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Aerodynamics of a Transitioning Turbine Stator Over a Range of Reynolds NumbersMidspan aerodynamic measurements for a three vane-four passage linear turbine vane cascade are given. The vane axial chord was 4.45 cm. Surface pressures and loss coefficients were measured at exit Mach numbers of 0.3, 0.7, and 0.9. Reynolds number was varied by a factor of six at the two highest Mach numbers, and by a factor of ten at the lowest Mach number. Measurements were made with and without a turbulence grid. Inlet turbulence intensities were less than I% and greater than IO%. Length scales were also measured. Pressurized air fed the test section, and exited to a low pressure exhaust system. Maximum inlet pressure was two atmospheres. The minimum inlet pressure for an exit Mach number of 0.9 was one-third of an atmosphere, and at a Mach number of 0.3, the minimum pressure was half this value. The purpose of the test was to provide data for verification of turbine vane aerodynamic analyses, especially at low Reynolds numbers. Predictions obtained using a Navier-Stokes analysis with an algebraic turbulence model are also given.
Document ID
19980218604
Document Type
Reprint (Version printed in journal)
Authors
Boyle, R. J. (NASA Lewis Research Center Cleveland, OH United States)
Lucci, B. L. (NASA Lewis Research Center Cleveland, OH United States)
Verhoff, V. G. (NASA Lewis Research Center Cleveland, OH United States)
Camperchioli, W. P. (NASA Lewis Research Center Cleveland, OH United States)
La, H. (NASA Lewis Research Center Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1998
Subject Category
Fluid Mechanics and Heat Transfer
Report/Patent Number
NASA/TM-1998-208408
E-11243
NAS 1.15:208408
Rept-98-GT-285
Meeting Information
Turbo(Stockholm)
Funding Number(s)
PROJECT: RTOP 523-26-13
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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