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Research Papers

An Experimental Study of Combustor Exit Profile Shapes on Endwall Heat Transfer in High Pressure Turbine Vanes

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

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

M. D. Polanka

Turbines Branch, Turbine Engine Division, Air Force Research Laboratory, WPAFB, OH 45433

J. Turbomach 131(2), 021009 (Jan 23, 2009) (10 pages) doi:10.1115/1.2950072 History: Received July 26, 2007; Revised December 05, 2007; Published January 23, 2009

The design and development of current and future gas turbine engines for aircraft propulsion have focused on operating the high pressure turbine at increasingly elevated temperatures and pressures. The drive toward thermal operating conditions near theoretical stoichiometric limits as well as increasingly stringent requirements on reducing harmful emissions both equate to the temperature profiles exiting combustors and entering turbines becoming less peaked than in the past. This drive has placed emphasis on determining how different types of inlet temperature and pressure profiles affect the first stage airfoil endwalls. The goal of the current study was to investigate how different radial profiles of temperature and pressure affect the heat transfer along the vane endwall in a high pressure turbine. Testing was performed in the Turbine Research Facility located at the Air Force Research Laboratory using an inlet profile generator. Results indicate that the convection heat transfer coefficients are influenced by both the inlet pressure profile shape and the location along the endwall. The heat transfer driving temperature for inlet profiles that are nonuniform in temperature is also discussed.

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Copyright © 2009 by American Society of Mechanical Engineers
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Figures

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Figure 1

Photograph of the TRF facility

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Figure 2

Drawing of the TRF test rig in a vane only configuration with the inlet profile generator

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Figure 3

Photograph of the turbine vane OD endwall instrumented with thin film heat flux gauges

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Figure 4

Schematic of the OD endwall indicating the locations of the thin film heat flux gauges

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Figure 5

Radial total pressure profiles measured at the vane inlet near the OD

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Figure 6

Radial total temperature profiles corresponding to the pressure profiles in Fig. 5

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Figure 7

Schematics illustrating secondary flow patterns that develop within the vane passage including (a) a cross-passage view near midaxial chord looking downstream, (b) a span view looking toward the endwall, and (c) an isometric view upstream looking downstream

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Figure 8

Velocity contours within the vane passage (X∕C=0.35) from Colban (8) showing secondary flow vectors and their corresponding vane inlet total pressure profiles for (a) a turbulent boundary layer and (b) a forward facing IP boundary layer near the endwall

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Figure 9

Nusselt number scaling for heat flux gauge (a) G1 near vane stagnation, (b) G2 near the vane pressure side leading edge, (c) H1 at the passage inlet near midpitch, and (d) H2 near the passage inlet near midpitch

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Figure 10

Nusselt number scaling for heat flux gauge (a) G3 near the vane pressure side at midaxial chord, (b) H3 near the vane pressure side trailing edge, and (c) H4 near the vane passage exit

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Figure 11

Nusselt number augmentation versus X∕C for each heat flux gauge

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