Abstract: A gas turbine engine combustor, eg of annular combustor configuration, has air inlets, typically in the dilution zone, which incorporate vortex generators operative to trip the inlet jet flow causing stabilizing vortex flow at the lateral edges of the jet. The vortex generators can comprise an inwardly directed abrupt change of section between forward and rearward parts of the air inlets. The rearward section of the air inlets can have a configuration operative to reinforce the jet stabilizing effect of the vortex flow. The combustor exhibits improved uniformity of jet and crossflow mixing.

Abstract: An anti-rotation locking assembly is provided for preventing rotation of a surface such as in a housing member with respect to a threaded shaft as on a body to which the housing member is threadably mounted. There are provided two opposing flats or relief surfaces on the end of threaded shaft extending beyond the housing surface. A recess is provided in the surface around the hole for accepting a locking c-ring. The recess has a non-circular profile in the plane of the surface to prevent rotation of the ring in the hole. A ring having an outer profile matching that of the recess is provided. The ring has outer dimensions and a shape to its sides which will cause its periphery to engage and cam over the sides of the recess. A threaded nut is provided for threading on the shaft over the ring to press the sides of the ring into the recess so as to cause the ring to grip the flats and engage the sides of the recess upon tightening.