公开(公告)号：US20230035302A1

公开(公告)日：2023-02-02

申请号：US17388228

申请日：2021-07-29

Applicant: General Electric Company

Inventor： Travis J. Packer ,  James Hamilton Grooms ,  David Fasig ,  Richard William Jendrix ,  Scott Alan Schimmels ,  Bradford Alan Tracey ,  Michael Alan Hile ,  Thomas Ryan Wallace

IPC: F01D11/24 ,  F01D9/02

Abstract: A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.

公开(公告)号：US11970946B2

公开(公告)日：2024-04-30

申请号：US17388228

申请日：2021-07-29

Applicant: General Electric Company

Inventor： Travis J. Packer ,  James Hamilton Grooms ,  David Fasig ,  Richard William Jendrix ,  Scott Alan Schimmels ,  Bradford Alan Tracey ,  Michael Alan Hile ,  Thomas Ryan Wallace

IPC: F01D11/24 ,  F01D9/02 ,  F01D25/24

CPC classification number: F01D11/24 ,  F01D9/02 ,  F01D25/243 ,  F05D2240/126 ,  F05D2240/55

Abstract: A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.