A three-dimensional theory is developed for a linear supersonic cascade moving between parallel walls, vibrating or interacting with an inlet distortion to predict the effect of sound absorbing wall liners on the unsteady aerodynamic forces. A side wall of the model is partially composed of a sound absorbing liner with uniform acoustic admittance, which is assumed to depend on the frequency sensed by the wall liner. The lined section of the wall is confined to the portion swept by blades. The change of the aerodynamic work of the vibrating rotor blades with changes of the cavity depth of the wall liner becomes conspicuous when the wall admittance for the acoustic mode of the least circumferential order is in a certain effective range. The wall liner effect on the intensity of sound generated by interaction with an inlet distortion is larger for downstream propagating waves than for upstream propagating waves.
|Number of pages||9|
|Journal||Transactions of the Japan Society of Mechanical Engineers Series B|
|Publication status||Published - Jan 1 1987|
All Science Journal Classification (ASJC) codes
- Condensed Matter Physics
- Mechanical Engineering