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

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 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 positioning comprises:

inserting a plurality of bushing sections downstream of the first collar, the bushing sections forming a retaining bushing, the retaining bushing including at least one retaining ring and one retaining peripheral skirt projecting axially from the retaining ring, the sections of the bushing being positioned such that the first collar bears axially against the retaining ring and the retaining peripheral skirt radially surrounds the first and the second collars,

mounting a retained bushing such that the retained bushing bears axially against the second collar, the retained bushing comprising a retained ring bearing axially against the second collar, the retained bushing comprising a retained peripheral skirt projecting axially from the retained ring, the retained peripheral skirt radially surrounding the retaining peripheral skirt,

clamping the first and the second collars axially between the bushing sections and the retained bushing.

11. The method according to claim 10 , wherein each section of bushing comprises at least one attachment lug, wherein said attachment lugs cooperate with the retaining peripheral skirt to define a peripheral channel into which the retained peripheral skirt is inserted, and wherein the fastening includes welding the attachment lugs to the retained bushing.

12. 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 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 attachment means holding 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.

13. The combustion chamber according to claim 12 , 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.

14. The combustion chamber according to claim 12 , wherein the attachment means comprises:

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,

a welded joint that fastens each attachment lug to the retained bushing.