Gas turbine engine combustion chamber

Details Gas turbine engine combustion chamber Gas turbine engine combustion chamber

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 3/14 (2006.01) F23C 6/04 (2006.01) F23R 3/28 (2006.01) F23R 3/34 (2006.01)

Patent

CA 2138203

A gas turbine engine combustion chamber (28) has primary and secondary combustion zones (36, 40). An annular secondary fuel and air mixing duct (56) surrounds the primary combustion zone (36). The annular secondary fuel and air mixing duct (56) is defined at its radially outer extremity by an annular wall (60). The annular wall (60) is at least partially formed by an annular manifold (74). The annular fuel manifold (74) has a number of radially inwardly extending fuel injectors (68) which inject fuel into the secondary fuel and air mixing duct (56). The annular fuel manifold (74) is mechanically isolated from the remaining portion (78) of the annular wall (60) by an annular gap (80). The annular fuel manifold (74) is supported from the combustor casing (48) by a fuel supply pipe (84) which is secured to the combustor casing (48) and the annular fuel manifold (74).

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