Verdichterzapfschlitzdiffusor

Details

Veröffentlichungs-Nr.

EP4782670

Anmeldetag

23. Januar 2026

Veröffentlichung

29. Juli 2026

Rechtsraum

EP

IPC

F02C3/08, F02C6/08, F02C9/18

Abstract

Gas turbine engines include an engine core defining an engine axis and having compressor section (300), combustor, and turbine sections arranged along the engine axis. A core flow path is defined through the sections of the engine core. A casing (302) of the compressor section (300) defines, in part, a portion of the core flow path, with a bleed air cavity (310) defined between the casing (302) of the compressor section (300) and an engine housing (312). An impeller (308) is arranged between the compressor (300) and combustor sections, the impeller (308) include an impeller shroud (316). A bleed aperture (314) is defined axially between the casing (302) and the impeller shroud (316) with a bleed flow extension (324) extending from the casing (302) and into the bleed air cavity (310) and a diffuser channel (322) is defined between a surface of the bleed flow extension (324) and a surface of the impeller shroud (316), with the diffuser channel (322) having an inlet area that is less than an outlet area.

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada

Fachgebiete