EXPERIMENTAL STUDY ON RADIAL COMPRESSOR INSTABILITY CAUSED BY INLET AIRFLOW RESTRICTION

Abstract

This work examines the issue of unstable performance in aircraft turbine engine compressors, focusing on radial compressors. It investigates the causes, mechanisms, and effects of compressor instability, such as airflow pulsations, pressure variations, engine vibrations, and the risk of compressor blade damage. The theoretical section explains how deviations in airflow rate from design specifications can result in flow separation and a transition from laminar to turbulent flow, which may lead to surge and possible reverse airflow.

The analysis of real MPM-20 engine measurements and results for key parameters such as pressures, temperatures, and airflow rates showed significant agreement with models, confirming the theoretical assumptions. These findings underline the crucial role of stable airflow management and effective compressor design in maintaining the safe operation of aircraft engines, especially under varying and extreme flight conditions.