Patent ID: 7591136

Claim:
A fuel injection system for a turbojet comprising: a fixed part including a swirler element configured to receive compressed air and to rotate said compressed air about a longitudinal axis of the fuel injection system, and a sliding crossmember comprising a centering part configured to center a fuel injector relative to the fuel injection system and to receive injected fuel for mixing with said compressed air from said swirler element, said sliding crossmember further comprising a flange mounted so as to slide on a sliding surface of the swirler element, the fixed part comprising antirotation means and the flange of the sliding crossmember comprising complementary antirotation means which interact with the antirotation means of the sliding crossmember to limit the rotation of the sliding crossmember relative to the fixed part, wherein the antirotation means of the sliding flange include at least one cutout formed in the flange and wherein the antirotation means of the fixed part include at least one lug protruding into said at least one cutout of the flange of the sliding crossmember, wherein said sliding crossmember is pivotable through a finite non-zero angle about said longitudinal axis of the fuel injection system until the lug butts against a wall of the cutout.