Verdichterzapfluftanschluss mit Hohlraumeinlassdraht

Details

Veröffentlichungs-Nr.

EP4722497

Anmeldetag

30. September 2025

Veröffentlichung

8. April 2026

Rechtsraum

EP

IPC

F01D5/10, F01D5/22, F01D11/08

Abstract

A compressor assembly (44) of a gas turbine engine includes: a case (100) surrounding a core; a row of stator blades (112) within the case, wherein the row of stator blades has first shrouds (114); a row of rotor blades (132) within the case and adjacent to the row of stator blades, wherein the row of rotor blades has second shrouds (134). The first shrouds define first mate faces (118) that axially face the second shrouds, and the second shrouds define second mate faces (138) that axially face the first shrouds. A bleed port groove (150) is defined between the first mate faces and the second mate faces. A bleed port (155) is defined along the bleed port groove, a bleed cavity (160) is defined in the case. The bleed cavity is exterior to the first shrouds and the second shrouds, and fluidly coupled to the core via the bleed port. A circumferentially extending first wire (170) is secured within the bleed port groove.

Anmelder

Firma

PRATT & WHITNEY CANADA CORP.

Land

🇨🇦 Kanada