Recuperated-Cycle-Motor

Details

Veröffentlichungs-Nr.

EP3739184

Aktenzeichen

EP20174487

Anmeldetag

13. Mai 2020

Veröffentlichung

28. Juni 2023

Erteilung

28. Juni 2023

Rechtsraum

EP

IPC

F02C3/073F02C3/14F02C7/08F02K3/068

Abstract

A gas turbine engine (10; 10A) includes a rotatable first shaft (12; 12A), a first disk (20; 20A) connected to the first shaft (12; 12A), a second disk (26; 26A) connected to the first shaft (12; 12A), a combustor (44; 44A) radially outward from the first disk (20; 20A) and the second disk (26; 26A), and a heat exchanger (40; 40A) connected to the combustor (44; 44A) aft of the second disk (26; 26A). The first disk (20; 20A) includes a row of low pressure compressor blades (46; 46A) and a row of high pressure turbine blades (48; 48A) connected to a radially outer end of the row of low pressure compressor blades (46; 46A). The second disk (26; 26A) includes a row of high pressure compressor blades (54; 54A) and a row of low pressure turbine blades (56; 56A) connected to a radially outer end of the row of high pressure compressor blades (54; 54A).

Anmelder

Firmen

RTX Corporation
Raytheon Technologies Corporation

Land

🇺🇸 USA

Fachgebiete