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TECHNICAL PAPERS

Experimental Evaluation of an Inlet Profile Generator for High-Pressure Turbine Tests

[+] Author and Article Information
M. D. Barringer

Mechanical Engineering Department, Virginia Polytechnic Institute and State University, Blacksburg, VA 24061mbarringer@vt.edu

K. A. Thole

Department of Mechanical and Nuclear Engineering, The Pennsylvania State University, University Park, PA 16802kthole@psu.edu

M. D. Polanka

 Air Force Research Laboratory, Turbines Branch, WPAFB, OH 45433Marc.Polanka@wpafb.af.mil

J. Turbomach 129(2), 382-393 (Jul 31, 2006) (12 pages) doi:10.1115/1.2436897 History: Received July 24, 2006; Revised July 31, 2006

Improving the performance and durability of gas turbine aircraft engines depends highly on achieving a better understanding of the flow interactions between the combustor and turbine sections. The flow exiting the combustor is very complex and it is characterized primarily by elevated turbulence and large variations in temperature and pressure. The heat transfer and aerodynamic losses that occur in the turbine passages are driven primarily by these spatial variations. To better understand these effects, the goal of this work is to benchmark an adjustable turbine inlet profile generator for the Turbine Research Facility (TRF) at the Air Force Research Laboratory. The research objective was to experimentally evaluate the performance of the nonreacting simulator that was designed to provide representative combustor exit profiles to the inlet of the TRF turbine test section. This paper discusses the verification testing that was completed to benchmark the performance of the generator. Results are presented in the form of temperature and pressure profiles as well as turbulence intensity and length scale. This study shows how a single combustor geometry can produce significantly different flow and thermal field conditions entering the turbine. Engine designers should place emphasis on obtaining accurate knowledge of the flow distribution within the combustion chamber. Turbine inlet conditions with significantly different profile shapes can result in altered flow physics that can change local aerodynamics and heat transfer.

Copyright © 2007 by American Society of Mechanical Engineers
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References

Figures

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Figure 15

Circumferential pressure near midspan over three vane pitches for Tests 107 (top) and 123 (bottom)

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Figure 16

Circumferential temperature near midspan over three vane pitches for Tests 107 (top) and 127 (bottom)

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Figure 1

Photograph of the TRF facility

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Figure 2

Photograph of the TRF combustor simulator

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Figure 3

Drawing of the central annular chamber (inlet shutter not shown)

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Figure 4

General instrumentation locations

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Figure 5

Plot of several radial pressure profiles measured at the simulator exit for the baseline tests

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Figure 6

Plot of several engine and combustor simulator exit pressure profiles

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Figure 7

Several pressure profiles measured at the simulator exit at different Reynolds numbers

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Figure 8

Plot of the pressure profile peak (measured) near the ID and OD endwalls scaled to the film cooling momentum flux ratio and simulator exit Re number

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Figure 9

Plots of pressure profiles at the simulator exit when the total dilution mass flow is: (a) 23–38%, and (b) 43–74% of the total combustor exit flow

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Figure 10

Plot of several radial temperature profiles measured at the simulator exit for the baseline tests

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Figure 11

Plot of several engine and simulator combustor exit temperature profiles

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Figure 12

Several temperature profiles measured at the simulator exit at different Reynolds numbers

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Figure 13

Plot of the near endwall temperatures as a function of film cooling temperature and momentum flux ratio for the baseline tests

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Figure 14

Plot of Tu and Λx at the midspan for hotwire Test 011

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