Gas turbine engine combustion chamber

Details Gas turbine engine combustion chamber Gas turbine engine combustion chamber

1994-12-15

1995-12-19

Casaregola, Louis J.

Power plants

Combustion products used as motive fluid

Combustion products generator

60739, 60747, F02C 722

Patent

active

054759790

ABSTRACT:
A gas turbine engine combustion chamber has primary and secondary combustion zones. An annular secondary fuel and air mixing duct surrounds the primary combustion zone. The annular secondary fuel and air mixing duct is defined at its radially outer extremity by an annular wall. The annular wall is at least partially formed by an annular manifold. The annular manifold has a number of radially inwardly extending fuel injectors which inject fuel into the secondary fuel and air mixing duct. The annular fuel manifold is mechanically isolated from the remaining portion of the annular wall by an annular gap. The annular fuel manifold is supported from the combustor casing by a fuel supply pipe which is secured to the combustor casing and the annular fuel manifold.

REFERENCES:
patent: 3974646 (1976-08-01), Markowski et al.
patent: 4052844 (1977-10-01), Caruel et al.
patent: 5201181 (1993-04-01), Ohmori et al.
patent: 5251447 (1993-10-01), Joshi et al.
patent: 5321948 (1994-06-01), Leonard
patent: 5394688 (1995-03-01), Amos

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