FIELD: engines and pumps.
SUBSTANCE: module of combustion chamber of the aircraft engine includes a rear wall of the combustion chamber, a lot of multipoint injection systems and a lot of fastening devices. On the periphery of rear wall of the combustion chamber there is a lot of through holes separated from each other. Each of the variety of multipoint injection systems is installed in one of the holes on rear wall of the combustion chamber with a working gap and each one includes a projecting part at the periphery of the above hole. Each of the variety of the fastening devices is meant for fixing of the multipoint injection systems on the rear wall of the combustion chamber and has the projecting part at the periphery of the hole on the side of the injection system. The working gap of injection systems is located in the zone of fastening devices on rear wall of the combustion chamber. Each projecting part of multipoint injection systems on the periphery to the hole and each projecting part of the fastening devices on the periphery to the hole, on the side of multipoint injection systems have an elongated shape formed with straight-line transverses. The shape has some part perpendicular to the injection axis where straight-line parts cross the curve along the transverse, and not along the tangent. Maximum size of the elongated shape formed with straight-line transverses passes radially in direction XX' to rear wall of the combustion chamber.
EFFECT: invention allows avoiding geometrical interaction between in-series located injection systems with maintenance of their characteristics.
12 cl, 9 dwg
