Inlet Flow Distortions as a Source of Performance Degradation in Micro-Turbojet Engine Investigated through Experimental Quantification

Micro-Turbojet engines play a crucial role in various aerospace applications, especially in small unmanned aerial vehicles (UAVs), target drones, and experimental aircraft. The overall performance of these engines is highly dependent on the efficiency of their air intake systems. The geometry and configuration of the inlet and duct significantly influence pressure recovery, airflow distortion, and ultimately, the engine’s thrust and fuel efficiency. Among the most critical components affected by these factors is the compressor, which is designed to operate under steady and uniform flow conditions. When subjected to distorted or non-uniform inlet flow, the compressor can suffer from performance degradation, and in severe cases, encounter instability phenomena such as rotating stall and surge.

These challenges highlight the importance of accurately quantifying the effects of inlet flow distortion on engine performance. However, current predictive tools are often insufficient, especially for Micro-Turbojet engines operating in complex or compact airframe environments. There is a clear need for a reliable and experimentally validated method to evaluate performance losses resulting from various inlet conditions.

This seminar presents the development of an experimental approach for a small-scale Micro-Turbojet engine to evaluate the effects of inlet distortions on engine performance. The results aim to support the optimization of air intake design and improve predictive capabilities for engine integration within specific airframes, ultimately contributing to more efficient propulsion systems.