Non-uniform flow in multistage axial compressors

This paper examines a specific example of distorted inlet flow through the two-dimensional annulus of a multistage compressor which can be solved completely. It is shown that the essential features of this exact solution, including stall, may be described by a two-parameter family of profiles and that an integral technique, utilizing these elementary profiles, will yield essentially the same results. While it is not clear that comparable success would hold for the three-diminsional problem, the results confirm the contention that the two-dimensional problem may be treated with acceptable accuracy by an integral technique.