Performance Assessment of an Engine-Integrated Closed-Air Cooling Thermal Management System in a Next Generation Fighter Configuration

Abstract

The increasing integration of high-performance electronics into supersonic aircraft introduces a significant thermal challenge for aviation engineers. Future fighter aircraft are expected to manage heat in the megawatt range. This necessitates the implementation of an efficient thermal management system (TMS) capable of intelligent heat dissipation through the utilization of multiple heat sinks. This paper investigates an engine-integrated TMS that utilizes engine airflow for heat dissipation. A closed-air reverse Brayton cycle is analyzed where heat is transferred from a coolant to the engine bypass flow. However, the operation of such a refrigeration cycle affects engine performance. For instance, it requires additional power from the engine, and the increased system mass necessitates a higher thrust demand. This study aims to analyze the trade-offs between cooling capacity and engine performance through an off-design analysis of a fighter configuration developed at the German Aerospace Center (DLR). By presenting the study results, the aim is to elucidate the interrelations, benefits, and disadvantages, providing a comprehensive understanding of an engine-integrated closed-air cooling TMS. The knowledge gained can be used in future studies to conduct architectural assessments and further enhance the efficiency and potential of engine TMS solutions.