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exit flow from a transonic compressor rotorThe three dimensional unsteady flow field behind a transonic compressor rotor with a design pressure ratio of 1.6 at a tip Mach number of 1.2 has been resolved on the blade passing time scale. Quantities determined were total and static pressures, tangential flow angle, and radial flow angle. The spatial and temporal resolution achieved was sufficient to determine velocity components inside individual blade wakes and in the surrounding flow. From these measurements the flow structure is described at stations immediately behind the rotor and one chord downstream. Some dominant features of the flow just behind the rotor are large radial velocity components, large static pressure fluctuations near the blade wakes, and definite unsteadiness (in rotor coordinates) of the wakes. The wake behavior one chord downstream is described in terms of the effect of the strong mean swirl on the behavior of shear disturbances. In the outer portion of the annulus, where the mean flow approximates a solid body rotation, a strong, persistent oscillatory flow is found with 16 periods in the circumference as roughly predicted by theory. In the inner portion of the annulus the disturbances attenuate axially.
Document ID
19760018086
Document Type
Conference Paper
Authors
Thompkins, W. T., Jr.
(Massachusetts Inst. of Tech. Cambridge, MA, United States)
Kerrebrock, J. L.
(Massachusetts Inst. of Tech. Cambridge, MA, United States)
Date Acquired
August 8, 2013
Publication Date
April 1, 1976
Publication Information
Publication: AGARD Unsteady Phenomena in Turbomachinery
Subject Category
AERODYNAMICS
Funding Number(s)
CONTRACT_GRANT: NGR-22-009-383
Distribution Limits
Public
Copyright
Other

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