Gas turbine engine combustors

Details Gas turbine engine combustors Gas turbine engine combustors

F - Mech Eng,Light,Heat,Weapons

23

R

60/168

F23R 3/04 (2006.01) F23R 3/06 (2006.01)

Patent

CA 1334893

A gas turbine engine combustor, eg of annulur 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.

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