Clearance control assembly

Patent metadata

Field	Value
Publication number	US-11970946-B2
Application number	US-202117388228-A
Country	US
Kind code	B2
Filing date	Jul 29, 2021
Priority date	Jul 29, 2021
Publication date	Apr 30, 2024
Grant date	Apr 30, 2024

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.

First claim

We claim:

1. A clearance control assembly for a gas turbine engine, the gas turbine engine defining an axial direction and a radial direction and including a stage of rotor blades and a shroud hanger, the assembly comprising:
a case defining a first flange and a second flange extending radially outwardly along the radial direction, wherein the first flange defines a forward wall face and an aft wall face and the second flange defines a forward wall face and an aft wall face, wherein the case is configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine, the case further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine; and
a baffle, wherein the baffle extends from the forward wall face of the first flange to the aft wall face of the second flange outward from the case, wherein the baffle, the case, the aft wall face of the first flange, and the forward wall face of the second flange define a chamber therebetween, the baffle having a forward end and an aft end, wherein the forward end of the baffle is engaged with the forward wall face of the first flange to form a first seal, and wherein the aft end of the baffle is engaged with the aft wall face of the second flange to form a second seal,
wherein 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.

2. The assembly of claim 1 , wherein the outlet is positioned aft of the first location and extends through the second flange.

3. The assembly of claim 1 , wherein the first seal comprises a first rope seal element positioned between the forward end of the baffle and the first flange, and wherein the second seal comprises a second rope seal element positioned between the aft end of the baffle and the second flange.

4. The assembly of claim 1 , wherein the shroud hanger has an aft hook that is configured to mate with a corresponding feature of the case, wherein the first location is a location where the aft hook of the shroud hanger mates with the corresponding feature of the case.

5. The assembly of claim 1 , wherein the chamber extends continuously from the forward end of the baffle to the aft end of the baffle.

6. The assembly of claim 1 , wherein the first flange and the second flange are located between the forward end of the baffle and the aft end of the baffle.

7. A gas turbine engine defining an axial direction and a radial direction, the engine comprising:
a compressor section;
a combustion section located downstream of the compressor section; and
a turbine section located downstream of the combustion section, wherein the turbine section includes a stage of rotor blades, a shroud hanger, and a clearance control assembly, the clearance control assembly comprising:
a case defining a first flange and a second flange extending radially outwardly along the radial direction, wherein the first flange defines a forward wall face and an aft wall face, and the second flange defines a forward wall face and an aft wall face, wherein the case is positioned outward along the radial direction from the stage of rotor blades, the case engaged with the shroud hanger at a first location; and
a baffle, wherein the baffle extends from the forward wall face of the first flange to the aft wall face of the second flange positioned outward from the case,

wherein the baffle, the case, the aft wall face of the first flange, and the forward wall face of the second flange form a chamber therebetween, the baffle having a forward end and an aft end, wherein the forward end of the baffle is engaged with the forward wall face of the first flange to form a first seal, wherein the aft end of the baffle is engaged with the aft wall face of the second flange to form a second seal,
wherein the baffle or the case defines an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.

8. The engine of claim 7 , wherein the outlet is positioned aft of the first location and extends through the second.

9. The engine of claim 7 , wherein the first seal comprises a first rope seal element positioned between the forward end of the baffle and the first flange, and wherein the second seal comprises a second rope seal element positioned between the aft end of the baffle and the second flange.

10. The engine of claim 7 , wherein the shroud hanger has an aft hook that is configured to mate with a corresponding feature of the case, the first location being where the aft hook of the shroud hanger mates with the corresponding feature of the case.

11. The engine of claim 7 , wherein the chamber extends continuously from the forward end of the baffle to the aft end of the baffle.

12. The engine of claim 7 , where the flange has a depression located near a root end of the flange.

Assignees

• Gen Electric

Inventors

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

Classifications

• F01D11/24 Primary

  by selectively cooling-heating stator or rotor components · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title

• F05D2240/126

  Baffles or ribs · CPC title

• F05D2240/55

  Seals · CPC title