Adiabatic film-cooling effectiveness is examined systematically on a typical high pressure turbine blade by varying three critical flow parameters: coolant blowing ratio, coolant-to-mainstream density ratio, and freestream turbulence intensity. Three coolant density ratios 1.0, 1.5, and 2.0 are chosen for this study. The average blowing ration and the turbulence intensity are 1.5% and 10.5%, respectively. Conduction-free pressure sensitive paint (PSP) technique is used to measure film-cooling effectiveness. Foreign gases are used to study the effect of coolant density. Two test blades feature axial angle and 45 deg compound-angle shaped holes on the suction side and pressure side. Both designs have 3 rows of 30 deg radial-angle cylindrical holes around the leading edge region. The inlet and the exit Mach number are 0.27 and 0.44, respectively. Reynolds number based on the exit velocity and blade axial chord length is 750,000. Overall, the compound angle design performs better film coverage that axial angle. Greater coolant-to-mainstream density ratio results in lower coolant-to-mainstream momentum and prevents coolant to lift-off.

References

References
1.
Han
,
J. C.
, and
Rallabandi
,
A. P.
,
2010
, “
Turbine Blade Film Cooling Using PSP Technique
,”
Front. Heat Mass Transfer
,
1
(
1
), pp.
1
21
.
2.
Gao
,
Z.
,
Narzary
,
D. P.
, and
Han
,
J. C.
,
2009
, “
Film-Cooling on a Gas Turbine Blade Pressure Side or Suction Side With Compound Angle Shaped Holes
,”
ASME J. Turbomach.
,
131
(
1
), p.
011019
.10.1115/1.2813012
3.
Narzary
,
D. P.
,
Liu
,
K. C.
, and
Rallabandi
,
A. P.
,
2010
, “
Influence of Coolant Density on Turbine Blade Film-Cooling Using Pressure Sensitive Paint Technique
,” ASME Paper No. GT2010-22781.
4.
Liu
,
K.
,
Narzary
,
D. P.
,
Han
,
J. C.
,
Mirzamoghadam
,
A. V.
, and
Riahi
,
A.
,
2010
, “
Influence of Shock Wave on Turbine Vane Suction Side Film Cooling With Compound-Angle Shaped Holes
,” ASME Paper No. GT2011-45927.
5.
McLachlan
,
B.
, and
Bell
,
J.
,
1995
, “
Pressure-Sensitive Paint in Aerodynamic Testing
,”
Exp. Therm. Fluid Sci.
,
10
(
4
), pp.
470
485
.10.1016/0894-1777(94)00123-P
6.
Jones
,
T.
,
1999
, “
Theory for the Use of Foreign Gas in Simulating Film Cooling
,”
Int. J. Heat Fluid Flow
,
20
(
3
), pp.
349
354
.10.1016/S0142-727X(99)00017-X
7.
Charbonnier
,
D.
,
Ott
,
P.
,
Jonsson
,
M.
,
Cottier
,
F.
, and
Köbke
,
T.
,
2009
, “
Experimental and Numerical Study of the Thermal Performance of a Film Cooled Turbine Platform
,” ASME Paper No. GT2009-60306.
8.
Kline
,
S. J.
, and
McClintock
,
F.
,
1953
, “
Describing Uncertainties in Single-Sample Experiments
,”
Mech. Eng.
,
75
(
1
), pp.
3
8
.
You do not currently have access to this content.