US 2014/0196466 A1 · METHODS AND SYSTEMS FOR OPERATING GAS TURBINE ENGINES

Abstract

Methods and systems for operating a gas turbine engine including a fuel delivery system and a plurality of combustor assemblies are provided. The fuel delivery system comprises a primary fuel circuit configured to continuously supply fuel to each of the plurality of combustor assemblies during a first mode of operation and a second mode of operation. At least one secondary fuel circuit of the fuel delivery system is configured to supply fuel to each of the plurality of combustor assemblies during the second mode of operation. The secondary fuel circuit includes at least one isolation valve coupled in flow communication with each of the plurality of combustor assemblies. The at least one isolation valve facilitates preventing fluid flow upstream into the secondary fuel circuit during the first mode of operation. The fuel delivery system, using the isolation valve, replaces a purging system in the gas turbine engine.

Claims20

Dependent claims

A fuel delivery system for a gas turbine engine including a plurality of combustor assemblies, said fuel delivery system comprising:

a primary fuel circuit configured to continuously supply fuel to each of the plurality of combustor assemblies during a first mode of operation and a second mode of operation;
and
at least one secondary fuel circuit configured to supply fuel to each of the plurality of combustor assemblies during the second mode of operation, said secondary fuel circuit comprising at least one isolation valve coupled in flow communication with each of the plurality of combustor assemblies, said at least one isolation valve facilitates preventing fluid flow upstream into said secondary fuel circuit during said first mode of operation, wherein the gas turbine engine does not include a purging system.

A method for controlling fuel flow in a gas turbine engine including a plurality of combustor assemblies, each of the combustor assemblies including at least one fuel circuit, wherein a fuel delivery system supplies each fuel circuit with fuel, said method comprising:

supplying fuel to each of the plurality of combustor assemblies via a primary fuel circuit during a first mode of operation;
and
supplying fuel to each of the plurality of combustor assemblies via the primary fuel circuit and at least one secondary fuel circuit during a second mode of operation, wherein each of the at least one secondary fuel circuits comprises at least one isolation valve coupled in flow communication with each of the plurality of combustor assemblies, wherein each of the isolation valve facilitates preventing fluid flow upstream into the secondary fuel circuit during the first mode of operation, wherein the gas turbine engine does not include a purging system.

A gas turbine engine assembly comprising:

a plurality of combustor assemblies;
a primary fuel circuit configured to continuously supply fuel to each of said plurality of combustor assemblies during a first mode of operation and a second mode of operation;
and
at least one secondary fuel circuit configured to supply fuel to each of said plurality of combustor assemblies during said second mode of operation, said secondary fuel circuit comprising at least one isolation valve coupled in flow communication with each of said plurality of combustor assemblies, said at least one isolation valve facilitates preventing fluid flow upstream into said secondary fuel circuit during said first mode of operation, wherein the gas turbine engine does not include a purging system.

1 more element

Dependencies are inferred from the claim text.

Methods and systems for operating gas turbine engines

Life of this patent

Methods and systems for operating gas turbine engines

Life of this patent

Abstract

Claims20