Antriebssysteme für Flugzeuge

Details

Veröffentlichungs-Nr.

EP4137686

Aktenzeichen

EP22190642

Anmeldetag

16. August 2022

Veröffentlichung

16. April 2025

Erteilung

16. April 2025

Rechtsraum

EP

IPC

F02C1/10F02K3/06F02C1/04F02C3/22F02C6/20F02C7/10F02C7/224F02C7/36

Abstract

Aircraft propulsion systems (200; 300; 400; 500) including a closed loop-supercritical fluid system (216; 316; 426; 526) having a turbine (214; 314; 428; 528), a cooler heat exchanger (224; 324; 432; 532), a compressor (226; 326; 434; 534), and a recovery heat exchanger (228; 328; 422; 522) arranged along a closed-loop flow path (220; 320; 406; 506) of a supercritical fluid. A shaft (212; 312; 436; 536) is operably coupled to the turbine (214; 314; 428; 528) and configured to be rotationally driven by the turbine (214; 314; 428; 528). A fan (204; 304; 410; 510) is configured to generate thrust, the fan (204; 304; 410; 510) operably coupled to the shaft (212; 312; 436; 536) to be rotationally driven by the shaft (212; 312; 436; 536). A burner (206; 306; 418; 518) is configured to combust a fuel and air from the fan (204; 304; 410; 510) to generate a combusted gas and supply said combusted gas to the recovery heat exchanger (228; 328; 422; 522) of the closed loop-supercritical fluid system (216; 316; 426; 526) and out an exhaust nozzle (210; 310; 424; 524).

Anmelder

Firmen

RTX Corporation
Raytheon Technologies Corporation

Land

🇺🇸 USA

Fachgebiete