Double box composite seal assembly with insert for gas turbine engine

Patent metadata

Field	Value
Publication number	US-11732597-B2
Application number	US-202117543799-A
Country	US
Kind code	B2
Filing date	Dec 7, 2021
Priority date	Sep 26, 2019
Publication date	Aug 22, 2023
Grant date	Aug 22, 2023

Abstract

A seal assembly for a gas turbine engine includes a seal including a main body extending circumferentially between opposed mate faces. The main body has a sealing portion and an engagement portion extending outwardly from sealing portion along at least one of the mate faces. The main body has a core including one or more core plies arranged to establish an internal cavity. An overwrap has one or more overwrap plies arranged to follow a perimeter of the one or more core plies to establish the engagement portion and the sealing portion. A platform insert extends between portions of the core and the overwrap to establish the sealing portion. A method of fabricating a seal for a gas turbine engine is also disclosed.

First claim

What is claimed is:

1. A method of fabricating a seal for a gas turbine engine, comprising:
forming a hollow core including a plurality of triaxially braided core plies along at least one mandrel;
positioning a platform insert including at least one intermediate ply along the core, the at least one intermediate ply having a fiber construction of substantially discontinuous fibers;
forming an overwrap including a plurality of biaxially braided overwrap plies that establish a passageway; and
inserting the core plies and the platform insert at least partially into the passageway such that the core, the platform insert and the overwrap cooperate to establish a sealing portion, wherein the sealing portion extends circumferentially between opposed mate faces, the core and the overwrap cooperate to establish an engagement portion having an opening along each of the mate faces, and the opening is dimensioned to receive a respective mounting block.

2. The method as recited in claim 1 , wherein the core plies and the overwrap plies comprise silicon carbide fibers, and further comprising:
embedding the silicon carbide fibers in a ceramic matrix.

3. The method as recited in claim 1 , wherein the at least one mandrel is a pair of mandrels arranged in an opposed relationship, the sealing portion establishes a seal face on a first side of the seal, the engagement portion establishes a backside face on a second side of the seal opposite the first side, and further comprising:
removing the pair of mandrels from the core to establish an internal cavity in an interior of the core, the internal cavity spanning circumferentially between the openings along the mate faces, and the internal cavity bounded radially between a first wall of the sealing portion establishing the seal face and a second wall of the engagement portion establishing the backside face.

4. The method as recited in claim 3 , wherein the steps of forming the core and the overwrap occur such that the biaxially and triaxially braided plies and the at least one intermediate ply span between the mate faces.

5. The method as recited in claim 4 , wherein the step of forming the core occurs such that an absolute bias angle of bias tows in the respective core plies is between 60 degrees and 70 degrees.

6. The method as recited in claim 5 , wherein the step of forming the overwrap occurs such that an absolute bias angle of bias tows in the respective overwrap plies is between 30 degrees and 40 degrees.

7. The method as recited in claim 3 , further comprising:
forming an elongated slot in the second wall of the engagement portion, the elongated slot extending inwardly from the backside face to the internal cavity.

8. The method as recited in claim 7 , wherein the elongated slot extends along a length of the internal cavity.

9. The method as recited in claim 7 , wherein a width of the elongated slot is less than a width of the opening along each of the mate faces.

10. The method as recited in claim 1 , wherein the at least one intermediate ply comprises a fabric.

11. The method as recited in claim 10 , wherein the fabric is woven.

12. The method as recited in claim 11 , wherein the fabric is a satin weave including warp tows interlaced with weft tows, and the warp tows or the weft tows are dimensioned to span between the mate faces.

13. The method as recited in claim 1 , wherein the seal is a blade outer air seal (BOAS).

14. The method as recited in claim 13 , wherein the step of forming the core occurs such that an absolute bias angle of bias tows in the respective core plies is between 60 degrees and 70 degrees.

15. The method as recited in claim 14 , wherein the step of forming the overwrap occurs such that an absolute bias angle of bias tows in the respective overwrap plies is between 30 degrees and 40 degrees.

16. A method of fabricating a seal for a gas turbine engine, comprising:
forming a hollow core including a plurality of triaxially braided core plies along a pair of mandrels arranged in an opposed relationship;
positioning a platform insert along the core;
forming an overwrap including a plurality of biaxially braided overwrap plies that establish a passageway;
inserting the core plies and the platform insert at least partially into the passageway such that the core, the platform insert and the overwrap cooperate to establish a sealing portion extending circumferentially between opposed mate faces, wherein the core and the overwrap cooperate to establish an engagement portion having an opening along each of the mate faces, the opening is dimensioned to receive a respective mounting block; and
removing the pair of mandrels from the core to establish an internal cavity in the core, wherein the internal cavity spans between the openings along the mate faces, and the internal cavity is bounded between a first wall of the sealing portion establishing a seal face and a second wall of the engagement portion establishing a backside face.

17. The method as recited in claim 16 , wherein the platform insert comprises a metal material.

18. The method as recited in claim 16 , wherein platform insert includes at least one intermediate ply along the core, and the at least one intermediate ply having a fiber construction of substantially discontinuous fibers.

19. The method as recited in claim 16 , wherein:
the step of forming the core occurs such that an absolute bias angle of bias tows in the respective core plies is between 60 degrees and 70 degrees; and
the step of forming the overwrap occurs such that an absolute bias angle of bias tows in the respective overwrap plies is between 30 degrees and 40 degrees.

20. The method as recited in claim 19 , wherein the seal is a blade outer air seal (BOAS).

Assignees

• Raytheon Tech Corp

Inventors

• Fernandez Robin H

Classifications

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F01D11/16

  by self-adjusting means (F01D11/12 takes precedence) · CPC title

• F02C7/28

  Arrangement of seals · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F05D2240/11

  Shroud seal segments · CPC title