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TECHNICAL PAPERS

A Study of the Effects of Tip Clearance in a Supersonic Turbine

[+] Author and Article Information
Daniel J. Dorney

Department of Mechanical Engineering, Virginia Commonwealth University, Richmond, VA 23284-3015

Lisa W. Griffin

Fluids Dynamics Analysis Branch, NASA Marshall Space Flight Center, Marshall Space Flight Center, AL 35812

Frank W. Huber

Riverbend Design Services, Palm Beach Gardens, FL 33418

J. Turbomach 122(4), 674-683 (Feb 01, 2000) (10 pages) doi:10.1115/1.1290400 History: Received February 01, 2000
Copyright © 2000 by ASME
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References

Griffin, L. W., and Rowey, R. J., 1993, “Analytical Investigation of the Unsteady Aerodynamic Environments in Space Shuttle Main Engine (SSME) Turbines,” ASME Paper No. 93-GT-363.
Griffin, L. W., and Huber, F. W., 1993, “Advancement of Turbine Aerodynamic Design Techniques,” ASME Paper No. 93-GT-370.
Griffin,  L. W., Huber,  F. W., and Sharma,  O. P., 1996, “Performance Improvement Through Indexing of Turbine Airfoils: Part 2—Numerical Simulation,” ASME J. Biomech. Eng., 118, No. 4, pp. 636–642.
Griffin, L. W., and Nesman, T., 1996, “Prediction of the Unsteady Aerodymanic Environment in the RRTT Turbine,” presented at the 14th Workshop for Fluid Dynamic Applications in Rocket Propulsion and Launch Vehicle Technology, NASA/Marshall Space Flight Center, Apr. 23–25.
Garcia, R., Griffin, L. W., Benjamin, T. G., Cornelison, J. W., Ruf, J. H., and Williams, R. W., 1995, “Computational Fluid Dynamics Analysis in Support of the Simplex Turbopump Design,” NASA CP-3282, 1 , pp. 462–470.
Griffin,  L. W., and Dorney,  D. J., 2000, “Simulations of the Unsteady Flow Through the Fastrac Supersonic Turbine,” ASME J. Turbomach., 122, pp. 225–233.
Foley,  A. C., and Ivey,  P. C., 1996, “Measurement of Tip-Clearance Flow in a Multistage, Axial Flow Compressor,” ASME J. Turbomach., 118, pp. 211–217.
Suder,  K. L., and Celestina,  M. L., 1996, “Experimental and Computational Investigation of the Tip Clearance Flow in a Transonic Axial Compressor Rotor,” ASME J. Turbomach., 118, pp. 218–229.
Kang,  S., and Hirsch,  C., 1996, “Numerical Simulation of Three-Dimensional Viscous Flow in a Linear Compressor Cascade With Tip Clearance,” ASME J. Turbomach., 118, pp. 492–505.
Chima,  R. V., 1998, “Calculation of Tip Clearance Effects in a Transonic Compressor Rotor,” ASME J. Turbomach., 120, pp. 131–140.
Baldwin, B. S., and Lomax, H., 1978, “Thin Layer Approximation and Algebraic Model for Separated Turbulent Flow,” AIAA Paper No. 78–257.
Roe,  P. L., 1981, “Approximate Riemann Solvers, Parameter Vectors, and Difference Schemes,” J. Comput. Phys., 43, pp. 357–372.
Dorney,  D. J., Davis,  R. L., Edwards,  D. E., and Madavan,  N. K., 1992, “Unsteady Analysis of Hot Streak Migration in a Turbine Stage,” AIAA J. Propul. Power, 8, No. 2, pp. 520–529.
Dorney,  D. J., and Schwab,  J. R., 1996, “Unsteady Numerical Simulations of Radial Temperature Profile Redistribution in a Single-Stage Turbine,” ASME J. Turbomach., 118, pp. 783–791.

Figures

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Midspan section of O–H grid topology for the turbine
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Axial-direction view of the computational grids for the turbine
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Tip clearance grids for the turbine
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Perspective view of the nozzle and rotor grids for the turbine
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Time-averaged entropy contours—50 percent span—Case 1
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Time-averaged entropy contours—50 percent span—Case 2
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Time-averaged entropy contours—75 percent span—Case 1
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Time-averaged entropy contours—75 percent span—Case 2
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Time-averaged entropy contours on rotor S.S.—Case 1
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Time-averaged entropy contours on rotor S.S.— Case 2
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Time-averaged total temperature contours at rotor passage exit—Case 1
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Time-averaged total temperature contours at rotor passage exit—Case 2
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Time-averaged pressure contours—50 percent span—Case 1
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Time-averaged pressure contours—50 percent span—Case 2
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Time-averaged pressure contours—75 percent span—Case 1
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Time-averaged pressure contours—75 percent span—Case 2
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Unsteady pressure history and decomposition—60 percent span leading edge—Case 1—rotor
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Unsteady pressure history and decomposition—60 percent span leading edge—Case 2—rotor
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Unsteady pressure envelope—Case 1—vane; –– min, —– avg, - - - max
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Unsteady pressure envelope—Case 2—vane; –– min, —– avg, - - - max
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Unsteady pressure envelope—Case 1—rotor; –– min, —– avg, - - - max
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Unsteady pressure envelope—Case 2—rotor; –– min, —– avg, - - - max
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Radial profile of circumferentially averaged absolute Mach number—vane exit
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Radial profile of circumferentially averaged absolute Mach number—rotor exit
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Radial profile of circumferentially averaged absolute circumferential flow angle—vane exit
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Radial profile of circumferentially averaged absolute circumferential flow angle—rotor exit
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Radial profile of circumferentially averaged absolute total pressure—vane exit
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Radial profile of circumferentially averaged absolute total pressure—rotor exit
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Radial profile of circumferentially averaged absolute total temperature—vane exit
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Radial profile of circumferentially averaged absolute total temperature—rotor exit

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