1,184,379. Gas turbine combustion apparatus. MINISTER OF TECHNOLOGY. Aug. 8, 1968 [Aug.10, 1967], No. 36855/67. Heading F1L. A combustion device for forming a flame stabilization zone in a swiftly moving gas stream flowing through a duct, such as the reheat duct 1 of a gas turbine engine, comprises, Fig. 1, concentric baffles 3, 4 defining a divergent annular channel therebetween and a hollow annular vane 5 upstream of the baffles 3, 4 which can be supplied with air under pressure to issue through holes in the vane and deflect the gas flow through the duct away from the divergent channel and around the baffles. In normal circumstances, no air is supplied to the vane 5 and the gas flows past the vane and baffles with little disturbance. When reheat is required, fuel is injected upstream of the stabilizing device and air tapped from the engine compressor or other source is supplied to the vane 5. In one arrangement, the latter is made from a circular tube 5a with a rear fairing 56, in which case the air issues through radial holes 6, 7 in the vane. In a different arrangement, the vane 5 is of one piece construction and the air issues through inclined holes 8, 9. The included angle between the baffles 3, 4 may be 20 or 30 degrees. In a modification, Fig. 2, the outer baffle 3 is arranged as before but a hollow annular vane 11 forms part of the inner baffle 10, air issuing through holes 12, when required. In further modifications, the air holes in the vanes can be replaced hy continuous slots, or the baffles can be curved or streamlined.
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