Annular combustion chamber of a turbomachine

Patent metadata

Field	Value
Publication number	US-8925331-B2
Application number	US-201214124511-A
Country	US
Kind code	B2
Filing date	Jun 4, 2012
Priority date	Jun 8, 2011
Publication date	Jan 6, 2015
Grant date	Jan 6, 2015

Abstract

An annular combustion chamber for a turbomachine presenting an axial direction, a radial direction, and an azimuth direction, the combustion chamber including a first annular wall and a second annular wall, each annular wall defining at least a portion of an enclosure of the combustion chamber. The first annular wall and the second annular wall present complementary assembly mechanisms that co-operate by engagement in azimuth.

First claim

The invention claimed is:

1. An annular combustion chamber for a turbomachine presenting an axial direction, a radial direction, and an azimuth direction, the combustion chamber comprising:
a first annular wall and a second annular wall, each annular wall defining at least a portion of an enclosure of the combustion chamber,
wherein the first annular wall and the second annular wall present complementary assembly means that co-operate by engagement in azimuth, and
wherein the complementary assembly means comprises a plurality of first tongues extending from the first annular wall in azimuth in a first direction, and a plurality of second tongues extending from the second annular wall in azimuth in a second direction, opposite to the first direction, the first and second tongues co-operating by engagement in azimuth.

2. An annular combustion chamber according to claim 1 , wherein the first annular wall includes a first annular flange extending radially, and the second annular wall includes a second annular flange extending radially, the first and second flanges co-operating by bearing axially against each other.

3. An annular combustion chamber according to claim 2 , wherein the first tongues are formed in the first annular flange, and the second tongues are formed in the second annular flange.

4. An annular combustion chamber according to claim 1 , further comprising blocking means for blocking rotation of the second annular wall relative to the first annular wall.

5. An annular combustion chamber according to claim 4 , wherein the blocking means comprises at least a first projection secured to the first annular wall and at least a second projection secured to the second annular wall,
the complementary assembly means co-operating in azimuth by engagement in a first direction, and
wherein the first projection and the second projection cooperate in azimuth by elastic engagement in the first direction, and cooperate in azimuth in abutment in a second direction that is opposite to the first direction.

6. An annular combustion chamber according to claim 4 , wherein the first annular wall includes a first annular flange extending radially, and the second annular wall includes a second annular flange extending radially, the first and second flanges co-operating by bearing axially against each other, and
wherein the blocking means comprises at least one foldable blade formed in one of the flanges selected from the first and second annular flanges that is engaged in a gap formed in the other one of the flanges selected from the first and second annular flanges.

7. A turbomachine comprising an annular combustion chamber according to claim 1 .

8. An assembly method for assembling an annular combustion chamber according to claim 1 , comprising:
presenting complementary assembly means of the facing first and second annular walls; and
engaging the complementary assembly means in azimuth by turning the second annular wall relative to the first annular wall.

9. An assembly method according to claim 8 , for assembling an annular combustion chamber including blocking means for blocking rotation of the second annular wall relative to the first annular wall, the method further comprising blocking the second annular wall against turning relative to the first annular wall.

Assignees

• Carrere Bernard
• Savary Nicolas
• Turbomeca

Inventors

• Carrere Bernard
• Savary Nicolas

Classifications

• Y10T29/49323

  Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles · CPC title

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• Y10T403/7005

  Lugged member, rotary engagement · CPC title

• F23R3/60 Primary

  Support structures; Attaching or mounting means · CPC title