Turbinenmotor mit Massenabweisung

Details

Veröffentlichungs-Nr.

EP4227513

Aktenzeichen

EP23156406

Anmeldetag

13. Februar 2023

Veröffentlichung

10. Dezember 2025

Erteilung

10. Dezember 2025

Rechtsraum

EP

IPC

F02C3/22F02C3/30F02C6/00F02C6/18F02C7/141F02C7/224

Abstract

Aircraft engines include a turbine engine (400) comprising a compressor section (404), a burner section (406), and a turbine section (408) arranged along a shaft (420), with a core flow path (420) through the turbine engine (400) such that exhaust from the burner section (406) passes through the turbine section (408), a condensing assembly (416) arranged downstream of the turbine section (408) of the turbine engine (400) along the core flow path (420), and an exhaust compressor (432) arranged downstream of the condensing assembly (416) along the core flow path (420). The condensing assembly (416) is configured to reduce a mass flow of the exhaust compressor (432) by condensing water vapor from the core flow (420) and removing liquid water from the core flow.

Anmelder

Firmen

RTX Corporation
Raytheon Technologies Corporation

Land

🇺🇸 USA

Fachgebiete