Cmc-Bauteil eines Gasturbinentriebwerks, das einen Teil einer im Wesentlichen Ringförmigen Gasturbinentriebwerksstufe Bildet, und Verfahren zur Verringerung Thermischer Spannung in einem Cmc-Bauteilsegment, das einen Teil einer im Wesentlichen Ringförmigen Stufe eines Gasturbinentriebwerks Bildet

Details

Veröffentlichungs-Nr.

EP4786742

Anmeldetag

30. Januar 2026

Veröffentlichung

5. August 2026

Rechtsraum

EP

Abstract

A ceramic matrix composite (CMC) component (200) of a gas turbine engine forming a portion of a substantially ring-shaped gas turbine engine stage includes an inner surface (210) configured for exposure to a hot gas path of the gas turbine engine and an outer surface (220) on a non-gas path side. An inner heat exchange passage (212) is disposed adjacent to the inner surface (210) of the CMC component at a first radial distance relative to an axis of the gas turbine engine. An outer heat exchange passage (222) is disposed adjacent to the outer surface (220) at a second radial distance relative to an axis of the gas turbine engine greater than the first radial distance. A method of reducing thermal stress in the ceramic matrix composite (CMC) component includes feeding a cold air (214) flow to the inner heat exchange passage (212); and feeding a hot air (224) flow to the outer heat exchange passage (222).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA