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Task I: A Computational Model for Short Wavelength Stall Inception and Development In Multi-Stage CompressorsA computational model is presented for simulating axial compressor stall inception and development via disturbances with length scales on the order of several (typically about three) blade pitches. The model was designed for multi-stage compressors in which stall is initiated by these short wavelength disturbances, also referred to as spikes. The inception process described is fundamentally nonlinear, in contrast to the essentially linear behavior seen in so-called modal stall inception . The model was able to capture the following experimentally observed phenomena: (1) development of rotating stall via short wavelength disturbances, (2) formation and evolution of localized short wavelength stall cells in the first stage of a mismatched compressor, (3) the switch from long to short wavelength stall inception resulting from the re-staggering of the inlet guide vane, (4) the occurrence of rotating stall inception on the negatively sloped portion of the compressor characteristic. Parametric investigations indicated that (1) short wavelength disturbances were supported by the rotor blade row, (2) the disturbance strength was attenuated within the stators, and (3) the reduction of inter-blade row gaps can suppress the growth of short wavelength disturbances. It is argued that each local component group (rotor plus neighboring stators) has its own instability point (i.e. conditions at which disturbances are sustained) for short wavelength disturbances, with the instability point for the compressor set by the most unstable component group.
Document ID
20030067317
Acquisition Source
Headquarters
Document Type
Other
Authors
Suder, Kenneth
(NASA Glenn Research Center Cleveland, OH, United States)
Tan, Choon-Sooi
(Massachusetts Inst. of Tech. Cambridge, MA, United States)
Date Acquired
September 7, 2013
Publication Date
May 1, 2003
Publication Information
Publication: Three-dimensional Aerodynamic Instability in Multi-stage Axial Compressors
Subject Category
Aircraft Propulsion And Power
Funding Number(s)
CONTRACT_GRANT: NAG3-2101
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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