Diffuser case support structure

Patent metadata

Field	Value
Publication number	US-11236677-B2
Application number	US-201916413347-A
Country	US
Kind code	B2
Filing date	May 15, 2019
Priority date	May 15, 2019
Publication date	Feb 1, 2022
Grant date	Feb 1, 2022

Abstract

A diffuser case support structure for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case. A sliding joint is formed between the fairing and the diffuser frame, the sliding joint comprising a fastener extending generally axially through an aperture disposed in the fairing.

First claim

What is claimed is:

1. A diffuser case support structure for a gas turbine engine comprising:
a fairing disposed circumferentially about a longitudinal axis, the fairing defining a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine, wherein a front end of the fairing defines the fluid path whereby the fairing is configured to receive a flow of gas and an aft end of the fairing defines the fluid path whereby the flow of gas is configured to exit the fairing at the aft end of the fairing;
a fairing flange extending from the aft end of the fairing;
a diffuser frame comprising a plurality of struts, each of the plurality of struts disposed between a pair of adjacent passages of the plurality of passages; and
a sliding joint forming an interface between the fairing and the diffuser frame, the sliding joint comprising a fastener extending generally axially through an aperture disposed in the fairing flange;
wherein the diffuser frame is configured to couple an inner diffuser case to an outer diffuser case.

2. The diffuser case support structure of claim 1 , wherein a space between each pair of adjacent passages of the plurality of passages defines a recessed portion of the fairing extending axially from an axial end of the fairing through a portion of the fairing.

3. The diffuser case support structure of claim 2 , wherein the diffuser frame and the inner diffuser case form a monolithic component.

4. The diffuser case support structure of claim 1 , further comprising a first seal configured to maintain a first seal between the outer diffuser case and the fairing.

5. The diffuser case support structure of claim 4 , further comprising a second seal configured to maintain a second seal between the fairing and the diffuser frame.

6. The diffuser case support structure of claim 1 , wherein the diffuser frame is made of a first material and the fairing is made of a second material different than the first material.

7. The diffuser case support structure of claim 5 , further comprising a third seal configured to maintain a third seal between the fairing and the diffuser frame, wherein the second seal is located radially opposite the fairing from the third seal.

8. The diffuser case support structure of claim 1 wherein the sliding joint further comprises a bushing extending through the aperture, the bushing compressed between the diffuser frame and the fastener.

9. The diffuser case support structure of claim 8 , wherein the fairing is configured to move radially with respect to the diffuser frame via the sliding joint, in response to at least one of thermal expansion and contraction of the fairing in a radial direction.

10. The diffuser case support structure of claim 9 , wherein the bushing comprises a flange at a first end of the bushing and a shaft at a second end of the bushing, wherein the shaft extends through the aperture, the shaft abuts the diffuser frame, and the fastener abuts the flange, and the bushing provides a load path between the fastener and the diffuser frame.

11. The diffuser case support structure of claim 5 , wherein at least one strut of the plurality of struts is hollow, thereby defining a channel configured to conduct a flow of fluid between a first compartment radially outside the inner diffuser case to a second compartment radially inside the inner diffuser case.

12. The diffuser case support structure of claim 1 , wherein the fairing is a single-piece of material.

13. A diffuser case support structure for a gas turbine engine comprising:
a fairing disposed circumferentially about a longitudinal axis, the fairing defining:
a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine, wherein a front end of the fairing defines the fluid path whereby the fairing is configured to receive a flow of gas and an aft end of the fairing defines the fluid path whereby the flow of gas is configured to exit the fairing at the aft end of the fairing;
a space between each pair of adjacent passages of the plurality of passages, the space defining a recessed portion of the fairing extending axially from an axial end of the fairing through a portion of the fairing; and
a fairing flange extending from the aft end of the fairing;

a diffuser frame comprising a plurality of struts, each strut of the plurality of struts disposed between a pair of adjacent passages of the plurality of passages; and
a sliding joint forming an interface between the fairing and the diffuser frame, the sliding joint comprising a fastener extending generally axially through an aperture disposed in the fairing flange;
wherein the diffuser frame is configured to couple an inner diffuser case to an outer diffuser case.

14. The diffuser case support structure of claim 13 , wherein the diffuser frame and the inner diffuser case form a monolithic component.

15. The diffuser case support structure of claim 13 , further comprising a diffuser frame flange extending radially inward from the outer diffuser case, wherein the diffuser frame is configured to be coupled to the diffuser frame flange via at least one of a metal joining process or a mechanical fastener.

16. The diffuser case support structure of claim 13 , further comprising:
a seal flange extending radially inward from the outer diffuser case; and
a first seal configured to maintain a seal between the seal flange and the fairing.

17. A gas turbine engine comprising:
an inner diffuser case;
an outer diffuser case; and
a diffuser case support structure coupling the inner diffuser case to the outer diffuser case, the diffuser case support structure comprising:
a fairing disposed circumferentially about a longitudinal axis, the fairing defining a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine, wherein a front end of the fairing the fluid path whereby the fairing is configured to receive a flow of gas and an aft end of the fairing defines the fluid path whereby the flow of gas is configured to exit the fairing at the aft end of the fairing;
a fairing flange extending from the aft end of the fairing;
a diffuser frame comprising a plurality of struts, each of the plurality of struts disposed between a pair of adjacent passages of the plurality of passages; and
a sliding joint forming an interface between the fairing and the diffuser frame, the sliding joint comprising a fastener extending generally axially through an aperture disposed in the fairing flange.

18. The gas turbine engine of claim 17 , wherein the diffuser frame and the inner diffuser case form a monolithic component.

19. The gas turbine engine of claim 17 , wherein the diffuser frame is coupled to the outer diffuser case via at least one of a metal joining process or a mechanical fastener.

20. The gas turbine engine of claim 17 , wherein the diffuser frame is made of a first material and the fairing is made of a second material different than the first material.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Hough Matthew Andrew
• Tu John S
• Harmon Stephen C
• Croteau Paul F
• Hanson Russell B
• Rathgeb Joshua C

Classifications

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F02C7/28 Primary

  Arrangement of seals · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title