Diffuser case assembly

Patent metadata

Field	Value
Publication number	US-11022144-B2
Application number	US-201916361938-A
Country	US
Kind code	B2
Filing date	Mar 22, 2019
Priority date	Mar 22, 2019
Publication date	Jun 1, 2021
Grant date	Jun 1, 2021

Abstract

A diffuser case assembly 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.

First claim

What is claimed is:

1. A diffuser case assembly for a gas turbine engine comprising:
an inner diffuser case;
an outer diffuser case;
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; and
a diffuser frame comprising a plurality of struts each extending between an outer radial strut end and an inner radial strut end, each of the plurality of struts disposed between a pair of adjacent passages of the plurality of passages, the diffuser frame coupling the inner diffuser case to the outer diffuser case, the diffuser frame further comprising an annular frame member which extends from the outer radial strut end to an axial frame end of the annular frame member in contact with the outer diffuser case;
wherein at least one strut of the plurality of struts is hollow and the at least one hollow strut defines a channel extending radially through the at least one hollow strut from the outer radial strut end to the inner radial strut end.

2. The diffuser case assembly 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 assembly of claim 2 , wherein the diffuser frame and the inner diffuser case form an integral component.

4. The diffuser case assembly of claim 1 , wherein the diffuser frame is physically independent of the fairing.

5. The diffuser case assembly 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, the first material having a greater strength than the second material.

6. The diffuser case assembly of claim 1 , further comprising at least one seal disposed between the fairing and the diffuser frame.

7. The diffuser case assembly of claim 1 further comprising a sliding joint forming an interface between the fairing and the diffuser frame, the sliding joint comprising an alignment pin extending radially inward from the diffuser frame and a pin bushing disposed on the fairing.

8. The diffuser case assembly of claim 7 , wherein the sliding joint is configured to move radially in response to at least one of thermal expansion and contraction of the fairing in a radial direction.

9. The diffuser case assembly of claim 1 , wherein the channel is configured to conduct a flow of fluid between a compartment radially outside the inner diffuser case to a compartment radially inside the inner diffuser case.

10. The diffuser case assembly of claim 1 , wherein an auxiliary line extends through the channel.

11. The diffuser case assembly of claim 1 , wherein the fairing is a single-piece casting.

12. A diffuser case assembly for a gas turbine engine comprising:
an inner diffuser case;
and outer diffuser case;
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; and
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;

a diffuser frame coupling the inner diffuser case to the outer diffuser case, the diffuser frame comprising a plurality of hollow struts each extending between an outer radial strut end and an inner radial strut end, each strut of the plurality of struts defining a channel extending radially through each strut from the outer radial strut end to the inner radial strut end, and each strut of the plurality of struts disposed between a pair of adjacent passages of the plurality of passages; and
an annular compartment located radially outside of the outer radial strut end, the annular compartment defined by the diffuser frame, the outer diffuser case, and a mixing seal in contact with the diffuser frame and the outer diffuser case;
wherein the channel of each strut of the plurality of struts provides fluid communication between the annular compartment and an interior of the inner diffuser case.

13. The diffuser case assembly of claim 12 , wherein the diffuser frame and the inner diffuser case form an integral component.

14. The diffuser case assembly of claim 12 , wherein the diffuser frame is physically independent of the fairing.

15. A gas turbine engine comprising:
an inner diffuser case;
an outer diffuser case; and
a diffuser case assembly coupling the inner diffuser case to the outer diffuser case, the diffuser case assembly 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;
a diffuser frame comprising a plurality of struts each extending between an outer radial strut end and an inner radial strut end, each of the plurality of struts disposed between a pair of adjacent passages of the plurality of passages, the diffuser frame further comprising an annular frame member which extends from the outer radial strut end to an axial frame end of the annular frame member in contact with the outer diffuser case; and
an annular compartment located radially outside of the outer radial strut end, the annular compartment defined by the diffuser frame, the outer diffuser case, and a mixing seal in contact with the diffuser frame and the outer diffuser case;

wherein at least one strut of the plurality of struts is hollow and the at least one hollow strut defines a channel extending radially through the at least one hollow strut from the outer radial strut end to the inner radial strut end, and wherein the channel provides fluid communication between the annular compartment and an interior of the inner diffuser case.

16. The gas turbine engine of claim 15 , wherein the diffuser frame and the inner diffuser case form an integral component.

17. The gas turbine engine of claim 15 , wherein the diffuser frame is physically independent of the fairing.

18. The gas turbine engine of claim 15 , wherein the diffuser frame is made of a first material and the fairing is made of a second material different than the first material, the first material having a greater strength than the second 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

• F05D2240/12

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

• F05D2260/231

  Preventing heat transfer · 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

• F01D9/023

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title

• F23R3/50

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title