US 5,345,757 A · Combustor apparatus for use in a gas turbine engine

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.

Claims9

Dependent claims

A combustor apparatus for a gas turbine engine comprising:

a plurality of injectors situated in said engine;
a fuel manifold for supplying fuel to said injectors;
a plurality of first fuel flow paths coupling said manifold to said plurality of injectors to provide fuel thereto;
at least one second fuel flow path for switchably coupling said manifold to at least one of said injectors to supply additional fuel thereto, not every one of said injectors having said second fuel flow path so coupled;
sensing means coupled to said engine for determining if a predetermined engine condition is present, and
electronic control means, coupled to said sensing means and said second fuel flow path, for switching said second fuel path to provide additional fuel to said at least one of said injectors when said sensing means determines that a predetermined engine condition exists.

3 more elements

Dependencies are inferred from the claim text.

Combustor apparatus for use in a gas turbine engine

Life of this patent

Combustor apparatus for use in a gas turbine engine

Life of this patent

Abstract

Claims9