The aim of this paper is to contribute to the growing subject of inlet/engine compatibility a discussion of some of the more interesting results of research and development testing of rig compressors and engines carried out at the Bristol Engine Division of Rolls-Royce (1971) Ltd, and to discuss these against a now extensive background literature.
The effects of an inlet system on an axial flow gas turbine are principally on performance, stability and mechanical integrity. In this paper attention is focused on the effects of total pressure distortion on the compressor system's performance and stability.