Annular turbomachine combustion chamber

Patent metadata

Field	Value
Publication number	US-9933164-B2
Application number	US-201515120015-A
Country	US
Kind code	B2
Filing date	Jan 27, 2015
Priority date	Feb 19, 2014
Publication date	Apr 3, 2018
Grant date	Apr 3, 2018

Abstract

An annular combustion chamber ( 10 ) for a turbomachine ( 100 ), the combustion chamber presenting an axial direction (X), a radial direction, and an azimuth direction, and comprising a first annular wall ( 12 ) and a second annular wall ( 14 ), each wall delimiting at least a portion of the volume of the annular combustion chamber ( 10 ), the first and second walls ( 12, 14 ) presenting complementary fitting elements ( 12 d , 14 d ), the first wall ( 12 ) presenting at least one first through hole ( 12 f ), while the second wall ( 14 ) presents at least one second through hole ( 14 f ), the combustion chamber ( 10 ) also having at least one pin ( 18 ) engaged in a pair of holes comprising a first hole ( 12 f ) and a second hole ( 14 f ), said pin ( 18 ) locking the fitting of the first and second walls ( 12, 14 ).

First claim

The invention claimed is:

1. An annular combustion chamber for a turbomachine including an axial direction, a radial direction, and an azimuth direction, the annular combustion chamber comprising a first annular wall and a second annular wall, each of the first annular wall and the second annular wall delimiting at least a portion of a volume of the annular combustion chamber, the first annular wall and the second annular wall including complementary fitting elements, the first annular wall including at least one first through hole, while the second annular wall includes at least one second through hole, the annular combustion chamber also having at least one pin engaged in a pair of through holes comprising one first through hole and one second through hole, said at least one pin locking a fitting together of the first annular wall and the second annular wall, said at least one pin being formed by an injector;
wherein one of the one first through hole or the one second through hole of the pair of through holes is provided in a projecting blade; and
wherein a projection arranged at the other of the one first through hole or the one second through hole of the pair of through holes extends substantially parallel to an axis of said other of the one first through hole or the one second through hole so as to co-operate with the projecting blade by snap-fitting.

2. The annular combustion chamber according to claim 1 , wherein the one first through hole and the one second through hole of the pair of through holes are disposed substantially facing each other.

3. The annular combustion chamber according to claim 1 , wherein the at least one pin extends substantially radially.

4. The annular combustion chamber according to claim 1 , wherein the complementary fitting elements comprise a plurality of axial tongues extending in the axial direction from one of the first annular wall and the second annular wall, and a plurality of openings provided in the other of the first annular wall and the second annular wall, said plurality of openings receiving the plurality of axial tongues.

5. The annular combustion chamber according to claim 1 , wherein one of the first annular wall and the second annular wall includes an annular shoulder that co-operates axially in abutment with the other of the first annular wall and the second annular wall.

6. The annular combustion chamber according to claim 1 , having only two annular walls delimiting the volume of the combustion chamber, wherein the two annular walls are the first annular wall and the second annular wall.

7. A turbomachine including the annular combustion chamber according to claim 1 .

8. An annular combustion chamber for a turbomachine including an axial direction, a radial direction, and an azimuth direction, the annular combustion chamber comprising a first annular wall and a second annular wall, each of the first annular wall and the second annular wall delimiting at least a portion of a volume of the annular combustion chamber, the first annular wall and second annular wall including complementary fitting elements, the first annular wall including at least one first through hole, while the second annular wall includes at least one second through hole, wherein both the at least one first through hole and the at least one second through hole face a radial center of the annular combustion chamber, the annular combustion chamber also having at least one pin engaged in a pair of through holes comprising one first through hole and one-second through hole, said at least one pin locking a fitting together of the first annular wall and second annular wall, said at least one pin being formed by an injector;
wherein one of the one first through hole or the one second through hole of the pair of through holes is provided in a projecting blade; and
wherein a projection arranged at the other of the one first through hole or the one second through hole of the pair of through holes extends substantially parallel to an axis of said other of the one first through hole or the one second through hole so as to co-operate with the projecting blade by snap-fitting.

9. The annular combustion chamber of claim 8 , wherein the first annular wall includes a plurality of first through holes spaced about a circumference of the first annular wall, and the second annular wall includes a plurality of second through holes spaced about a circumference of the second annular wall, and the annular combustion chamber includes a plurality of injectors spaced about a circumference of the annular combustion chamber, each injector of the plurality of injectors extending through a respective pair of through holes comprising a first through hole and a second through hole, wherein each pair of through holes containing a respective injector of the plurality of injectors faces the radial center of the annular combustion chamber.

10. The annular combustion chamber of claim 9 , wherein the complementary fitting elements comprise a plurality of axial tongues extending in the axial direction from one of the first annular wall and the second annular wall, and a plurality of openings provided in the other of the first annular wall and the second annular wall, said plurality of openings receiving the plurality of axial tongues.

Assignees

• Safran Helicopter Engines

Inventors

• Savary Nicolas
• Berteau Patrick
• Carrere Bernard
• Dubourdieu Jean-Marc
• Naudot Ludovic

Classifications

• F23R3/283

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F23R2900/00019

  Repairing or maintaining combustion chamber liners or subparts · CPC title

• F23R3/60 Primary

  Support structures; Attaching or mounting means · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title