Überdrehzahlschutz für einen Turboverdichter einer Flugzeugtriebwerksanordnung

Details

Veröffentlichungs-Nr.

EP4810781

Anmeldetag

18. März 2026

Veröffentlichung

23. September 2026

Rechtsraum

EP

IPC

F02C6/12

Abstract

A powerplant assembly (24) includes an engine (32), a turbocompressor (34), and an overspeed protection valve (74). The engine (32) includes an air intake (64) and an engine exhaust (68). The turbocompressor (34) includes a compressor section (46), a turbine section (48), and a rotational assembly (50). The rotational assembly (50) includes a turbocompressor shaft (54), a bladed compressor rotor (56) of the compressor section (46), and a turbine rotor (58) of the turbine section (48). The engine (32) and the turbocompressor (34) form a gas flow path (60). The gas flow path (60) extends from the compressor section (46) to the air intake (64), through the engine (32), and from the engine exhaust (68) to the turbine section (48). The overspeed protection valve (74) forms a portion of the gas flow path (60). The overspeed protection valve (74) is positionable in an open state and a closed state.

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada

Fachgebiete