Wärmeverwaltungssystem für ein Flugzeugantriebssystem mit Offenem Rotor

Details

Veröffentlichungs-Nr.

EP4733566

Anmeldetag

24. Oktober 2025

Veröffentlichung

29. April 2026

Rechtsraum

EP

IPC

F02C6/20, B64D33/08, F02C7/14

Abstract

A propulsion system (20) for an aircraft includes an open propulsor rotor (38), a turbine engine (32) and a thermal management system (36). The turbine engine (32) includes an engine core (82) and an engine flowpath (76). The engine core (82) includes a compressor section (71), a combustor section (72) and a turbine section (73). The engine flowpath (76) extends longitudinally though the compressor section (71), the combustor section (72) and the turbine section (73) from an airflow inlet (78) into the engine flowpath (76) to a combustion products exhaust (80) from the engine flowpath (76). The thermal management system (36) is configured to manage heat energy generated by the propulsion system (20) during operation of the turbine engine (32). The thermal management system (36) includes an electric boost compressor (114), a heat exchanger (116) and a system flowpath (110) disposed outside of the engine core (82). The system flowpath (110) extends longitudinally through the electric boost compressor (114) and the heat exchanger (116) from an airflow inlet (122) into the system flowpath (110) to an airflow exhaust (124) from the system flowpath (110).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA

Fachgebiete