Kühlanordnung für Motorkomponenten

Details

Veröffentlichungs-Nr.

EP3557001

Aktenzeichen

EP19169810

Anmeldetag

17. April 2019

Veröffentlichung

31. März 2021

Erteilung

31. März 2021

Rechtsraum

EP

IPC

F01D9/04F01D5/18F01D11/00

Abstract

A gas turbine engine (10) includes a first vane (328a-1) of a turbine section (221), a second vane (328b-1) of the turbine section (221), an impingement plate (352) that includes a first impingement hole (352a) and a second impingement hole (352a), and a pipe that supplies a fluid. The first vane (328a-1) includes a first platform (232-1). The second vane (328b-1) includes a second platform (232-1) and a baffle (356b-1). A first portion of the fluid (352b) traverses the first impingement hole (352a) and impinges on a first surface (408a) of the first platform (232-1). A second portion of the fluid (352b) traverses the second impingement hole (352a) and impinges on a second surface (408b) of the second platform (232-1). A third portion of the fluid (356a) bypasses the impingement plate (352) and enters the baffle (356b-1).

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete