Optimization of blade angles of a nine-stage version of a high-pressure compressor of a supersonic passenger aircraft engine.

The choice of the type and configuration of the engine, as well as ensuring its coordinated operation in critical modes to minimize thrust losses, have a significant impact on the fuel-economic and environmental performance of a high-speed passenger aircraft. Research work in this area is aimed at developing and improving the methodology for forming layouts and assessing the aerodynamic, flight performance, and economic characteristics of supersonic passenger aircraft with an acceptable level of fuel efficiency, high flight safety, and low levels of sonic boom and noise. In the field of aircraft engine building, using modeling methods, it is necessary to provide a lead vector for the formation of a scientific and technical reserve for creating competitive engines in the shortest possible time. This paper presents the results of optimization of HPC blade angles and a variant of the engine with a constant high-pressure turbine is formed. [ABSTRACT FROM AUTHOR]