Adaptiver Motor mit Verstärkungsspule

Details

Veröffentlichungs-Nr.

EP3604784

Aktenzeichen

EP19189434

Anmeldetag

31. Juli 2019

Veröffentlichung

29. Dezember 2021

Erteilung

29. Dezember 2021

Rechtsraum

EP

IPC

F02K3/12F02C3/14F02C6/02F02C3/113

Abstract

A gas turbine engine (10) includes a first spool (14,16), a second spool (12), a primary combustor (70), and a diffuser (68). The first spool (14,16) includes a first compressor (18,24) rotationally driven by a first turbine (20,26) via a first shaft (22,28). The second spool (12) includes a second compressor (74) driven by a second turbine (76) via a second shaft (78). The first compressor (18,24), the diffuser (68), and the primary combustor (70) are arranged in series to provide a compressed airflow discharged from the first compressor (18,24) to the primary combustor (70) via the diffuser (68), which includes walls that diverge towards the primary combustor (70). The second compressor (74) is fluidly coupled to the diffuser (68) to receive at least a portion of the compressed airflow from the diffuser (68). The second turbine (76) is fluidly coupled to the diffuser (68) to discharge an expanded airflow to the diffuser (68).

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete