Hybrid diffuser case for a gas turbine engine combustor

Patent metadata

Field	Value
Publication number	US-10060631-B2
Application number	US-201414911158-A
Country	US
Kind code	B2
Filing date	Aug 29, 2014
Priority date	Aug 29, 2013
Publication date	Aug 28, 2018
Grant date	Aug 28, 2018

Abstract

A hybrid diffuser case for a gas turbine engine includes an outer diffuser case wall that extends downstream from an annular outer pre-diffuser case shroud. An inner diffuser case wall extends downstream from an annular inner pre-diffuser case shroud. A multiple of struts extend between the annular outer pre-diffuser case shroud and the annular inner pre-diffuser case shroud.

First claim

What is claimed is:

1. A hybrid diffuser case for a gas turbine engine, comprising:
an outer diffuser case wall that extends downstream from an annular outer pre-diffuser case shroud;
an inner diffuser case wall that extends downstream from an annular inner pre-diffuser case shroud;
a plurality of struts that extend between the annular outer pre-diffuser case shroud and the annular inner pre-diffuser case shroud;
a compressor case interface that extends from the annular outer pre-diffuser case shroud, wherein the compressor case interface terminates with compressor interface fastener flange that extends radially therefrom, and the compressor interface fastener flange extends around and is perpendicular to a central longitudinal engine axis; and
a plurality of stiffeners that extend between the compressor interface fastener flange and the outer diffuser case wall.

2. The hybrid diffuser case as recited in claim 1 , further comprising an outer arcuate interface wall between the outer diffuser case wall and the annular outer pre-diffuser case shroud.

3. The hybrid diffuser case as recited in claim 1 , further comprising an arcuate interface wall between the inner diffuser case wall and the annular inner pre-diffuser case shroud.

4. The hybrid diffuser case as recited in claim 3 , further comprising a bearing support that extends from an inner diffuser case skirt.

5. The hybrid diffuser case as recited in claim 4 , wherein the bearing support terminates with a bearing support fastener flange that extends radially therefrom, and the bearing support a fastener flange extends around and is perpendicular to the central longitudinal engine axis.

6. The hybrid diffuser case as recited in claim 4 , wherein the bearing support and the compressor case interface are located along a common axis.

7. The hybrid diffuser case as recited in claim 1 , further comprising an inboard interface wall that extends from an annular inner diffuser case skirt.

8. The hybrid diffuser case as recited in claim 7 , wherein the inboard interface wall terminates with an inboard interface wall fastener flange that extends radially therefrom, the inboard interface wall fastener flange extends around and is perpendicular to the central longitudinal engine axis.

9. A hybrid diffuser case for a gas turbine engine, comprising:
an outer diffuser case wall that extends downstream from an annular outer pre-diffuser case shroud;
an inner diffuser case wall that extends downstream from an annular inner pre-diffuser case shroud;
a plurality of struts that extend between the annular outer pre-diffuser case shroud and the annular inner pre-diffuser case shroud;
a compressor case interface that extends from the annular outer pre-diffuser case shroud, wherein the compressor case interface terminates with a compressor interface fastener flange that extends radially therefrom, the compressor interface fastener flange extends around and is perpendicular to a central longitudinal engine axis;
a bearing support that extends from the inner diffuser case wall; and
a plurality of stiffeners that extend between the compressor interface fastener flange and the outer diffuser case wall.

10. The hybrid diffuser case as recited in claim 9 , further comprising an inner diffuser case skirt between the inner diffuser case wall and the annular inner pre-diffuser case shroud, the bearing support extends from the inner diffuser case skirt.

11. The hybrid diffuser case as recited in claim 10 , wherein the bearing support terminates with a bearing support fastener flange that extends radially therefrom, the bearing support fastener flange extends around and is perpendicular to the central longitudinal engine axis.

12. The hybrid diffuser case as recited in claim 9 , wherein the bearing support and the compressor case interface are located along a common axis.

13. The hybrid diffuser case as recited in claim 9 , further comprising an outer arcuate interface wall between the outer diffuser case wall and the annular outer pre-diffuser case shroud, wherein the compressor case interface extends from the annular outer pre-diffuser case shroud.

Assignees

• United Technologies Corp

Inventors

• Lyons Christopher B
• Williams Alexander W
• Broulidakis Alexander

Classifications

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F04D29/542

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

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F23R3/04

  Air inlet arrangements · CPC title

• F23R3/60 Primary

  Support structures; Attaching or mounting means · CPC title