Überkritischer CO2-Zyklus für Gasturbinenmotoren unter Verwendung eines Partiellen Kernabgasstroms

Details

Veröffentlichungs-Nr.

EP3851652

Aktenzeichen

EP21151918

Anmeldetag

15. Januar 2021

Veröffentlichung

27. Dezember 2023

Erteilung

27. Dezember 2023

Rechtsraum

EP

IPC

F02C1/10F02C6/18F02K3/06F02K3/115

Abstract

A gas turbine engine (400) includes a compressor section, a combustor section, a turbine section, a nozzle section, and the compressor section, the combustor section, the turbine section, and the nozzle section define a core flow path that expels through the nozzle section. The gas turbine engine further includes a waste heat recovery system (402) including a heat recovery heat exchanger (432) arranged at the nozzle section, wherein the heat recovery heat exchanger (432) is arranged within the nozzle section such that the heat recovery heat exchanger (432) occupies less than an entire area of an exhaust area (548) of the nozzle section and a heat rejection heat exchanger (428) arranged to reduce a temperature of a working fluid of the waste heat recovery system (402).

Anmelder

Firmen

RTX Corporation
Raytheon Technologies Corporation

Land

🇺🇸 USA

Fachgebiete