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Research Papers

Migration of Combustor Exit Profiles Through 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, J. P. Clark, P. J. Koch

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

J. Turbomach 131(2), 021010 (Jan 23, 2009) (10 pages) doi:10.1115/1.2950076 History: Received July 26, 2007; Revised January 03, 2008; Published January 23, 2009

The high pressure turbine stage within gas turbine engines is exposed to combustor exit flows that are nonuniform in both stagnation pressure and temperature. These highly turbulent flows typically enter the first stage vanes with significant spatial gradients near the inner and outer diameter endwalls. These gradients can result in secondary flow development within the vane passage that is different than what classical secondary flow models predict. The heat transfer between the working fluid and the turbine vane surface and endwalls is directly related to the secondary flows. The goal of the current study was to examine the migration of different inlet radial temperature and pressure profiles through the high turbine vane of a modern turbine engine. The tests were performed using an inlet profile generator located in the Turbine Research Facility at the Air Force Research Laboratory. Comparisons of area-averaged radial exit profiles are reported as well as profiles at three vane pitch locations to document the circumferential variation in the profiles. The results show that the shape of the total pressure profile near the endwalls at the inlet of the vane can alter the redistribution of stagnation enthalpy through the airfoil passage significantly. Total pressure loss and exit flow angle variations are also examined for the different inlet profiles.

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Copyright © 2009 by American Society of Mechanical Engineers
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Figures

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Figure 8

CFD prediction of the exit flow angle as a function of vane span

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Figure 9

Average total pressure loss as a function of span location for the different inlet profiles

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Figure 10

Radial total pressure profiles measured at the vane exit for (a) Inlet profile A, (b) Inlet Profile B, (c) Inlet Profile C, and (d) Inlet Profile D

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Figure 12

Secondary flow vectors over contours of nondimensional exit temperature θ near the vane exit plane for Inlet Profiles B and D

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Figure 13

Static pressure, normalized by P1 of the vane airfoil for Inlet Profiles B and D on the pressure surfaces and suction surfaces

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Figure 1

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

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Figure 2

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

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Figure 3

Schematic showing the three different flow path regions and measurement locations

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Figure 4

Radial profiles of total pressure at the vane inlet

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Figure 5

Radial inlet profiles of total temperature corresponding to the pressure profiles in Fig. 4

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Figure 6

Total pressure loss across the vanes at Z∕S=0.19 for Inlet Profile B

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Figure 7

Total pressure loss ξ(%) across the vane for Inlet Profile B with high freestream turbulence 21% (a) and low freestream turbulence 1% (b), shown for three vane pitches

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Figure 11

Radial total temperature profiles measured at the vane exit for (a) Inlet Profile A, (B) Inlet Profile b, (c) Inlet Profile C, and (d) Inlet Profile D

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