Title page for ETD etd-08132003-111548


Type of Document Master's Thesis
Author Kempf, Severin Gabriel
Author's Email Address skempf@vt.edu
URN etd-08132003-111548
Title Numerical Study of the Stability of Embedded Supersonic Compressor Stages
Degree Master of Science
Department Mechanical Engineering
Advisory Committee
Advisor Name Title
Ng, Fai Committee Chair
Dancey, Clinton L. Committee Member
King, Peter S. Committee Member
Keywords
  • supersonic
  • highly-loaded
  • transoinc
  • compressor
  • shock-structure
Date of Defense 2003-07-21
Availability unrestricted
Abstract
A numerical case study of a multistage compressor with relative supersonic rotors is presented. The purpose of the investigation was to determine the flow instability mechanism of the UEET compressor and its relation to the rotor shock structure in the relative velocity reference frame. The computational study was conducted with the NASA code ADPAC , utilizing the mixing-plane assumption for the boundary condition between adjacent, relatively-rotating blade rows. A steady, five-blade-row, numerical simulation using the Baldwin-Lomax turbulence model was performed, creating several constant speed lines. The results are presented, highlighting the role shock structure plays in the stability of the compressor. The shock structure in the downstream rotor isolates the upstream rotor from the exit conditions until the shock detaches from the leading edge. At this point the shock structure in the upstream rotor moves, changing the conditions for the downstream rotor. This continues with increasing pressure at the exit until the shock in the upstream rotor detaches from the leading edge. This event causes an instantaneous drop in the mass flow rate, initiating positive incident separation on the suction side of stator-two.
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