Combustion chamber for an aircraft engine, and method for attaching an injection system in a combustion chamber of an aircraft engine

Patent metadata

Field	Value
Publication number	US-9310083-B2
Application number	US-201113819113-A
Country	US
Kind code	B2
Filing date	Aug 12, 2011
Priority date	Aug 27, 2010
Publication date	Apr 12, 2016
Grant date	Apr 12, 2016

Abstract

A combustion chamber in which the injection system is attached so as to prevent any axial motion of the injection system, the combustion chamber includes: a baffle including a tubular portion having a first upstream end surrounded by a first radially projecting collar; and an injection system including a bowl which includes a cylindrical portion inserted into the tubular portion, the cylindrical portion including a second upstream end surrounded by a second radially projecting collar, the second collar axially bearing against the first collar, wherein the combustion chamber includes a clamp which axially clamps the first and the second collars against one another, and a fastener which retains the clamp clamped on either side of the first and second collars.

First claim

The invention claimed is:

1. A combustion chamber of an aircraft engine comprising:
a baffle comprising at least one tubular portion, the tubular portion extending in the direction of a reference axis, the tubular portion having a first upstream end surrounded by a first radially projecting collar;
an injection system comprising at least one bowl which comprises a cylindrical portion inserted into the tubular portion, the cylindrical portion comprising a second upstream end that exits the first upstream end of the tubular portion, the second upstream end of the cylindrical portion being surrounded by a second radially projecting collar, the second collar being braced axially against the first collar;
a clamp configured to clamp the first and the second collars against one another axially, and
a fastener configured to retain the clamp clamped on either side of the first and second collars,
wherein the clamp comprises a first element having a portion thereof that bears axially against the first collar and a second element, distinct from the first element and separately mountable from the first element in the combustion chamber, having a portion thereof that bears against the second collar, and wherein the first and second elements are configured to cooperate with each other to clamp the first and the second collars against one another axially.

2. An aircraft engine comprising at least one combustion chamber according to claim 1 .

3. A method for attaching an injection system in an aircraft engine combustion chamber, the combustion chamber including a baffle that comprises at least one tubular portion, the tubular portion extending in the direction of a reference axis, the tubular portion having a first upstream end surrounded by a first radially projecting collar, the injection system comprising at least one bowl that comprises a cylindrical portion inserted into the tubular portion, the cylindrical portion comprising a second upstream end exiting the first upstream end of the tubular portion, the second upstream end of the cylindrical portion being surrounded by a second radially projecting collar, the second collar bearing axially against the first collar, the method comprising:
positioning a clamp on either side of the first and the second collars in such manner that said clamp clamps the first and the second collars against one another axially; and
fastening the clamp on either side of the first and the second collars in such manner that the clamp is retained in an axially clamping position on either side of the first and the second collars,
wherein the clamp comprises a first element having a portion thereof that bears axially against the first collar and a second element, distinct from the first element and separately mountable from the first element in the combustion chamber, having a portion thereof that bears against the second collar, and wherein the first and second elements are configured to cooperate with each other to clamp the first and the second collars against one another axially.

4. A combustion chamber of an aircraft engine comprising:
a baffle comprising a tubular portion, the tubular portion extending in the direction of a reference axis, the tubular portion having a first upstream end surrounded by a first radially projecting collar;
an injection system comprising a bowl which comprises a cylindrical portion inserted into the tubular portion, the cylindrical portion comprising a second upstream end that exits the first upstream end of the tubular portion, the second upstream end of the cylindrical portion being surrounded by a second radially projecting collar, the second collar being braced axially against the first collar;
clamping means that clamp the first and the second collars against one another axially, and
attachment means that retain the clamping means clamped on either side of the first and second collars,
wherein the clamping means comprise a first element having a portion thereof that bears axially against the first collar and a second element, distinct from the first element and separately mountable from the first element in the combustion chamber, having a portion thereof that bears against the second collar, and wherein the first and second elements are configured to cooperate with each other to clamp the first and the second collars against one another axially.

5. A combustion chamber of an aircraft engine comprising:
a baffle comprising at least one tubular portion, the tubular portion extending in the direction of a reference axis, the tubular portion having a first upstream end surrounded by a first radially projecting collar;
an injection system comprising at least one bowl which comprises a cylindrical portion inserted into the tubular portion, the cylindrical portion comprising a second upstream end that exits the first upstream end of the tubular portion, the second upstream end of the cylindrical portion being surrounded by a second radially projecting collar, the second collar being braced axially against the first collar;
a clamp configured to clamp the first and the second collars against one another axially, and
a fastener configured to retain the clamp clamped on either side of the first and second collars,
wherein the clamp comprises:
a retaining bushing split into at least two bushing sections, the retaining bushing comprising:
a retaining ring bearing axially against the first collar, and
a peripheral retaining skirt projecting axially from the retaining ring, the peripheral retaining skirt surrounding the first and second collars radially,

a retained bushing comprising:
a retained ring bearing axially against the second collar, and
a peripheral retained skirt projecting axially from the retained ring, the peripheral retained skirt surrounding the peripheral retaining skirt radially; the fastener configured to hold together the retaining bushing and the retained bushing such that the retaining ring and the retained ring hold the first and second collars clamped against one another so that no relative axial movement between the two is possible.

6. The combustion chamber according to claim 5 , wherein the tubular portion has a lateral wall, a shoulder projecting radially from the lateral wall, an annular channel being defined between the first collar and the shoulder, the retaining ring being inserted in the annular channel.

7. The combustion chamber according to claim 5 , wherein the fastener comprises:
at least two attachment lugs joined to the retaining bushing, said attachment lugs combining with the retaining peripheral skirt to form a peripheral channel in which the retained peripheral skirt is inserted,
at least one welded joint that fastens each attachment lug to the retained bushing.

8. The combustion chamber according to claim 5 , wherein the first and second collars radially abut the retaining peripheral skirt.

9. The combustion chamber according to claim 5 , wherein the retaining peripheral skirt has a height lower than a height of the assembly formed by the first collar and the second collar.

10. A method for attaching an injection system in an aircraft engine combustion chamber, the combustion chamber including a baffle that comprises at least one tubular portion, the tubular portion extending in the direction of a reference axis, the tubular portion having a first upstream end surrounded by a first radially projecting collar, the injection system comprising at least one bowl that comprises a cylindrical portion inserted into the tubular portion, the cylindrical portion comprising a second upstream end exiting the first upstream end of the tubular portion, the second upstream end of the cylindrical portion being surrounded by a se

Assignees

• Bunel Jacques Marcel Arthur
• Demoulin Brice Arnaud
• De Sousa Mario César
• Sevi Guillaume
• Snecma

Inventors

• Bunel Jacques Marcel Arthur
• Demoulin Brice Arnaud
• De Sousa Mario César
• Sevi Guillaume

Classifications

• F23R3/14

  by using swirl vanes · CPC title

• F23R3/60 Primary

  Support structures; Attaching or mounting means · CPC title

• F23R3/283

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

• Y10T29/49323

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

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title