Radialabblasventil für Gasturbinenkompressor

Details

Veröffentlichungs-Nr.

EP3907389

Aktenzeichen

EP21172406

Anmeldetag

6. Mai 2021

Veröffentlichung

25. Juni 2025

Erteilung

25. Juni 2025

Rechtsraum

EP

IPC

F02C6/08F04D27/02

Abstract

A bleed system of a gas turbine engine (20) includes a bleed duct (66) having a duct inlet (70) located at a flowpath of a gas turbine engine (20), and a bleed outlet (72) located outside of the flowpath, and extending circumferentially around a central longitudinal axis. A plurality of bleed doors (86) are located at the bleed outlet (72) and are arrayed along a circumferential length on the bleed duct (66). Each bleed door (86) includes a first circumferential end (92), and a second circumferential end (94). The bleed doors (86) are arrayed such that when the bleed doors (86) are in a closed position the first circumferential end (92) is located at the second circumferential end (94) of an adjacent bleed door (86) of the bleed doors (86). Each bleed door (86) includes a pivot (104), such that each bleed door (86) rotates about the pivot (104) from the closed position covering the duct outlet (72) to an opened position allowing a bleed airflow to pass through the duct outlet (72).

Anmelder

Firmen

RTX Corporation
Raytheon Technologies Corporation

Land

🇺🇸 USA

Fachgebiete