Montagesysteme und -Verfahren für Brennkammerplatten

Details

Veröffentlichungs-Nr.

EP3388746

Aktenzeichen

EP18166994

Anmeldetag

12. April 2018

Veröffentlichung

31. März 2021

Erteilung

31. März 2021

Rechtsraum

EP

IPC

F23R3/00

Abstract

Combustors of gas turbine engines having a combustor shell (330; 430; 530; 630; 730; 830; 930; 1030) having a first end (342; 942) and a second end (344; 1044) opposite the first end, a first securing element (346; 946) positioned at the first end of the combustor shell, a second securing element (348; 1048) positioned at the second end of the combustor shell, a plurality of high temperature material panels (340; 440; 540; 640; 740; 840; 940; 1040) fixedly secured by the first securing element (346; 946) at the first end (342; 942) and the second securing element (348; 1048) at the second, wherein a panel gap (454; 554; 654) is formed between edges of adjacent high temperature material panels of the plurality of high temperature material panels, and a seal divider (450; 550; 650) extending from the first end (342; 942) to the second end (344; 1044) and positioned on the combustor shell and arranged to seal the panel gap (454; 554; 654) between adjacent first and second high temperature material panels.

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete