Shroud segment retainer

Patent metadata

Field	Value
Publication number	US-10012111-B2
Application number	US-201514844769-A
Country	US
Kind code	B2
Filing date	Sep 3, 2015
Priority date	Sep 26, 2014
Publication date	Jul 3, 2018
Grant date	Jul 3, 2018

Abstract

A gas turbine, including: axially adjacent first and second components each having a gas path facing surface within an engine casing, inter-component cavity located between first and second components on the gas path outboard side, an axial-restrictor within the inter component cavity for restricting movement of the first or second component relative to at least one other first and second component or engine casing, wherein the axial-restrictor is radially located in the engine casing or other first and second component and includes a radially facing surface; a retaining element, including a body having circumferential length extending around the gas turbine engine and axial length extending between axially adjacent first and second components when in use; an obstructing portion between the radially facing surface of the axial-restrictor and opposing second radial surface of the other first or second component or engine casing to restrict radial movement of in use axial-restrictor.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
axially adjacent first and second components each having a main gas path facing surface within an engine casing,
an inter component cavity located between the first and second components on an outboard side of a main gas path;
an axial restrictor located within the inter component cavity for axially restricting movement of the first component relative to either of the second component or the engine casing, wherein the axial restrictor is radially located in the engine casing or the second component and includes a radially facing surface; and
a retaining element, comprising:
a main body having a circumferential length extending around the gas turbine engine and an axial length which extends between the axially adjacent first and second components when in use; and
an obstructing portion located between the radially facing surface of the axial restrictor and an opposing second radial surface of the second component or the engine casing, so as to restrict the radial movement of the axial restrictor, in use,

wherein the axial restrictor is separate from the engine casing and has a radial component which is received within a corresponding slot in the engine casing to provide an axial facing surface which abuts the first component or the second component to provide a shear axial restraint for the first component or the second component.

2. The turbine engine according to claim 1 , wherein the main body includes one or more corrugations along the axial length thereof.

3. The turbine engine as claimed in claim 2 , wherein the one or more corrugations include one or more flat-topped peaks or troughs.

4. The gas turbine engine as claimed in claim 2 , wherein the obstructing portion is provided by a peak or trough of one of the one or more corrugations.

5. The gas turbine engine as claimed in claim 2 , wherein the obstructing portion includes an axially extending platform to provide a radially facing obstruction against which the axial restrictor can rest in use, wherein the platform is provided on a corrugation of the one or more corrugations.

6. The gas turbine engine as claimed in claim 1 , wherein the main body includes a plurality of openings to allow air to flow through the retaining element.

7. The gas turbine engine as claimed in claim 1 , in which the retaining element further comprises an anti-fret portion which includes a limb which extends from the main body and is frictionally engaged between either or both of the first and second component and engine casing.

8. The gas turbine engine as claimed in claim 7 in which the retaining element is axially and radially restrained by the anti-fret portion.

9. The gas turbine engine as claimed in claim 1 further comprising a sealing element which is located between the first and second component within a sealing cavity, wherein the retaining element bounds one side of the sealing cavity.

10. The gas turbine engine as claimed in claim 1 , wherein the retaining element is an assembly of parts comprising one or more of the main body, platform and anti-fret portion.

11. The gas turbine engine as claimed in claim 10 , wherein the platform is one of the assembled parts and defines the axial extent of the retaining element at one end thereof.

12. A retaining element for radially locating an axial restrictor in a gas turbine engine, the retaining element comprising:
a main body having a circumferential length extending around the gas turbine engine and an axial length which extends between axially adjacent first and second components when in use; and
an obstructing portion located between a radially facing surface of the axial restrictor and an opposing second radial surface of the second component or an engine casing, so as to restrict the radial movement of the axial restrictor, in use,
wherein the main body includes one or more corrugations along the axial length thereof, and
wherein the obstructing portion includes an axially extending platform to provide a radially facing obstruction against which the axial restrictor can rest in use, wherein the platform is provided on a flat topped peak of a corrugation of the one or more corrugations.

13. The retaining element as claimed in claim 12 , wherein the main body includes a plurality of openings to allow air to flow through the retaining element.

14. The retaining element as claimed in claim 12 , in which the retaining element further comprises an anti-fret portion which includes a limb which extends from the main body and is frictionally engaged between either or both of the first and second component and engine casing.

15. The retaining element as claimed in claim 14 in which the retaining element is axially and radially restrained by the anti-fret portion.

Assignees

• Rolls Royce Plc

Inventors

• Hurst Andrew James
• Simms Mark John

Classifications

• F01D9/02

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

• F05D2240/11

  Shroud seal segments · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F05D2240/10

  Stators · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title