Research Papers

Effects of Combustor Exit Profiles on Vane Aerodynamic Loading and Heat Transfer in a High Pressure Turbine

[+] Author and Article Information
M. D. Barringer, K. A. Thole

Department of Mechanical and Nuclear Engineering, The Pennsylvania State University, University Park, PA 16802

M. D. Polanka

 Air Force Research Laboratory, Turbines Branch, WPAFB, OH 45433

J. Turbomach 131(2), 021008 (Jan 23, 2009) (10 pages) doi:10.1115/1.2950051 History: Received October 10, 2006; Revised December 03, 2007; Published January 23, 2009

The flow and thermal fields exiting gas turbine combustors dictate the overall performance of the downstream turbine. The goal of this work was to investigate the effects of engine representative combustor exit profiles on high pressure turbine vane aerodynamics and heat transfer. The various profiles were produced using a nonreacting turbine inlet profile generator in the Turbine Research Facility (TRF) located at the Air Force Research Laboratory (AFRL). This paper reports how the pressure loading and heat transfer along the vane surface was affected by different turbine inlet pressure and temperature profiles at different span locations. The results indicate that the inlet total pressure profiles affected the aerodynamic loading by as much as 10%. The results also reveal that the combination of different total pressure and total temperature profiles significantly affected the vane heat transfer relative to a baseline test with uniform inlet total pressure and total temperature. Near the inner diameter endwall, the baseline heat transfer was reduced 30–40% over the majority of the vane surface. Near the outer dimeter endwall, it was found that certain inlet profiles could increase the baseline heat transfer by 10–20%, while other profiles resulted in a decrease in the baseline heat transfer by 25–35%. This study also shows the importance of knowing an accurate prediction of the local flow driving temperature when determining vane surface heat transfer.

Copyright © 2009 by American Society of Mechanical Engineers
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Figure 1

Velocity contours within the vane passage (X∕C=0.35) from Colban (9) showing secondary flow vectors and their corresponding vane inlet total pressure profiles for (A) a turbulent boundary layer and (B) a forward facing inflection point near the endwall

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Figure 2

Photograph of the TRF facility

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Figure 3

Drawing of the combustor simulator central chamber indicating the general flow paths

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Figure 4

Instrumentation rakes mounted in the upstream (left) and downstream (right) traverses

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Figure 5

Photographs of TRF vanes that were instrumented with pressure gauges (left) and HFGs (right)

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Figure 6

Plot of several radial pressure profiles at the turbine vane inlet

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Figure 7

Plot of the vane surface pressure at (a) Z∕Sp=0.50 and (b) Z∕Sp=0.90

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Figure 8

Plot of several radial temperature profiles at the turbine vane inlet

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Figure 9

Nusselt number distribution along the vane surface in the ID region at (a) Z∕Sp=0.24 and in the OD region at (b) Z∕Sp=0.90

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Figure 10

Plot of the Stanton number versus Reynolds number along the vane surface at (a) Z∕Sp=0.24 and (b) Z∕Sp=0.90

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Figure 11

Plot showing the effect of driving temperature on Nusselt number at the Z∕Sp=0.24 and Z∕Sp=0.90 measurement locations for a vane inlet pressure profile corresponding to type A (test 126) and type B (test 135)




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