Effect of Inlet Distortion on Performance of a Compressor Stage. Part I. Pneumatic Data.
Abstract
An experimental investigation into the effects of inlet distortion on an isolated turbomachine rotor was conducted. The data obtained from pneumatic instrumentation was analyzed to gain insight into both the overall stage performance and the flow field of an individual rotor blade. The results indicate that the unsteadiness introduced by the distortion increases blade normal force and stage pressure rise. While undergoing inlet distortion, it was found that the rotor does not locally follow the undistorted pressure loss characteristic. Entry into rotating stall results in an abrupt decrease in the stage pressure rise. A definite hysteresis loop is evident for the stalling and unstalling of the rotor. A more complete understanding of the inlet distortion and rotating stall phenomena requires unsteady measurements which will be discussed in a subsequent report. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1977
- Accession Number
- ADA046055
Entities
People
- F. O. Carta
- J. N. Perkins
- L. W. Hardin
- W. C. Griffith
Organizations
- North Carolina State University