Gust response decomposition in a stator/rotor axial compressor with varying axial gap
Journal
Journal of Propulsion and Power
Journal Volume
13
Journal Issue
2
Pages
178-185
Date Issued
1997
Author(s)
Abstract
The objective of this paper is to decompose the unsteady force on the rotor of a stator/rotor axial compressor into vortical and potential contributions, for axial gaps of 10, 20, and 30% chord between blade rows. Three methods of decomposition are proposed. The final method adopted requires two steps. First, the potential contributed gust within the gap region is found using a panel code for stator/rotor configuration and the vortical contributed gust from the difference between that calculated by a Navier-Stokes code and the potential gust. Second, the rotor gust response is decomposed using the Navier-Stokes code in the rotor cascade configuration, with the vortical and potential disturbances as separate inlet boundary conditions. Results show that the rotor gust response caused by vortical contribution is dominant when the upstream wake impinges upon the rotor leading edge. The rotor gust response caused by potential contribution reaches an extremum when the stator trailing edge is closest to the rotor leading edge. Both vortical and potential contributions are important to determine the total blade response when the axial gap is less than about 30% of the chord.
SDGs
Type
journal article