Pressure relief arrangement for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11028782-B2
Application number	US-201816124559-A
Country	US
Kind code	B2
Filing date	Sep 7, 2018
Priority date	Oct 12, 2017
Publication date	Jun 8, 2021
Grant date	Jun 8, 2021

Abstract

A pressure relief arrangement for a gas turbine engine comprises a hinged door and a mount. A plastically deformable member is provided between and coupled to the hinged door and the mount. The deformable member is configured to deform between a non-deformed state when the door is in a closed position and an elongated deformed state when the door is in an open position.

First claim

We claim:

1. A gas turbine engine comprising
a pressure relief arrangement pressure relief arrangement including
a hinged door;
a mount; and
a plastically deformable member provided between and coupled to the hinged door and the mount, the deformable member being configured to deform between a non-deformed state when the door is in a closed position and an elongated deformed state when the door is in an open position, wherein the plastically deformable member is coupled to the hinged door via an articulated link.

2. The gas turbine engine according to claim 1 , wherein the articulated link is pivotally connected to the door and to the plastically deformable member, so that the articulated link can pivot between a first position when the door is in the closed position and a second position when the door is in the open position.

3. A gas turbine engine comprising
a pressure relief arrangement pressure relief arrangement including
a hinged door;
a mount; and
a plastically deformable member provided between and coupled to the hinged door and the mount, the deformable member being configured to deform between a non-deformed state when the door is in a closed position and an elongated deformed state when the door is in an open position, wherein the plastically deformable member is made from a plurality of stacked elements, each stacked element extending fully between the opposite ends of the plastically deformable member.

4. The gas turbine engine according to claim 3 , wherein the stacked elements are identical in shape and size, and optionally material.

5. The gas turbine engine according to claim 3 , wherein the stacked elements are cut from sheet or plate.

6. A gas turbine engine comprising
a pressure relief arrangement pressure relief arrangement including
a hinged door;
a mount; and
a plastically deformable member provided between and coupled to the hinged door and the mount, wherein the plastically deformable member comprises one or more bends that deviate from a linear path between opposite ends of the plastically deformable member, the plastically deformable member being configured to deform between a non-deformed state in which the plastically deformable member has a first length measured between the opposite ends of the plastically deformable member in a direction of the linear path when the door is in a closed position and an elongated deformed state in which the one or more bends straighten out and cause the plastically deformable member to plastically deformed and have a second length measured between the opposite ends of the plastically deformable member in the direction of the linear path when the door is in an open position, the second length being greater than the first length.

7. The gas turbine engine according to claim 6 , wherein each of the one or more bends of the plastically deformable member curve through 180°.

8. The gas turbine engine according to claim 6 , wherein the radius of each bend of the one or more bends is at least five times the width of the plastically deformable member measured in a plane parallel to the plane in which the radius of curvature lies.

9. The gas turbine engine according to claim 6 , wherein the one or more bends are asymmetric about a line that extends between the opposite ends of the plastically deformable member.

10. The gas turbine engine according to claim 6 , wherein the one or more bends are symmetric about a line that extends between the opposite ends of the plastically deformable member.

11. The gas turbine engine according to claim 6 , wherein the plastically deformable member is made from a metal.

12. The gas turbine engine according to claim 6 , comprising an engine core, and a casing member surrounding the engine core, and wherein the mount is provided radially internally of the core casing member and the door being arranged to pivot outwardly away from the core.

13. The gas turbine engine according to claim 6 , wherein each of the one or more bends is U-shaped.

14. The gas turbine engine according to claim 6 , wherein the plastically deformable member is pivotably coupled with the hinged door and pivotably coupled with the mount.

15. The gas turbine engine according to claim 6 , wherein the one or more bends comprises alternating convex and concave curves.

16. The gas turbine engine according to claim 6 , wherein the plastically deformable member is made from a plurality of stacked elements, each stacked element extending fully between the opposite ends of the plastically deformable member.

Assignees

• Rolls Royce Plc

Inventors

• Ruston Simon M
• Yang Rong
• Fox Matthew
• Kulkarni Aniket Anand

Classifications

• F02C7/00 Primary

  Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) · CPC title

• F02C9/18 Primary

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title

• F01D21/14

  responsive to other specific conditions · CPC title

• F02K3/06

  with front fan · CPC title