Film cooling technique is widely used to protect the components from being destroyed by hot mainstream in a modern gas turbine. Combining round-holes is a promising way of improving film cooling effectiveness. A DoE (design of experiment) simulation of 396 cases focusing on the arrangement of the combined-hole with double holes for improving film cooling performance is carried out in this work, and the influence of an aerodynamic parameter, blowing ratio is considered as well. The dimensionless lateral distance (PoD) and compound angle (CA) of the double holes have relative influence on the film cooling performance of the combined-hole unit. At the low blowing ratio, increasing symmetrical compound angle (SCA) has positive influence on the area-average effectiveness (EFF) of the combined-hole. But at the intermediate and large blowing ratio, the influence of SCA on the area-average EFF depends on the range of PoD. At the small PoD, the area-average EFF ascends basically along SCA axis. However, the area-average EFF first ascends and subsequently descends along SCA axis at the large PoD. Asymmetrical compound angle (ACA) is also considered to fit the antikidney vortexes produced in the combined-hole film cooling compared to their ideal schematic. However, the film cooling effect of the cases with ACA is not as good as expected. The area-average EFF of ACA cases locates in the level between that of the adjacent SCA cases. The optimal arrangement of combined-hole unit for improving film cooling effectiveness is relative to the local flow field. The optimal arrangement of PoD and CA for improving the combined-hole film cooling performance is different at different blowing ratios.

References

References
1.
Goldstein
,
R. J.
,
1971
, “
Film Cooling
,”
Advances in Heat Transfer
, Vol.
7
,
Academic Press
,
New York
, pp.
321
379
.
2.
Walters
,
D. K.
, and
Leylek
,
J. H.
,
2000
, “
A Detailed Analysis of Film-Cooling Physics—Part 1: Streamwise Injection With Cylindrical Holes
,”
ASME J. Turbomach.
,
122
(
1
), pp.
102
112
.10.1115/1.555433
3.
Mayhew
,
J. E.
,
Baughn
,
J. W.
, and
Byerley
,
A. R.
,
2003
, “
The Effect of Freestream Turbulence on Film Cooling Adiabatic Effectiveness
,”
Int. J. Heat Fluid Flow
,
24
(
5
), pp.
669
679
.10.1016/S0142-727X(03)00081-X
4.
Drost
,
U.
, and
Bolcs
,
A.
,
1999
, “
Investigation of Detailed Film Cooling Effectiveness and Heat Transfer Distributions on a Gas Turbine Airfoil
,”
ASME J. Turbomach.
,
121
(2), pp.
233
242
.10.1115/1.2841306
5.
Zhang
,
L. J.
, and
Pudupaty
,
R.
,
2000
, “
The Effects of Injection Angle and Hole Exit Shape on Turbine Nozzle Pressure Side Film Cooling
,”
ASME
Paper No. 2000-GT-0247.10.1115/2000-GT-0247
6.
Ahn
,
J.
,
Schobeiri
,
M. T.
,
Han
,
J. C.
, and
Moon
,
H. K.
,
2005
, “
Film cooling Effectiveness on the Leading Edge of a Rotating Film-Cooled Blade Using Pressure Sensitive Paint
,”
ASME
Paper No. GT2005-68344.10.1115/GT2005-68344
7.
McGovern
,
K. T.
, and
Leylek
,
J. H.
,
2000
, “
A Detailed Analysis of Film Cooling Physics: Part II Compound-Angle Injection With Cylindrical Holes
,”
ASME J. Turbomach.
,
122
(
1
), pp.
113
121
.10.1115/1.555434
8.
Hyams
,
D. G.
, and
Leylek
,
J. H.
,
2000
, “
A Detailed Analysis of Film Cooling Physics: Part III Streamwise Injection With Shaped Holes
,”
ASME J. Turbomach.
,
122
(
1
), pp.
122
132
.10.1115/1.555435
9.
Gritsch
,
M.
,
Schulz
,
A.
, and
Wittig
,
S.
,
1998
, “
Adiabatic Wall Effectiveness Measurements of Film Cooling Holes With Expanded Exits
,”
ASME J. Turbomach.
,
120
(
3
), pp.
549
556
.10.1115/1.2841752
10.
Schmidt
,
D. L.
,
Sen
,
B.
, and
Bogard
,
D. G.
,
1996
, “
Film Cooling With Compound Angle Holes: Adiabatic Effectiveness
,”
ASME J. Turbomach.
,
118
(4), pp.
807
813
.10.1115/1.2840938
11.
McGrath
,
E. L.
,
Leylek
,
J. H.
, and
Buck
,
F. A.
,
2002
, “
Film Cooling on a Modern HP Turbine Blade Part 4: Compound-Angle Shaped Holes
,”
ASME
Paper No. GT2002-30521.10.1115/GT2002-30521
12.
Kusterer
,
K.
,
Bohn
,
D.
,
Sugimoto
,
T.
, and
Tanaka
,
R.
,
2007
, “
Double-Jet Ejection of Cooling Air for Improved Film Cooling
,”
ASME J. Turbomach.
,
129
(
4
), pp.
809
815
.10.1115/1.2720508
13.
Heidmann
,
J. D.
,
2008
, “
A Numerical Study of Anti-Vortex Film Cooling Designs at High Blowing Ratio
,”
ASME
Paper No. GT2008-50845.10.1115/GT2008-50845
14.
Han
,
C.
,
Ren
,
J.
, and
Jiang
,
H. D.
,
2012
, “
Multi-Parameter Influence on Combined-Hole Film Cooling System
,”
Int. J. Heat Mass Transfer
,
55
(
15–16
), pp.
4232
4240
.10.1016/j.ijheatmasstransfer.2012.03.064
15.
Kusterer
,
K.
,
Elyas
,
A.
,
Bohn
,
D.
,
Sugimoto
,
T.
,
Tanaka
,
R.
, and
Kazari
,
M.
,
2010
, “
Film Cooling Effectiveness Comparison Between Shaped- and Double Jet Film Cooling Holes in a Row Arrangement
,”
ASME
Paper No. GT-2010-22604.10.1115/GT2010-22604
16.
Li
,
X. Y.
,
Ren
,
J.
, and
Jiang
,
H. D.
,
2011
, “
Algebraic Anisotropic Eddy-Viscosity Modeling Application to the Turbulent Film Cooling Flows
,”
ASME
Paper No. GT2011-45791.10.1115/GT2011-45791
17.
Li
,
X. Y.
,
Ren
,
J.
, and
Jiang
,
H. D.
,
2012
, “
Full Field Algebraic Anisotropic Eddy Viscosity Model
,”
ASME
Paper No. GT2012-68667.10.1115/GT2012-68667
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