This paper investigates the aerodynamic and film cooling effectiveness characteristics of a first stage turbine high lift guide vane and its corresponding downstream blade. The vane and blade geometrical profiles and operating conditions are representative of that normally found in a heavy-duty gas turbine. Both the vane and the blade airfoils consist of multirow film cooling holes located at various axial positions along the airfoil chord. The film cooling holes are geometrically three-dimensional in shape and depending on the location on the airfoil, they can be either symmetrically fan shaped or nonsymmetrically fan shaped. Additionally the film cooling holes can be either compounded or in-line with the external flow direction. Numerical studies and experimental investigations in a linear cascade have been conducted at vane and blade exit isentropic Mach number of 0.8. The influence of the coolant flow ejected from the film cooling holes has been investigated for both the vane and the blade profiles. For the nozzle guide vane, the measured film cooling effectiveness compared well with the predictions, especially on the pressure side. The suction side film cooling effectiveness, which consisted of two prethroat film rows, proved very effective up to the suction side trailing edge. For the blade, there was a reasonable comparison between the measured and predicted film cooling effectiveness. Again the blade prethroat fan shaped cooling holes proved very effective up to the suction side trailing edge. For the vane, the impact of varying the blowing ratios showed a strong variation in the film cooling effectiveness on the pressure side. However, on the blade, the effect of varying the blowing ratio had a greater impact on the suction side film effectiveness compared to the pressure side.

References

References
1.
Hiddemann
,
M.
,
Hummel
,
F.
,
Schmidli
,
J.
, and
Tunon
,
P.
,
2011
, “
The Next Generation Alstom GT26, The Pioneer in Operational Flexibility
,” Power-Gen, Milan, Italy, June 7–9.
2.
Lanzenberger
,
K.
,
Daxer
,
J.
,
Philipson
,
S.
, and
Hoffs
,
A.
,
2008
, “
A Further Retrofit Upgrade For Alstom's Sequential Combustion GT24 Gas Turbine
,” PowerGen International, New Orleans, LA, December 11–13.
3.
Hoffs
,
A.
,
Doebbeling
,
K.
, and
Philipson
,
S.
,
2007
, “
Evolutionary Steps—A Further Performance Upgrade for Alstom's GT13E2 Gas Turbine
,” Power-Gen Middle East, Manama, Bahrain, January 22–24.
4.
Philipson
,
S.
,
Lindvall
,
K.
, and
Ladwig
,
M.
,
2008
, “
Alstom's GT26 Gas Turbine—A Field Proven Advanced Class Gas Turbine For All Duties
,” Russian Power Conference, Moscow, April 15–17.
5.
Stephan
,
B.
,
Krueckels
,
J.
, and
Gritsch
,
M.
,
2010
, “
Investigation of Aerodynamic Losses and Film Cooling Effectiveness for a NGV Profile
,”
ASME
Paper No. GT2010-22810.10.1115/GT2010-22810
6.
Krueckels
,
J.
,
Colban
,
W.
,
Gritsch
,
M.
, and
Schnieder
,
M.
, 2011, “
Validation of a First Vane Platform Cooling Design
,”
ASME
Paper No. GT2011-45252.10.1115/GT2011-45252
7.
Krueckels
,
J.
,
Gritsch
,
M.
, and
Schnieder
,
M.
, 2009, “
Design Considerations and Validation of Trailing Edge Pressure Side Bleed Cooling
,”
ASME
Paper No. GT2009-59161.10.1115/GT2009-59161
8.
Colban
,
W.
,
Gratton
,
A.
,
Thole
,
K. A.
, and
Haendler
,
M.
,
2005
, “
Heat Transfer and Film-Cooling Measurements on a Stator Vane With Fan-Shaped Cooling Holes
,” ASME Turbo Expo 2005: Power for Land, Sea, and Air, Reno-Tahoe, NV, June 6–9,
ASME
Paper No. GT2005-68258.10.1115/GT2005-68258
9.
Colban
,
W.
,
Thole
,
K. A.
, and
Haendler
,
M.
,
2007
, “
Experimental and Computational Comparisons of Fan-Shaped Film Cooling on a Turbine Vane Surface
,”
ASME J. Turbomach.
,
129
, pp.
23
31
.10.1115/1.2370747
10.
Colban
,
W. F.
,
Thole
,
K. A.
, and
Bogard
,
D.
,
2011
, “
A Film-Cooling Correlation for Shaped Holes on a Flat-Plate Surface
,”
ASME J. Turbomach.
,
133
, p.
011002
.10.1115/1.4002064
11.
Nirmalan
,
N. V.
, and
Hylton
,
L. D.
,
1990
, “
An Experimental Study of Turbine Vane Heat Transfer With Leading Edge and Downstream Film Cooling
,”
ASME J. Turbomach.
,
112
, pp.
477
487
.10.1115/1.2927683
12.
Abuaf
,
N.
,
Bunker
,
R.
, and
Lee
,
C. P.
,
1997
, “
Heat Transfer and Film Cooling Effectiveness in a Linear Airfoil Cascade
,”
ASME J. Turbomach.
,
119
, pp.
302
309
.10.1115/1.2841113
13.
Camci
,
C.
, and
Arts
,
T.
,
1985
, “
Experimental Heat Transfer Investigation Around the Film Cooled Leading Edge of a High Pressure Gas Turbine Rotor Blade
,”
ASME J. Eng. Gas Turbines and Power
,
107
, pp.
1016
1021
.10.1115/1.3239805
14.
Goldstein
,
R. J.
, and
Chen
,
H. P.
,
1985
, “
Film Cooling on a Gas Turbine Blade Near the Endwall
,”
ASME J. Eng. Gas Turbines and Power
,
107
, pp.
117
122
.10.1115/1.3239670
15.
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
, pp.
233
242
.10.1115/1.2841306
16.
Gritsch
,
M.
,
Schulz
,
A.
, and
Wittig
,
S.
,
1998
, “
Heat Transfer Coefficients Measurements of Film-Cooling Holes With Expanded Exits
,”
IGTI Conference
,
Stockholm
, June 2–5,
ASME
Paper No. 98-GT-28.
17.
Bell
,
C. M.
,
Hamakawa
,
H.
, and
Ligrani
,
P. M.
,
2000
, “
Film Cooling From Shaped Holes
,”
ASME J. Heat Transfer
,
122
, pp.
224
232
.10.1115/1.521484
18.
Dittmar
,
J.
,
Schulz
,
A.
, and
Wittig
,
S.
,
2003
, “
Assessment of Various Film-Cooling Configurations Including Shaped and Compound Angle Holes Based on Large-Scale Experiments
,”
ASME J. Turbomach.
,
125
, pp.
57
64
.10.1115/1.1515337
19.
Thole
,
K. A.
,
Gritsch
,
M.
,
Schulz
,
A.
, and
Wittig
,
S.
,
1998
, “
Flowfield Measurements for Film-Cooling Holes With Expanded Exits
,”
ASME J. Turbomach.
,
120
, pp.
327
336
.10.1115/1.2841410
20.
Saumweber
,
C.
, and
Schulz
,
A.
,
2004
, “
Interaction of Film Cooling Rows: Effects of Hole Geometry and Row Spacing on the Cooling Performance Downstream of the Second Row of Holes
,”
ASME J. Turbomach.
,
126
, pp.
237
246
.10.1115/1.1731395
21.
Saumweber
,
C.
, and
Schulz
,
A.
,
2003
, “
Interaction of Film Cooling Rows: Effects of Hole Geometry and Row Spacing on the Cooling Performance Downstream of the Second Row of Holes
,” IGTI Turbo Expo, Atlanta, GA, June 16–19,
ASME
Paper No. GT2003-38195.10.1115/GT2003-38195
22.
Teng
,
S.
, and
Han
,
J. C.
,
2000
, “
Effect of Film-Hole Shape on Turbine Blade Heat Transfer Coefficient Distribution
,”
AIAA
Paper No. 2000-1035.10.2514/6.2000-1035
23.
Furukawa
,
T.
, and
Ligrani
,
P. M.
,
2002
, “
Transonic Film Cooling Effectiveness From Shaped Holes on a Simulated Turbine Airfoil
,”
AIAA J. Thermophys. Heat Transf.
,
16
(
2
), pp.
228
237
.10.2514/2.6672
24.
Mhetras
,
S. P.
,
Han
,
J. C.
, and
Rudolph
,
R.
,
2007
, “
Effect of Flow Parameter Variation on Full Coverage Film Cooling Effectiveness for a Gas Turbine Blade
,”
ASME
Paper No. GT2007-27071.10.1115/GT2007-27071
25.
Gao
,
Z.
,
Narzary
,
D. P.
,
Mhetras
,
S. P.
, and
Han
,
J. C.
,
2007
, “
Full Coverage Film Cooling for a Turbine Blade With Axial Shaped Holes
,”
AIAA
Paper No. 2007-4031.10.2514/6.2007-4031
26.
Moffat
,
R. J.
,
1988
, “
Describing the Uncertainties in Experimental Results
,”
Exp. Therm. Fluid Sci.
,
1
, pp.
3
17
.10.1016/0894-1777(88)90043-X
You do not currently have access to this content.