Abstract: In a pilot burner fuel nozzle for a premixed type combustor, diffusion pilot fuel injection ports (fuel holes 101) are disposed unevenly in the circumferential direction, whereby a nonuniform pilot flame is formed in the circumferential direction in the premixed type combustor. Thereupon, the heat is distributed in the axial direction, so that oscillated combustion does not occur, by which stable combustion can be maintained.

Abstract: Bulkhead 14 is conical and therefore the surface of bulkhead liners 30 has a curved or arcuate surface 68. Raised lip 70 with planar surface 72 is adjacent and surrounded in each opening 20. Fuel nozzle guide 24 may be rotated against and sealed to the surface of the liner segments.

Abstract: A thrust reverser for a turbojet engine is disclosed in which the actuator for the thrust reverser is attached to a second support frame located downstream of the reverse thrust opening. A plurality of longitudinally extending beams interconnect the downstream support frame to an upstream support frame which is located upstream of the reverse thrust opening. A cylinder of the actuating device is attached to the downstream support frame and the extendible and retractable piston rod is attached to the moveable thrust reverser element. The location of the actuating device allows for a better stress distribution and enables the weight to be reduced as compared to prior art thrust reversers.