The relative aerodynamic and performance effects associated with rotor–NGV gap coolant injections were investigated in the Axial Flow Turbine Research Facility (AFTRF) of the Pennsylvania State University. This study quantifies the effects of the coolant injection on the aerodynamic performance of the turbine for radial cooling, impingement cooling in the wheelspace cavity and root injection. Overall, it was found that even a small quantity (1 percent) of cooling air can have significant effects on the performance character and exit conditions of the high pressure stage. Parameters such as the total-to-total efficiency, total pressure loss coefficient, and three-dimensional velocity field show local changes in excess of 5, 2, and 15 percent, respectively. It is clear that the cooling air disturbs the inlet end-wall boundary layer to the rotor and modifies secondary flow development, thereby resulting in large changes in turbine exit conditions.

Issue Section:
Technical Papers
Keywords:
gas turbines, aerodynamics, cooling, rotors, thermodynamics, high-pressure effects, rotational flow
Topics:
Coolants, Cooling, Flow (Dynamics), Pressure, Rotors, Turbines, Uncertainty, Impingement cooling, High pressure (Physics)
1.
Karstensen, K., 1997, “The Solar Turbines Project—Developing the 21st Century Gas Turbine,” Department of Energy Office of Fossil Energy, Project Synopsis.
2.
Alwang, A., 1981, “Measurement of Non-Steady Fluid Dynamic Quantitie´s,” von Karman Institute for Fluid Dynamics Lecture Series—Measurement Techniques in Turbomachines.
3.
Metzger, D., Kim, Y., and Yu, Y., 1993, “Turbine Cooling: An Overview of Some Focus Topics,” Proc. 1993 International Symposium on Transport Phenomena in Thermal Engineering.
4.
Owen, J. M., and Rogers, R. H., 1989, “Flow and Heat Transfer in Rotating Disc Systems, Vol. 1: Rotor-Stator Systems,” Research Studies Press ltd. and John Wiley.
5.
Bunker, R., Metzger, D., and Wittig, S., 1992, “Local Heat Transfer in Turbine Disk Cavities: Part I—Rotor and Stator Cooling With Hub Injection of Coolant,” ASME J. Turbomach., 114.
6.
Bunker, R., Metzger, D., and Wittig, S., 1992, “Local Heat Transfer in Turbine Disk Cavities: Part II—Rotor Cooling With Radial Location Injection of Coolant,” ASME J. Turbomach., 114.
7.
von Karman, T., 1921, “U¨ber Llaminare und Turbulente Reibung,” Z. Angew. Math. Mech., 1.
8.
Cobb
,
E.
, and
Saunders
,
O.
,
1956
, “
Heat Transfer From a Rotating Disk
,”
Proc. R. Soc. London, Ser. A
,
26A
, pp.
343
–
351
.
9.
Maroti, L., Deak, G., and Kreith, F., 1960, “Flow Phenomena of Partially Enclosed Rotating Disks,” ASME J. Basic Eng., 82.
10.
Daily
,
J.
, and
Nece
,
R.
,
1960
, “
Chamber Dimensional Effects on Induced Flow and Frictional Resistance of Enclosed Rotating Disks
,”
ASME J. Basic Eng.
,
82
, pp.
217
–
232
.
11.
Dorfman, L. A., 1963, Hydrodynamic Resistance and the Heat Loss of Rotating Solids, Oliver and Boyd, Edinburgh.
12.
Metzger
,
D.
,
Mathis
,
W.
, and
Grochowsky
,
L.
,
1979
, “
Jet Cooling at the Rim of a Rotating Disk
,”
ASME J. Eng. Power
,
101
, pp.
68
–
72
.
13.
Popiel
,
C.
, and
Boguslawski
,
L.
,
1986
, “
Local Heat Transfer From a Rotating Disk in an Impinging Round Jet
,”
ASME J. Heat Transfer
,
108
, pp.
357
–
364
.
14.
Qureshi, G., Nguyen, M., Saad, N., and Tadros, R., 1989, “Heat Transfer Measurements for Rotating Turbine Disks,” ASME Paper No. 89-GT-26.
15.
Pincombe, J., 1989, “Chapter 33, Gas Turbine Disk Cooling Flows,” Handbook of Flow Visualization, Wen-Jei Yang, ed., Hemisphere Publishing Corp.
16.
Lakshminarayana
,
B.
,
Camci
,
C.
,
Halliwell
,
I.
, and
Zaccaria
,
M.
,
1996
, “
Design and Development of a Turbine Research Facility to Study Rotor–Stator Interaction
,”
Int. J. Turbo Jet Engines
,
13
, pp.
155
–
172
.
17.
Laksminarayana, B., Camci, C., Halliwell, I., and Zaccaria, M., 1992, “Investigation of Three Dimensional Flow Field in a Turbine Including Rotor/Stator Interaction,” AIAA/SAE/ASME/ASEE 28th Joint Propulsion Conference and Exhibit, July 6–8, Nashville, TN.
18.
Friedrichs
,
S.
,
Hodson
,
H. P.
, and
Dawes
,
W. N.
,
1997
, “
Aerodynamic Aspects of Endwall Film-Cooling
,”
ASME J. Turbomach.
,
119
, pp.
786
–
795
.
19.
Wiedner, G., 1994, “Passage Flow Structure and Its Influence on Endwall Heat Transfer in a 90° Turning Duct,” Ph.D. Thesis in Aerospace Engineering, The Pennsylvania State University.
20.
Zaccaria, M. A., 1994, “Investigation of Three Dimensional Flow Field in a Turbine Including Rotor/Stator Interaction,” Ph.D. Thesis in Aerospace Engineering, The Pennsylvania State University.
21.
McDonel, J. D., and Eiswerth, J. E., 1977, “Effects of Film Injection on Performance of a Cooled Turbine,” AGARD Conference Proceedings, CP-229.
22.
Abernathy, R. B., Benedict, R. P., and Dowdell, R. B., 1985, “ASME Measurement Uncertainty,” ASME J. Fluids Eng., 107.
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