Transients in Turbocompressors
Abstract
Designers of axial flow jet engine compressors have achieved substantial gains in both pressure rise per stage and in reducing irreversible losses through years of analysis and development testing under nearly steady flow conditions. Non-steady inlet flow conditions produced by a number of aircraft operations have, however, continued to challenge the industry with problems of transient flows for which basic understanding is largely absent. In particular the phenomenon of transient rotating stall within individual compressor stages remains an unsolved problem. Observations indicate that distorted inlet flows generate transient instabilities that at least produce losses and may grow to significant compressor stall. It is important to decrease sensitivity to the effects of inlet distortion without reducing performance during steady operation. Dual goals are, therefore, to design engines having reduced likelihood of incurring transient stall and also the ability to rapidly clear any stall that arises and then return to normal operation. (kt)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 31, 1981
- Accession Number
- ADA215030
Entities
People
- J. N. Perkins
- L. G. Lee
- W. C. Griffith
- W. H. Hall
Organizations
- North Carolina State University