| 摘要 |
933,775. Generating combustion products under pressure. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. April 20, 1960 [April 21, 1959], No. 13895/60. Class 51(1). In combustion equipment for gas turbine jet propulsion engines particularly reheat equipment thereof, flame-stabilizing rings 5, 6 of V-section are provided and a fuel ring manifold 7, 8 is disposed within each V-section ring, fuel being delivered from orifices 7a in the manifold through openings 5a formed at the angle of the V-section, and further fuel ring manifolds 9, 10 are provided upstream of the flame-stabilizing rings and of such a diameter relative to the flame stabilizer rings that the fuel delivered by them flows in contact with the flame stabilizers. Fuel is supplied to the ring manifolds 7, 8, 9, 10 through inlet portions 3, the inlet portions together with rods 2 serving to support the manifolds and stabilizing rings within the jet pipe 1. The manifolds 7, 8 may be supported within the stabilizing rings 5, 6 by a member 12, as shown in Fig. 7, which permits differential expansion of the two components. Various arrangements of apparatus, having two or three flame stabilizing rings and two or three further ring manifolds upstream thereof are described. In Fig. 13, two fuel ring manifolds 25, 26 are disposed within the flame stabilizing ring 5, one manifold 25 having a low delivery coefficient and the other 26 having a high coefficient, fuel being supplied through the manifold 26 up to a certain altitude and then through the manifold 25. The two manifolds 25, 26 may be disposed one downstream of the other, the downstream manifold injecting fuel with a downstream component of velocity while the upstream manifold injects fuel in an upstream direction. |
