A staged combustion chamber for a gas turbine

Details A staged combustion chamber for a gas turbine A staged combustion chamber for a gas turbine

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/34 (2006.01) F23C 6/04 (2006.01) F23D 14/62 (2006.01) F23R 3/14 (2006.01) F23R 3/16 (2006.01) F23R 3/28 (2006.01)

Patent

CA 2328283

A three-stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (54,70,92). The fuel and air mixing ducts (54, 70, 92) have a plurality of air injections apertures (62,64,76,98) spaced apart in the direction of flow through the fuel and air mixing ducts (54,70,92). The apertures (62,64,76,98) reduce the magnitude of the fluctuations in the fuel to air ratio of the fuel and air mixture supplied into the at least one combustion zone (36,40,44). This reduces the generation of harmful vibrations in the combustion chamber (28).

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