An axially staged combustion system for a gas turbine engine

Details An axially staged combustion system for a gas turbine engine An axially staged combustion system for a gas turbine engine

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/28 (2006.01) F23R 3/10 (2006.01)

Patent

CA 2595424

An axially staged combustion system is provided for a gas turbine engine comprising a main body structure having a plurality of first and second injectors. First structure provides fuel to at least one of the first injectors. The fuel provided to the one first injector is adapted to mix with air and ignite to produce a flame such that the flame associated with the one first injector defines a flame front having an average length when measured from a reference surface of the main body structure. Each of the second injectors comprising a section extending from the reference surface of the main body structure through the flame front and having a length greater than the average length of the flame front. Second structure provides fuel to at least one of the second injectors. The fuel passes through the one second injector and exits the one second injector at a location axially spaced from the flame front.

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