COMBUSTOR FOR GAS TURBINE ENGINE

The combustor employs an array of fuel injectors (19) arranged in the mouth plane of the combustor flame tube (15/17). Each injector (19) has a baffle plate (44) through which the injector nozzle (33) projects, the baffle plate (44) having axial holes (49) for atomisation air to intercept and atomise radial fuel jets from the injector nozzle (33). Cooling of the flame tube (15/17) is performed by full coverage impingement and effusion without disturbing the cooling film by entry and penetration of transverse air jets. Flame stabilisation is achieved under all required operating conditions by the radial-fuel/axial-air atomisation in conjunction with the baffle plates (44). Comprehensive combustion mixing and dilution is achieved by the uniformly distributed supply of up to 90% of the total air supplied to the combustor around and through the baffle plates. There is a resultant economy in the air used for cooling, a uniformity of temperature distribution, stability of operation, and minimal emission of oxides of nitrogen.