Kühlplattenbolzen für Brennkammer

Details

Veröffentlichungs-Nr.

EP3677838

Aktenzeichen

EP20150393

Anmeldetag

6. Januar 2020

Veröffentlichung

29. Dezember 2021

Erteilung

29. Dezember 2021

Rechtsraum

EP

IPC

F23R3/00F23R3/60

Abstract

A combustor liner for a gas turbine engine, the combustor liner including a panel (150) configured to at least partially define a combustion chamber (128). The combustor liner further includes a shell (152) configured to mount to the panel (150) and form a gap (205) between the panel (150) and the shell (152). The panel includes a stud (200) and a plurality of a stand-off pins (204) proximate to the stud (200) defining a cavity (210) therebetween. The shell (152) includes a plurality of angled impingement holes (208) located away from the cavity (210) but extending through the shell (152) at an orientation such that cooling air passing through the angled impingement holes (208) is directed towards the cavity (210) between adjacent stand-off pins (204) and at an acute angle relative to the stud (200).

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete