
,
S.-J.
, and
Han
,
J.-C.
,
2014
, “
Film Cooling With Forward and Backward Injection for Cylindrical and Fan-Shaped Holes Using PSP Measurement Technique
,”
ASME
Paper No. GT2014-26232.
36.
Han
,
J. C.
, and
Rallabandi
,
A. P.
,
2010
, “
Turbine Blade Film Cooling Using PSP Technique
,”
Front. Heat Mass Transfer
,
1
, p.
013001
.
37.
Kline
,
S. J.
, and
McClintock
,
F. A.
,
1953
, “
Describing Uncertainties in a Single Sample Experiment
,”
Mech. Eng. (Am. Soc. Mech. Eng.)
,
75
, pp.
3
8
.
You do not currently have access to this content.