Gas turbomachine diffuser assembly with radial flow splitters

Patent metadata

Field	Value
Publication number	US-2018195722-A1
Application number	US-201815912243-A
Country	US
Kind code	A1
Filing date	Mar 5, 2018
Priority date	Aug 14, 2013
Publication date	Jul 12, 2018
Grant date	—

Abstract

A diffuser assembly includes a casing at a compressor aft end; an inner barrel member radially inward of the casing; and an array of radial flow splitters extending between the inner barrel member and the casing. Each radial flow splitter includes a leading edge facing into a flow of air, a trailing end wall opposite the leading edge, a pair of side walls extending between the leading edge and the trailing end wall, and an axis extending through the leading edge and the trailing end wall. A width of each radial flow splitter increases from the leading edge to the trailing end wall. The side walls diverge away from the axis in a downstream direction corresponding to the flow of air. Optionally, the side walls also diverge away from the axis in a radial direction between the inner barrel member and the casing.

First claim

What is claimed is:

1 . A diffuser assembly for a gas turbomachine comprising:
a forward casing disposed at an aft end of a compressor; an inner barrel member disposed radially inward of the forward casing; and an array of radial flow splitters extending between the inner barrel member and the forward casing, each radial flow splitter of the array of radial flow splitters comprising a leading edge facing into a flow of air from the compressor, a trailing end wall opposite the leading edge, a pair of side walls extending between the leading edge and the trailing end wall, and a longitudinal axis extending through the leading edge and the trailing end wall; wherein a width of each radial flow splitter increases from the leading edge to the trailing end wall; and wherein the pair of side walls diverge away from the longitudinal axis in a downstream direction corresponding to the flow of air.

2 . The diffuser assembly of claim 1 , wherein the pair of side walls further diverge away from the longitudinal axis in a radial direction between the inner barrel member and the forward casing.

3 . The diffuser assembly of claim 1 , wherein the longitudinal axis of each radial flow splitter of the array of radial flow splitters is aligned with a centerline axis of a respective combustor of the gas turbomachine.

4 . The diffuser assembly of claim 3 , wherein each radial flow splitter of the array of radial flow splitters is axially and circumferentially disposed beneath a transition piece of a respective combustor of the gas turbine.

5 . The diffuser assembly of claim 1 , wherein the inner barrel member comprises an upstream end proximate to the compressor, a downstream end opposite the upstream end, and an intermediate portion extending between the upstream end and the downstream end; and wherein the intermediate portion comprises a curved portion terminating in a first wall extending radially from the inner barrel member, the array of radial flow splitters being disposed along the intermediate portion such that the respective trailing end walls terminate at the curved portion.

6 . The diffuser assembly of claim 5 , wherein the downstream end of the inner barrel member comprises the first wall, an annular shelf connected to the first wall, and a second wall extending radially from the annular shelf opposite the first wall; and wherein the second wall is connected to an aft inner casing of the compressor.

7 . The diffuser assembly of claim 1 , wherein each of the radial flow splitters of the array of radial flow splitters is integrally, materially formed with the inner barrel member.

8 . The diffuser assembly of claim 1 , wherein the inner barrel member, the array of radial flow splitters, and the forward casing are materially, integrally formed with one another around at least a portion of a circumference extending about a longitudinal axis of the gas turbomachine.

9 . The diffuser assembly of claim 1 , wherein each of the radial flow splitters comprises a top surface extending from the leading edge to the trailing end wall and extending between the pair of side walls; and wherein the top surface comprises a mounting element configured to engage a mounting feature on the forward casing.

10 . The diffuser assembly of claim 9 , wherein each of the radial flow splitters is mechanically fastened to the forward casing through the mounting element.

11 . A gas turbomachine comprising:
a compressor for compressing a flow of air; a plurality of combustors for combusting fuel with the flow of air to produce combustion products; a turbine driven by the combustion products, the turbine being coupled to the compressor; and a diffuser assembly comprising:
a forward casing disposed at an aft end of the compressor;
an inner barrel member disposed radially inward of the forward casing; and
an array of radial flow splitters extending between the inner barrel member and the forward casing, each radial flow splitter of the array of radial flow splitters comprising a leading edge facing into a flow of air from the compressor, a trailing end wall opposite the leading edge, a pair of side walls extending between the leading edge and the trailing end wall, and a longitudinal axis extending through the leading edge and the trailing end wall;
wherein a width of each radial flow splitter increases from the leading edge to the trailing end wall; and
wherein the pair of side walls diverge away from the longitudinal axis in a downstream direction corresponding to the flow of air.

12 . The gas turbomachine of claim 11 , wherein the pair of side walls further diverge away from the longitudinal axis in a radial direction between the inner barrel member and the forward casing.

13 . The gas turbomachine of claim 11 , wherein the longitudinal axis of each radial flow splitter of the array of radial flow splitters is aligned with a centerline axis of a respective combustor of the plurality of combustors.

14 . The gas turbomachine of claim 13 , wherein each radial flow splitter of the array of radial flow splitters is axially and circumferentially disposed beneath a transition piece of a respective combustor of the plurality of combustors.

15 . The gas turbomachine of claim 11 , wherein the inner barrel member comprises an upstream end proximate to the compressor, a downstream end opposite the upstream end, and an intermediate portion extending between the upstream end and the downstream end; and wherein the intermediate portion comprises a curved portion terminating in a first wall extending radially from the inner barrel member, the array of radial flow splitters being disposed along the intermediate portion such that the respective trailing end walls terminate at the curved portion.

16 . The gas turbomachine of claim 15 , wherein the downstream end of the inner barrel member comprises the first wall, an annular shelf connected to the first wall, and a second wall extending radially from the annular shelf opposite the first wall; and wherein the second wall is connected to an aft inner casing of the compressor.

17 . The gas turbomachine of claim 11 , wherein each of the radial flow splitters of the array of radial flow splitters is integrally, materially formed with the inner barrel member.

18 . The gas turbomachine of claim 11 , wherein the inner barrel member, the array of radial flow splitters, and the forward casing are materially, integrally formed with one another around at least a portion of a circumference extending about a longitudinal axis of the gas turbomachine.

19 . The gas turbomachine of claim 11 , wherein each of the radial flow splitters comprises a top surface extending from the leading edge to the trailing end wall and extending between the pair of side walls; and wherein the top surface comprises a mounting element configured to engage a mounting feature on the forward casing.

20 . The gas turbomachine of claim 19 , wherein each of the radial flow splitters is mechanically fastened to the forward casing through the mounting element.

Assignees

• Gen Electric

Inventors

• Schott Carl Gerard
• Black Kenneth Damon
• Casavant Matthew Stephen

Classifications

• F02C3/06

  the compressor comprising only axial stages (F02C3/10 takes precedence) · CPC title

• F23R3/10 Primary

  for primary air (F23R3/06, F23R3/045 take precedence) · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F04D29/544

  Blade shapes · CPC title