A large-scale model of an inclined row of film cooling holes is used to obtain detailed surface and flow field measurements that will enable future computational fluid dynamics code development and validation. The model consists of three holes of 1.9-cm diameter that are spaced three hole diameters apart and inclined 30 deg from the surface. The length to diameter ratio of the coolant holes is about 18. Measurements include film effectiveness using IR thermography and near wall thermocouples, heat transfer using liquid crystal thermography, flow field temperatures using a thermocouple, and velocity and turbulence quantities using hotwire anemometry. Results are obtained for blowing ratios of up to 2 in order to capture severe conditions in which the jet is lifted. For purposes of comparison with prior art, measurements of the velocity and turbulence field along the jet centerline are made and compare favorably with two data sets in the open literature thereby verifying the test apparatus and methodology are able to replicate existing data sets. In addition, a computational fluid dynamics model using a two-equation turbulence model is developed, and the results for velocity, turbulent kinetic energy and turbulent dissipation rate are compared with experimentally derived quantities.

References

References
1.
Goldstein
,
R. J.
,
1971
, “
Film Cooling
,”
Adv. Heat Transf.
,
7
, pp.
321
379
.10.1016/S0065-2717(08)70020-0
2.
Thole
,
K. A.
,
Sinha
,
A. K.
,
Bogard
,
D. G.
, and
Crawford
,
M. E.
,
1990
, “
Mean Temperature Measurements of Jets in Crossflow for Gas Turbine Film Cooling Applications
,”
Third International Symposium on Transport Phenomena and Dynamics of Rotating Machinery
(ISROMAC-3),
Honolulu, HI
, February 26–March 2.
3.
Sinha
,
A. K.
,
Bogard
,
D. G.
, and
Crawford
,
M. E.
,
1991
, “
Film-Cooling Effectiveness Downstream of a Single Row of Holes With Variable Density Ratio
,”
ASME J. Turbomach.
,
113
, pp.
442
449
.10.1115/1.2927894
4.
Foster
,
N. W.
, and
Lampard
,
D.
,
1980
, “
The Flow and Film Cooling Effectiveness Following Injection Through a Row of Holes
,”
ASME J. Eng. Power
,
102
, pp.
584
588
.10.1115/1.3230306
5.
Kohli
,
A.
, and
Bogard
,
D. G.
,
1997
, “
Adiabatic Effectiveness, Thermal Fields, and Velocity Fields for Film Cooling With Large Angle Injection
,”
ASME J. Turbomach.
,
119
, pp.
352
358
.10.1115/1.2841118
6.
Foster
,
N. W.
, and
Lampard
,
D.
,
1975
, “
Effect of Density and Velocity Ratio of Discrete Hole Film Cooling
,”
AIAA J.
,
113
, pp.
1112
1114
.10.2514/3.6960
7.
Pietrzyk
,
J. R.
,
Bogard
,
D. G.
, and
Crawford
,
M. E.
,
1990
, “
Effect of Density Ratio on the Hydrodynamics of Film Cooling
,”
ASME J. Turbomach.
,
112
, pp.
437
443
.10.1115/1.2927678
8.
Pietrzyk
,
J. R.
,
Bogard
,
D. G.
, and
Crawford
,
M. E.
,
1989
, “
Hydrodynamic Measurements of Jets in Crossflow for Gas Turbine Film Cooling Application
,”
ASME J. Turbomach.
,
111
, pp.
139
145
.10.1115/1.3262248
9.
Pietrzyk
,
J. R.
,
1989
, “
Experimental Study of Interaction of Dense Jets With a Crossflow for Gas Turbine Applications
,” Ph.D. thesis,
University of Texas at Austin
,
Austin, TX
.
10.
Walters
,
D. K.
, and
Leylek
,
J. H.
,
1997
, “
A Systematic Computational Methodology Applied to a Three-Dimensional Film-Cooling Flowfield
,”
ASME J. Turbomach.
,
119
, pp.
777
785
.10.1115/1.2841188
11.
El-Gabry
,
L.
,
Heidmann
,
J.
, and
Ameri
,
A.
,
2010
, “
Penetration Characteristics of Film-Cooling Jets at High Blowing Ratio
,”
AIAA J.
,
48
, pp.
1020
1024
.10.2514/1.42611
12.
Andreopoulos
,
J.
, and
Rodi
,
W.
,
1984
, “
Experimental Investigations of Jets in a Crossflow
,”
J. Fluid Mech.
,
138
, pp.
93
127
.10.1017/S0022112084000057
13.
Kohli
,
A.
, and
Bogard
,
D. G.
,
2005
, “
Turbulent Transport in Film Cooling Flows
,”
ASME J. Heat Transf.
,
127
, pp.
513
520
.10.1115/1.1865221
14.
Roach
,
P. E.
,
1986
, “
The Generation of Nearly Isotropic Turbulence by Means of Grids
,”
Heat Fluid Flow
,
8
(
2
), pp.
89
92
.10.1016/0142-727X(87)90001-4
15.
El-Gabry
,
L.
,
Thurman
,
D.
, and
Poinsatte
,
P.
,
2011
, “
Procedure for Determining Length Scales Using Hotwire Anemometry
,” NASA/TM (NF1676B TN4063).
16.
Thurman
,
D.
,
El-Gabry
,
L.
,
Poinsatte
,
P.
, and
Heidmann
,
J.
,
2011
, “
Turbulence and Heat Transfer Measurements in an Inclined Large Scale Film Cooling Array—Part II, Temperature and Heat Transfer Measurements
,”
ASME Turbo Expo 2011
,
Vancouver
, Canada, June 6–10,
ASME
Paper No. GT2011-46498.10.1115/GT2011-46498
17.
Yavuzkurt
,
S.
,
1984
, “
A Guide to Uncertainty Analysis of Hot-Wire Data
,”
J. Fluid Eng.
,
106
, pp.
181
186
.10.1115/1.3243096
18.
Bruun
,
H. H.
,
1995
,
Hot-Wire Anemometry: Principles and Signal Analysis
,
Oxford University Press
, New York.
19.
Johnson
,
P.
,
Shyam
,
V.
, and
Hah
,
C.
,
2011
, “
Reynolds-Averaged Navier–Stokes Solutions to Flat Plate Film Cooling Scenarios
,” NASA/TM-2011-217025, #E-17690.
You do not currently have access to this content.