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Recommendations for Achieving Accurate Numerical Simulation of Tip Clearance Flows in Transonic Compressor RotorsThe tip clearance flows of transonic compressor rotors are important because they have a significant impact on rotor and stage performance. While numerical simulations of these flows are quite sophisticated. they are seldom verified through rigorous comparisons of numerical and measured data because these kinds of measurements are rare in the detail necessary to be useful in high-speed machines. In this paper we compare measured tip clearance flow details (e.g. trajectory and radial extent) with corresponding data obtained from a numerical simulation. Recommendations for achieving accurate numerical simulation of tip clearance flows are presented based on this comparison. Laser Doppler Velocimeter (LDV) measurements acquired in a transonic compressor rotor, NASA Rotor 35, are used. The tip clearance flow field of this transonic rotor was simulated using a Navier-Stokes turbomachinery solver that incorporates an advanced k-epsilon turbulence model derived for flows that are not in local equilibrium. Comparison between measured and simulated results indicates that simulation accuracy is primarily dependent upon the ability of the numerical code to resolve important details of a wall-bounded shear layer formed by the relative motion between the over-tip leakage flow and the shroud wall. A simple method is presented for determining the strength of this shear layer.
Document ID
20000121217
Acquisition Source
Glenn Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
VanZante, Dale E. (NASA Glenn Research Center Cleveland, OH United States)
Strazisar, Anthony J. (NASA Glenn Research Center Cleveland, OH United States)
Wood, Jerry R, (NASA Glenn Research Center Cleveland, OH United States)
Hathaway, Michael D. (Army Research Lab. Cleveland, OH United States)
Okiishi, Theodore H. (Iowa State Univ. of Science and Technology Ames, IA United States)
Date Acquired
September 7, 2013
Publication Date
September 1, 2000
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA/TM-2000-210347
NAS 1.15:210347
E-12395
Meeting Information
Meeting: International Gas Turbine Institute Exposition
Location: Indianapolis, IN
Country: United States
Start Date: July 7, 1999
End Date: July 10, 1999
Sponsors: American Society of Mechanical Engineers
Funding Number(s)
PROJECT: RTOP 523-26-33
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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