Film cooling flow for reduction in heat flux to a gas turbine engine hot gas path component is generally assumed to be steady. However, unsteady film cooling may occur due to naturally occurring flow unsteadiness or may be induced intentionally. Analysis of pulsed or otherwise unsteady film coolant flow necessitates a reformulation of the existing steady-state technique for net heat flux reduction (NHFR). We show that addition of a cross-coupled term to the traditional steady form of the NHFR equation with time averaged quantities accounts for the unsteady effects. In the experimental technique to determine the time averaged NHFR, we present a new parameter γ to capture the combined influence of the average adiabatic effectiveness and the coupling between η and h. Measurement of γ is shown to be straightforward but requiring careful considerations beyond those required to measure η with steady film cooling.

1.
Sen
,
B.
,
Schmidt
,
D. L.
, and
Bogard
,
D. G.
, 1996, “
Film Cooling With Compound Angle Holes: Heat Transfer
,”
ASME J. Turbomach.
0889-504X,
118
, pp.
800
806
.
2.
Ekkad
,
S. V.
,
Ou
,
S.
, and
Rivir
,
R. B.
, 2006, “
Effect of Jet Pulsation and Duty Cycle on Film Cooling From a Single Jet on a Leading Edge Model
,”
ASME J. Turbomach.
0889-504X,
128
, pp.
564
571
.
3.
Coulthard
,
S.
,
Volino
,
R.
, and
Flack
,
K.
, 2007, “
Effect of Jet Pulsing on Film Cooling-Part I: Effectiveness and Flow-Field Temperature Results
,”
ASME J. Turbomach.
0889-504X,
129
, pp.
232
246
.
4.
Coulthard
,
S.
,
Volino
,
R.
, and
Flack
,
K.
, 2007, “
Effect of Jet Pulsing on Film Cooling-Part II: Heat Transfer Results
,”
ASME J. Turbomach.
0889-504X,
129
, pp.
247
257
.
5.
ASM International
, 2000,
ASM Specialty Handbook: Nickel, Cobalt, and Their Alloys
,
ASM International
,
Metals Park, OH
.
6.
Han
,
J. C.
,
Dutta
,
S.
, and
Ekkad
,
S. V.
, 2000,
Gas Turbine Heat Transfer and Cooling Technology
,
Taylor & Francis
,
London
, Chap. 2.
7.
Mick
,
W. J.
, and
Mayle
,
R. E.
, 1988, “
Stagnation Film Cooling and Heat Transfer Including Its Effect Within the Hole Pattern
,”
ASME J. Turbomach.
0889-504X,
110
, pp.
66
72
.
8.
Rutledge
,
J. L.
,
King
,
P. I.
, and
Rivir
,
R. B.
, 2008, “
CFD Predictions of Pulsed Film Cooling Heat Flux on a Turbine Blade Leading Edge
,”
ASME
Paper No. IMECE2008-67276.
9.
Rutledge
,
J. L.
,
King
,
P. I.
, and
Rivir
,
R.
, 2009, “
Net Heat Flux Reduction Performance of Pulsed Film Cooling on a Turbine Blade Leading Edge
,”
AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
, AIAA Paper No. 2009-5103.
10.
Rutledge
,
J. L.
,
King
,
P. I.
, and
Rivir
,
R.
, 2009, “
Experimental Flow Visualization of Pulsed Film Cooling on a Turbine Blade Leading Edge
,”
AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
, AIAA Paper No. 2009-5104.
You do not currently have access to this content.