Aktives System zur Regelung des Schaufelspitzenspiels für Flugzeugtriebwerk

Details

Veröffentlichungs-Nr.

EP4807144

Anmeldetag

26. Februar 2026

Veröffentlichung

16. September 2026

Rechtsraum

EP

Abstract

An aircraft engine (10) includes a gas path annularly extending around a central axis in serial flow communication across a compressor (14) and turbine (18). The turbine (18) has a casing (26), a shroud (32) secured to the casing (26), and blades (28) radially inward of the shroud (32), with a clearance defined between blade tips and the shroud (32). An active tip clearance control device (36) for directing a flow of cooling air to the casing (26) includes a first cooling air source (40) at a first temperature, a second cooling air source (42) at a second temperature than the first temperature, and a valve (46) having a first inlet fluidly connected to the first air source (40), a second inlet fluidly connected to the second air source (42), and an outlet selectively connectible to the first and second inlets. The outlet is fluidly connected to the casing (26) to selectively direct the flow of air from the first or second air source (40, 42) to the casing (26).

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada