Propulsion System Flow Stability Program (Dynamic). Part XI. Lift Engine Compressor Tests and Response to Steady-State Distortion.
Abstract
A four-stage lift engine type compressor was tested over its complete operating range with and without combined circumferential and radial distortion of inlet total pressure. The compressor rig was equipped with interstage instrumentation at each rotor exit and the test procedure was such that a circumferential and radial survey of interstage data were obtained at each test point. Analysis of the data showed that interstage flow mixing and distortion attenuation was related to the slope of the characteristics of the individual stages. Detailed observations of the interstage data are presented which provide considerable insight into distorted compressor operation. A simple analytical procedure to describe compressor events is proposed. Recommendations are made for additional analytical and empirical investigations to corroborate the analysis and conclusions. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1968
- Accession Number
- AD0503303
Entities
People
- James A. Korn