Patent ID: 9310083
Filing Date: 2016-04-12
CPC Classification: F23R,Y10T

Claim Text:
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.