Gasturbinenmotor mit Fachvereisungsschutzsystem

Details

Veröffentlichungs-Nr.

EP4818490

Anmeldetag

31. März 2026

Veröffentlichung

7. Oktober 2026

Rechtsraum

EP

IPC

F02C6/08, F01D25/02

Abstract

A gas turbine engine is provided that includes a fan section, a compressor section, a combustion section, a turbine section, an annular fan bypass air path, a bleed air structure (54), an annular compartment (64), and an anti-icing system (68). The compressor section has a low (30A) and high (30B) pressure compressor sections. The fan bypass air path is defined by inner (52B) and outer (52A) bypass wall structures. An outer radial boundary structure defines an outer radial boundary of a core gas path within the low pressure compressor section (30A). The bleed air structure is disposable in an open state or in a closed state. The annular compartment (64) is defined by the inner bypass wall structure (52B), the outer radial boundary structure, and a firewall (66). The anti-icing system (68) is disposable in an activated state or in a deactivated state. In the activated state the anti-icing system (68) is configured to mitigate ice accumulation within the annular compartment (64).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA

Fachgebiete