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

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.

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.

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.

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.

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.