公开(公告)号：US12188359B2

公开(公告)日：2025-01-07

申请号：US18477912

申请日：2023-09-29

Applicant: RTX CORPORATION

Inventor： Daniel S. Rogers ,  James E. Weisheit ,  Morely S. Sherman ,  Mikayla M. Rogers ,  Timothy J. Harding ,  Marshall F. Thayer ,  Joseph Micucci

IPC: F01D11/08 ,  F01D9/04 ,  F01D25/24

Abstract: A gas turbine engine includes a turbine section that has a retainer ring, a first vane that bears against the retainer ring to prevent movement of the first vane in a first axial direction, a second vane axially spaced from the first vane, and a blade axially between the first vane and the second vane. A blade outer air seal is situated radially outwardly of the blade. The blade outer air seal includes a ceramic matrix composite body that defines a core gaspath side that faces the blade, a forward end, an aft end, and circumferential sides. There is a spring seal at the aft end of the blade outer air seal that seals against the second vane. The spring seal provides a preload that biases the blade outer air seal against the first vane and thereby biases the first vane against the retainer ring.

公开(公告)号：US20240110488A1

公开(公告)日：2024-04-04

申请号：US18456787

申请日：2023-08-28

Applicant: RTX CORPORATION

Inventor： Paul M. Lutjen ,  Daniel S. Rogers ,  Timothy J. Harding ,  James E. Weisheit ,  Morely S. Sherman ,  Mikayla M. Rogers ,  Marshall F. Thayer ,  Joseph Micucci

IPC: F01D11/16

CPC classification number: F01D11/16 ,  F05D2240/55 ,  F05D2260/38 ,  F05D2300/6033

Abstract: A gas turbine engine includes a turbine section that has a ceramic matrix composite body that defines a core gaspath side that a row of blades, a forward end, an aft end, and circumferential sides. The forward end abuts at least one vane of a first row of vanes, and the aft end including a seal channel. A compliant seal is disposed in the seal channel and seals against at least one vane of a second row of vanes.

公开(公告)号：US20240110487A1

公开(公告)日：2024-04-04

申请号：US18477912

申请日：2023-09-29

Applicant: RTX CORPORATION

Inventor： Daniel S. Rogers ,  James E. Weisheit ,  Morely S. Sherman ,  Mikayla M. Rogers ,  Timothy J. Harding ,  Marshall F. Thayer ,  Joseph Micucci

IPC: F01D11/08 ,  F01D9/04

CPC classification number: F01D11/08 ,  F01D9/04 ,  F05D2300/6033

Abstract: A gas turbine engine includes a turbine section that has a retainer ring, a first vane that bears against the retainer ring to prevent movement of the first vane in a first axial direction, a second vane axially spaced from the first vane, and a blade axially between the first vane and the second vane. A blade outer air seal is situated radially outwardly of the blade. The blade outer air seal includes a ceramic matrix composite body that defines a core gaspath side that faces the blade, a forward end, an aft end, and circumferential sides. There is a spring seal at the aft end of the blade outer air seal that seals against the second vane. The spring seal provides a preload that biases the blade outer air seal against the first vane and thereby biases the first vane against the retainer ring.