Method for supplying fuel to a gas turbine engine

Details Method for supplying fuel to a gas turbine engine Method for supplying fuel to a gas turbine engine

1994-05-02

1995-04-11

Casaregola, Louis J.

Power plants

Combustion products used as motive fluid

60 39091, F02C 722

Patent

active

054047099

ABSTRACT:
A combustor apparatus is provided for a gas turbine engine including a circumferential ring of injectors. A fuel manifold provides a source of fuel for the injectors. The combustor apparatus includes a plurality of first fuel flow paths between the manifold and all of the injectors. Fuel is provided to all of the injectors via these first flow paths. At least one second fuel flow path including an electronically switchable valve is coupled between the manifold and a selected one of the injectors to provide additional fuel thereto at certain times when special engine operating conditions, such as demand for initial ignition, crossfire and altitude relight are sensed.

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