Dichtungsanordnung mit Verteilter Kühlanordnung

Details

Veröffentlichungs-Nr.

EP3865682

Aktenzeichen

EP21156078

Anmeldetag

9. Februar 2021

Veröffentlichung

29. Mai 2024

Erteilung

29. Mai 2024

Rechtsraum

EP

IPC

F01D25/24

Abstract

An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal arc segment (66; 166; 266; 366) that has a sealing portion (72; 372) and a pair of opposed rails extending outwardly from the sealing portion (72; 372). The sealing portion (72; 372) includes a sealing face (72A) dimensioned to bound a core flow path (C) and has a backside face (72C; 172C) opposed to the sealing face (72A). The backside face (72C; 172C) includes a first localized region (LR1), a second localized region (LR2) between the pair of rails, and a third localized region (LR3). A support (68; 168; 268; 368) includes a mounting portion (76) and a first interface portion (78; 178; 374). At least one retention pin (84; 284; 384) is dimensioned to engage the first interface portion (78; 178; 374) of the support (68; 168; 268; 368) and at least one of the pair of rails such that the seal arc segment (66; 166; 266; 366) is carried by the at least one retention pin (84; 284; 384). A support plate (86; 186; 286; 386) is arranged relative to the support (68; 168; 268; 368) such that the at least one retention pin (84; 284; 384) is trapped between the support plate (86; 186; 286; 386) and the support (68; 168; 268; 368). A cooling cavity (96; 196; 296; 396) is established between the support (68; 168; 268; 368), the support plate (86; 186; 286; 386), and the second localized region (LR2). A method of sealing is also disclosed.

Anmelder

Firmen

RTX Corporation
Raytheon Technologies Corporation

Land

🇺🇸 USA

Fachgebiete