Diffuser case support structure

Patent metadata

Field	Value
Publication number	US-2020200028-A1
Application number	US-201816228994-A
Country	US
Kind code	A1
Filing date	Dec 21, 2018
Priority date	Dec 21, 2018
Publication date	Jun 25, 2020
Grant date	—

Abstract

A diffuser case support structure for a gas turbine engine is disclosed. The diffuser case support structure includes a fairing disposed circumferentially about a longitudinal axis. The fairing forms at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. The fairing defines a plurality of apertures extending through the fairing. At least one spoke extends through at least one respective aperture of the plurality of apertures. The at least one spoke is configured to couple an inner diffuser case and an outer diffuser case of the gas turbine engine.

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 and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine, the fairing defining a plurality of apertures extending through the fairing; and at least one spoke extending through at least one respective aperture of the plurality of apertures; wherein the at least one spoke is configured to couple an inner diffuser case and an outer diffuser case of the gas turbine engine.

2 . The diffuser case support structure of claim 1 , wherein the fairing defines a plurality of channels, the plurality of channels forming the at least a portion of the fluid path between the compressor and the combustor.

3 . The diffuser case support structure of claim 2 , wherein each aperture of the plurality of apertures is disposed between each respective pair of circumferentially adjacent channels of the plurality of channels.

4 . The diffuser case support structure of claim 1 , wherein the at least one spoke comprises a plurality of spokes.

5 . The diffuser case support structure of claim 4 , wherein each spoke of the plurality of spokes extends through a respective one of the plurality of apertures.

6 . The diffuser case support structure of claim 1 , wherein the at least one spoke is physically independent of the fairing.

7 . The diffuser case support structure of claim 1 , wherein the at least one spoke is made of a first material, and the fairing is made of a second material, different than the first material.

8 . The diffuser case support structure of claim 1 , further comprising at least one seal disposed between the fairing and at least one of the inner diffuser case and the outer diffuser case.

9 . The diffuser case support structure of claim 1 further comprising a sliding joint forming an interface between the fairing and at least one of the inner diffuser case and the outer diffuser case.

10 . The diffuser case support structure of claim 9 , 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.

11 . The diffuser case support structure of claim 1 , wherein the at least one spoke is hollow along at least a portion of a radial length of the at least one spoke.

12 . The diffuser case support structure of claim 11 , wherein the at least one spoke is configured to conduct a flow of fluid.

13 . The diffuser case support structure of claim 1 , wherein an auxiliary line extends through an aperture of the plurality of apertures.

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

15 . 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 apertures extending through the fairing; and
a plurality of channels extending through the fairing, the plurality of channels forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine; and
at least one spoke extending through at least one respective aperture of the plurality of apertures; wherein the at least one spoke is configured to couple an inner diffuser case and an outer diffuser case of the gas turbine engine.

16 . The diffuser case support structure of claim 15 , wherein each aperture of the plurality of apertures is disposed between each respective pair of circumferentially adjacent channels of the plurality of channels.

17 . The diffuser case support structure of claim 15 , wherein the at least one spoke is physically independent of the fairing.

18 . A gas turbine engine comprising:
an inner diffuser case; an outer diffuser case; and a diffuser case support structure, the diffuser case support structure comprising:
a fairing disposed circumferentially about a longitudinal axis and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine, the fairing defining a plurality of apertures extending through the fairing; and
at least one spoke extending through at least one respective aperture of the plurality of apertures;
wherein the at least one spoke is configured to couple the inner diffuser case to the outer diffuser case.

19 . The gas turbine engine of claim 18 , wherein the fairing comprises a plurality of channels, the plurality of channels forming the at least a portion of the fluid path between the compressor and the combustor.

20 . The gas turbine engine of claim 18 , wherein the at least one spoke is physically independent of the fairing.

Assignees

• United Technologies Corp

Inventors

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

Classifications

• F05D2240/91

  on a stationary structure · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F05D2240/12

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

• F01D9/065 Primary

  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

• 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