Gasturbinenmotor mit Kühlung durch Transkritischen Dampfzyklus

Details

Veröffentlichungs-Nr.

EP3296665

Aktenzeichen

EP17191939

Anmeldetag

19. September 2017

Veröffentlichung

4. September 2019

Erteilung

4. September 2019

Rechtsraum

EP

IPC

F25B9/00F25B9/06F02C3/04F02C7/18F02C7/22F02C7/224F25B40/02

Abstract

A gas turbine engine (20) has a compressor section (24), a combustor (56), and a turbine section (28). An associated fluid is to be cooled and an associated fluid is to be heated. A transcritical vapor cycle (185; 234; 240) heats the fluid to be heated, and cools the fluid to be cooled. The transcritical vapor cycle (185; 234; 240) includes a gas cooler (165; 246) in which the fluid to be heated is heated by a refrigerant in the transcritical vapor cycle (185; 234; 240). An evaporator heat exchanger (174; 254) at which the fluid to be cooled is cooled by the refrigerant in the transcritical vapor cycle (185; 234; 240). A compressor (188; 242) upstream of the gas cooler (165; 246) compresses the refrigerant to a pressure above a critical point (160) for the refrigerant. An expansion device (194; 248) expands the refrigerant downstream of the gas cooler (165; 246), with the evaporator heat exchanger (174; 254) being downstream of the expansion device (194; 248), and such that the refrigerant passing through the gas cooler (165; 246) to heat the fluid to be heated is generally above the critical point (160).

Anmelder

Firma

United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete