Support assembly for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9896956-B2
Application number	US-201514719634-A
Country	US
Kind code	B2
Filing date	May 22, 2015
Priority date	May 22, 2015
Publication date	Feb 20, 2018
Grant date	Feb 20, 2018

Abstract

A support assembly for a gas turbine engine includes at least one inner support that extends about a circumferential axis and defines a cavity for receiving a control ring. At least one cover plate is attached to at least one inner support to enclose the cavity. At least one of the inner support and the cover plate includes a rail and the other of the inner support and the cover plate includes a groove for engaging the rail.

First claim

What is claimed is:

1. A support assembly for a gas turbine engine comprising:
at least one inner support extending about a circumferential axis defining a cavity for receiving a control ring; and
at least one cover plate attached to the at least one inner support enclosing the cavity, wherein a rail is located on one of the inner support and the cover plate and a groove for engaging the rail is located on the other of the inner support and the cover plate.

2. The assembly of claim 1 , further comprising a control ring located in the cavity extending about the circumferential axis.

3. The assembly of claim 1 , wherein the groove is located in the cover plate and the rail is located on the inner support.

4. The assembly of claim 1 , wherein the groove is located in the inner support and the rail is located on the cover plate.

5. The assembly of claim 1 , wherein at least one of the groove and the rail are located on a hook portion of the at least one cover plate.

6. The assembly of claim 5 , wherein the inner support includes a recess for accepting the hook portion.

7. The assembly of claim 6 , wherein at least one of the groove and the rail is circumferentially offset from the recess.

8. The assembly of claim 7 , wherein a hook accepting groove is at least partially axially aligned with the recess.

9. The assembly of claim 1 , further comprising a blade outer air seal attached to the inner support.

10. The assembly of claim 1 , wherein the at least one cover plate and the at least one inner support are made of materials with similar metal properties.

11. The assembly of claim 1 , wherein the at least one cover plate and the at least one inner support are made of the same material.

12. The assembly of claim 1 , wherein the at least one inner support includes a C-shaped cross section with an opening facing one of an upstream or forward direction.

13. A gas turbine engine comprising:
at least one inner support extending about a circumferential axis defining a cavity for receiving a control ring;
at least one cover plate attached to the at least one inner support enclosing the cavity, wherein a rail is located on at least one of the inner support and a hook portion of the cover plate and a groove for engaging the rail is located on the other of the inner support and the hook portion of the cover plate and the inner support includes a recess for accepting the hook portion; and
a blade outer air seal attached to the inner support.

14. The gas turbine engine of claim 13 , further comprising a control ring located in the cavity extending about the circumferential axis.

15. The gas turbine engine of claim 13 , wherein at least one of the groove and the rail is circumferentially offset from the recess.

16. The gas turbine engine of claim 15 , wherein a hook accepting groove is at least partially axially aligned with the recess.

17. The gas turbine engine of claim 13 , wherein the at least one cover plate and the at least one inner support are made of materials with similar metal properties.

18. The gas turbine engine of claim 13 , wherein the at least one cover plate and the at least one inner support are made of the same material.

Assignees

• United Technologies Corp

Inventors

• Jenkins Decari S
• Bauer Steven J

Classifications

• F01D11/18

  using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F01D11/14 Primary

  Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing (rotors with blades adjustable in operation F01D7/00) · CPC title

• F05D2240/307

  related to the tip of a rotor blade · CPC title