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Shock structure measured in a transonic fan using laser anemometryShock structure measurements acquired in a low aspect ratio transonic fan rotor are presented and analyzed. The rotor aspect ratio is 1.56 and the design tip relative Mach number is 1.38. The rotor flowfield was surveyed at near maximum efficiency and near stall operating conditions. Intra-blade velocity measurements acquired with a laser fringe anemometer on blade-to-blade planes in the supersonic region from 10 to 60 percent span are presented. The three-dimensional shock surface determined from the velocity measurments is used to determine the shock surface normal Mach number in order to properly calculate the ideal shock jump conditions. The ideal jump conditions are calculated based upon the Mach numbers measured on a surface of revolution and based upon the normal Mach number to indicate the importance of accounting for shock three dimensionality in turbomachinery design. Comparison of the shock locations with those predicted by a 3-D Euler code showed very good agreement and indicated the usefulness of integrating computational and experimental work to enhance the understanding of the flow physics occurring in transonic turbomachinery passages.
Document ID
19870012496
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wood, Jerry R.
(NASA Lewis Research Center Cleveland, OH, United States)
Strazisar, Anthony J.
(NASA Lewis Research Center Cleveland, OH, United States)
Simonyi, P. Susan
(Sverdrup Technology, Inc. Middleburg Heights, Ohio., United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1987
Publication Information
Publication: AGARD Transonic and Supersonic Phenomena in Turbomachines
Subject Category
Aircraft Propulsion And Power
Accession Number
87N21929
Distribution Limits
Public
Copyright
Other
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