Composite component with damper for gas turbine engine

Patent metadata

Field	Value
Publication number	US-11879351-B2
Application number	US-202117549168-A
Country	US
Kind code	B2
Filing date	Dec 13, 2021
Priority date	Dec 13, 2021
Publication date	Jan 23, 2024
Grant date	Jan 23, 2024

Abstract

An assembly for a gas turbine engine according to an aspect of the present disclosure includes a metallic damper including a first contact surface and a gas turbine engine component. The gas turbine engine component includes a main body extending in a first direction between a gaspath surface and a second contact surface. The first and second contact surfaces oppose each other along an interface extending in a second direction. The first and second contact surfaces are dimensioned to contact each other along the interface in a hot assembly state. The main body is established by a composite including fibers in a matrix material. At least some of the fibers are arranged to establish a plurality of cooling passages aligned with the interface relative to the second direction. A method of damping for a gas turbine engine is also disclosed.

First claim

What is claimed is:

1. An assembly for a gas turbine engine comprising:
at least one metallic damper including a first contact surface; and
a gas turbine engine component comprising:
a main body extending in a first direction between a gaspath surface and a second contact surface;
wherein the first and second contact surfaces oppose each other along an interface extending in a second direction, the first and second contact surfaces are dimensioned to contact each other along the interface in a hot assembly state, and the first and second contact surfaces are spaced apart along the interface in a cold assembly state; and
wherein the main body is established by a composite including fibers in a matrix material, and at least some of the fibers are arranged to establish a plurality of cooling passages aligned with the interface relative to the second direction.

2. The assembly as recited in claim 1 , wherein the at least one damper includes a damper body having a plurality of standoffs dimensioned to establish a set of discrete contact points along the interface in the hot assembly state.

3. The assembly as recited in claim 2 , wherein the plurality of cooling passages are a first set of cooling passages, the at least one damper includes a plurality of recesses interspersed with the standoffs, the recesses establish a second set of cooling passages along the interface bounded by the second contact surface of the gas turbine engine component, the second set of cooling passages are aligned with respective cooling passages of the first set of cooling passages, and the main body of the gas turbine engine component includes a third set of cooling passages aligned with the respective standoffs.

4. The assembly as recited in claim 1 , wherein the fibers include sets of fibers arranged in two-dimensional weaves about the respective cooling passages.

5. The assembly as recited in claim 4 , wherein the fibers are arranged to establish an overwrap that encircles the sets of fibers and the cooling passages.

6. The assembly as recited in claim 1 , wherein the fibers are arranged to establish a three-dimensional weave, and the three-dimensional weave includes segments of fiber that alternate on opposite sides of the cooling passages and crisscross to establish one or more internal walls of the main body between the cooling passages.

7. The assembly as recited in claim 6 , wherein the segments of fiber are arranged such that the respective fiber loops about each one of the cooling passages.

8. The assembly as recited in claim 1 , wherein:
the main body includes a core established by the fibers, the core comprising the cooling passages;
the main body includes a first mounting point and a second mounting point on opposite sides of the core relative to the second direction;
the main body includes a first ply and a second ply extending along opposite sides of the core relative to the first direction to establish the gas path surface and the second contact surface, and the first and second plies are joined together at a first bifurcation and a second bifurcation adjacent to the respective first and second mounting points.

9. The assembly as recited in claim 8 , wherein the gas turbine engine component is dimensioned to be suspended between the first and second mounting points in an installed position.

10. The assembly as recited in claim 8 , wherein:
the at least one damper includes a damper body having a plurality of standoffs, and the plurality of standoffs are dimensioned to establish a set of discrete contact points along the interface in the hot assembly state; and
the gas turbine engine component and the at least one damper cooperate to establish a plurality of cooling paths along the interface between the set of discrete contact points.

11. The assembly as recited in claim 1 , wherein the gas turbine engine component is a turbine component.

12. The assembly as recited in claim 1 , wherein the at least one damper includes a first damper and a second damper opposed to, but spaced apart from, the first damper.

13. A gas turbine engine comprising:
an array of blades rotatable about an engine axis;
an array of vanes adjacent to the array of blades;
an array of blade outer air seals distributed about the array of blades to bound a gas path; and
wherein at least one of the blades, the vanes and the blade outer air seals comprises:
at least one metallic damper including a first contact surface;
a wall including a main body extending between a gaspath surface and a second contact surface, the first and second contact surfaces dimensioned to contact each other along an interface during engine operation, and the first and second contact surfaces are spaced apart along the interface in a cold assembly state; and
wherein the main body is established by a composite including fibers in a matrix material, and at least some of the fibers are arranged to establish a plurality of cooling passages adjacent to the interface.

14. The gas turbine engine as recited in claim 13 , wherein the wall is suspended between first and second mounting points secured to an engine static structure, and the first and second mounting points are spaced apart from and on opposite sides of the interface.

15. The gas turbine engine as recited in claim 14 , wherein:
the wall extends in an axial direction between a leading edge portion and a trailing edge portion, extends in a circumferential direction between first and second mate faces and extends in a radial direction between the second contact surface and the gas path surface relative to the engine axis; and
one of the first and second contact surfaces faces radially outwardly with respect to the radial direction, and another one of the first and second contact surfaces faces radially outwardly with respect to the radial direction.

16. The gas turbine engine as recited in claim 14 , wherein:
the at least one damper includes a damper body having a plurality of standoffs dimensioned to establish a set of discrete contact points along the interface during engine operation; and
the gas turbine engine component and the at least one damper cooperate to establish a plurality of cooling paths along the interface between the set of discrete contact points.

17. The gas turbine engine as recited in claim 13 , wherein the fibers are arranged to establish a three-dimensional weave, and the three-dimensional weave includes segments of fiber arranged along respective periodic paths that alternate on opposite sides of the cooling passages and crisscross to establish one or more internal walls of the main body between the cooling passages.

18. A method of damping for a gas turbine engine comprising:
positioning a gas turbine engine component adjacent to at least one metallic damper, wherein:
the at least one damper includes a first contact surface; and
the gas turbine engine component includes a main body extending between a gaspath surface and a second contact surface, the first and second contact surfaces are spaced apart along the interface in a cold assembly state, and the main body is established by a composite including fibers arranged to establish a plurality of cooling passages aligned with the interface;

damping the gas turbine engine component in response to contact between the first and second contact surfaces along the interface; and
conveying cooling flow through the cooling passages to provide cooling augmentation to a portion of the at least one damper in contact with the gas turbine engine component along the interface.

Assignees

• Raytheon Tech Corp
• Rtx Corp

Inventors

• Kim Russell
• Roach James T

Classifications

• F01D25/28 Primary

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F01D25/04 Primary

  Antivibration arrangements · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F05D2300/6012

  Woven fabrics · CPC title