Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages II : preliminary analysis of over-all performance

Abstract

Report presenting an investigation of the overall performance of a 20-inch-tip-diameter, eight-stage axial-flow compressor conducted as the initial step in an investigation of the problems encountered in a high-pressure-ratio axial-flow compressor with transonic inlet stages. The investigation was made over a range of weight flows at equivalent speeds from 30 to 100 percent of design speed. Results regarding the overall performance, stage performance, comparison with design, and engine application are provided.