An Argument for Enhancement of the Current Inlet Distortion Ground Test Practice for Aircraft Gas Turbine Engines

[+] Author and Article Information
Milt Davis, Alan Hale, Dave Beale

Sverdrup Technology, Inc., Arnold Engineering Development Center, AEDC, Arnold Air Force Base, TN 37389

J. Turbomach 124(2), 235-241 (Apr 09, 2002) (7 pages) doi:10.1115/1.1451087 History: Received November 17, 2000; Online April 09, 2002
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SAE Aerospace Recommended Practice, 1978, ARP-1420, “Gas Turbine Engine Inlet Flow Distortion Guidelines,” Mar.
SAE Aerospace Information Report, 1983, AIR-1419, “Inlet Total-Pressure Distortion Considerations for Gas Turbine Engines,” May.
Davis, M. W., Jr., et al. 1999, “A Proposal for Integration of Wind Tunnel and Engine Test Programs for the Evaluation of Airframe-Propulsion Compatibility Using Numerical Simulations,” ASME Paper No. 99-GT-345.
Overall, B. W., 1976, “Evaluation of an Airjet Distortion Generator Used to Produce Steady-State Total-pressure Distortion at the Inlet of Turbine Engines,” AEDC-TR-76-141.
Brimelow, B., Collins, T. P., and G. A. Pfefferkorn, 1976, “Engine Testing in a Dynamic Environment,” AIAA Paper No. 74-1198.
Lazalier, G. R., and J. T. Tate, 1970, “Development of a Prototype Discrete Frequency, Total-pressure Fluctuation Generator for Jet Engine/Inlet Compatibility Investigation,” Proc. Air Force Airframe Propulsion Compatibility Symposium, AFAPL-TR-69-103.
Reynolds, G. G., et al., 1973, “An Experimental Evaluation of Unsteady Flow Effects on an Axial Compressor—P3 Generator Program,” AFAPL-TR-73-43, July.
SAE S-16 Committee, 1995, ARD50026, “A Current Assessment of Planer Waves,” Society of Automotive Engineers.
Hale,  A. A., and O’Brien,  W. F., 1998, “A Three-Dimensional Turbine Engine Analysis Compressor Code (TEACC) for Steady-State Inlet Distortion,” ASME J. Turbomach., 120, pp. 422–430.
Hearsey, R. M., 1970, “HTO300—A Computer Program for the Design and Analysis of Axial Turbomachinery.”
Seyler, D. R., and Gestolow, J. P., 1967, “Single Stage Experimental Evaluation of High Mach Number Compressor Rotor Blading—Part 2: Performance of Rotor 1B,” NASA-CR-54582.
Longley, J. P., et al., 1994, “Effects of Rotating Inlet Distortion on Multistage Compressor Stability,” ASME Paper 94-GT-220.
Stocks, C. P., and Bissinger, N. C., 1981, “The Design and Development of the Tornado Engine Air Intake,” Paper No. 10 of AGARD CP-301.
Ludwig, G., 1989, “Tomahawk Engine/Inlet Compatibility Study for F107-WR-400/402 Engines,” Williams International Report CMEP 5003-2025.


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Typical distortion screen and corresponding distortion pattern
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Schematic of airjet distortion generator
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Simulation of time-variant distortion with steady-state patterns
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Overall TEACC methodology
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Radial-circumferential view of 3-D grid for Rotor 1B
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Rotor 1B distortion screen definition
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Comparison of TEACC calculations with distortion to that observed experimentally
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Dynamic distortion generator concept and corresponding airflow reduction behind the screen
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Flow coefficient at stall versus distortion rotation rate 12
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Effect of rotating screen on Rotor 1B stability limit
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Example of induced swirl at screen boundary location—co-rotation shown
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Comparison of blade overall performance with swirl at a constant airflow rate
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Comparison of flowfield swirl before and after the rotor against the clean inlet for both co and counter-rotation swirl
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Comparison of blade performance with co and counter-rotation present




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