Gas turbine engine mixing duct and method to start the engine

Details Gas turbine engine mixing duct and method to start the engine Gas turbine engine mixing duct and method to start the engine

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/26 (2006.01)

Patent

CA 2626259

A combustion chamber device having a field static pressure gradient adapted to expel a flame kernel or hot spot from a fuel-air mixing duct. The swirling flow passing through an annular mixing duct is turned from a radial direction to an axial direction before entering the combustion chamber. An ignition source located within the fuel-air mixing duct can then be used to start the combustion process in the gas turbine.

L'invention concerne un dispositif à chambre à combustion présentant un gradient de pression statique permettant d'expulser un noyau de flamme ou un point chaud à partir d'un conduit de mélange air-combustible. L'écoulement tourbillonnant traversant un conduit de mélange annulaire est dévié d'un sens radial à un sens axial avant d'entrer dans la chambre de combustion. Ensuite, une source d'allumage située dans le conduit de mélange air-combustible peut être utilisée pour lancer le processus de combustion dans la turbine à gaz.

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