Gas turbine engine having a gap between an outlet guide vane and an inner wall surface of a diffuser

Patent metadata

Field	Value
Publication number	US-9388703-B2
Application number	US-201113635892-A
Country	US
Kind code	B2
Filing date	Mar 18, 2011
Priority date	Mar 19, 2010
Publication date	Jul 12, 2016
Grant date	Jul 12, 2016

Abstract

A gas turbine engine is provided, which comprises an outlet guide vane provided downstream of a compressor; an outer casing supporting a radially outward part of the outlet guide vane; and an inner diffuser supporting a radially inward part. The outlet guide vane includes a radially inward inner flange; a projecting part projecting radially inward from the inner flange; and an engagement part protruding to one side in an axial direction of the projecting part. The inner diffuser includes a smaller-diameter part having a smaller outer diameter than the other part located upstream. The inner diffuser is provided with an engagement groove extending to one side in the axial direction from an outer peripheral surface of the smaller-diameter part or a region in the vicinity thereof. The engagement part is inserted into the engagement groove with a gap between the engagement part and groove.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
an outlet guide vane downstream of a compressor;
an outer casing supporting a radially outward part of the outlet guide vane; and
an inner diffuser supporting a radially inward part of the outlet guide vane;
wherein the outlet guide vane includes:
a radially inward inner flange;
a projecting part projecting radially inward from the inner flange; and
an engagement part protruding to one side in an axial direction from a foreside of the projecting part;
wherein the inner diffuser includes a smaller-diameter part having a smaller outer diameter than a part adjacent to the smaller-diameter part;
wherein the inner diffuser is provided with an engagement groove extending to the one side in the axial direction from an outer peripheral surface of the smaller-diameter part or a region in the vicinity of the outer peripheral surface of the smaller-diameter part;
wherein the engagement part is inserted into the engagement groove with a gap between the engagement part and the engagement groove;
wherein a last-stage stator vane of the compressor is upstream of the outlet guide vane;
wherein the outer casing supports a radially outward part of the stator vane;
wherein the inner diffuser supports a radially inward part of the stator vane;
wherein the stator vane includes:
a radially inward stator vane inner flange;
a projecting part projecting radially inward from a foreside of the stator vane inner flange; and
a stator vane engagement part protruding to a downstream side from the projecting part;

wherein the inner diffuser includes an engaged part at a foreside of the smaller-diameter part and protruding forward; and
wherein the engaged part is between the stator vane engagement part and the stator vane inner flange.

2. The gas turbine engine according to claim 1 ,
Wherein the gap is formed between an axial rear end surface of the engagement part and an axially inside surface of the engagement groove.

3. The gas turbine engine according to claim 1 ,
wherein a radially outward surface of the engagement part is configured to contact a radially outward surface of the second engagement groove during operation of the gas turbine.

4. The gas turbine engine according to claim 1 ,
wherein the projecting part is at a downstream part of the inner flange, and the engagement part protrudes to a downstream side.

5. The gas turbine engine according to claim 1 ,
wherein a radially inward surface of the engaged part is configured to contact a radially outward surface of the stator vane engagement part, during operation of the gas turbine.

6. The gas turbine engine according to claim 1 ,
wherein an inlet of an oblique introduction passage extending to inside of the inner diffuser is formed between the stator vane engagement part and the compressor.

Assignees

• Ikeguchi Takuya
• Sakai Yusuke
• Terauchi Koji
• Kawasaki Heavy Ind Ltd

Inventors

• Ikeguchi Takuya
• Sakai Yusuke
• Terauchi Koji

Classifications

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title

• F04D29/644

  especially adapted for elastic fluid pumps · CPC title

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title

• F05D2220/3219

  for the last stage of a compressor or a high pressure compressor · CPC title