US 2020/0232645 A1 · GAS TURBINE LOAD/UNLOAD PATH CONTROL

Abstract

A loading/unloading method for a gas turbine system is disclosed. The gas turbine system includes a combustion section featuring a primary combustion stage with a first plurality of fuel nozzles and a downstream, secondary combustion stage with a second plurality of fuel nozzles. For loading, the method progresses through each of a plurality of progressive combustion modes that sequentially activate a higher number of at least one of the first or second plurality of fuel nozzles; and for unloading, the method progresses through each of a plurality of progressive combustion modes that sequentially activate a lower number of at least one of the first or second plurality of fuel nozzles. During each combustion mode, regardless of whether loading or unloading, a primary combustion stage exit temperature of a combustion gas flow is controlled to be within a predefined target range corresponding to the respective combustion mode.

Claims20

Dependent claims

A loading/unloading method for a gas turbine (GT) system, the gas turbine system including a compressor feeding air to a combustion section that is coupled to a turbine, the combustion system including a plurality of combustors, each combustor including a primary combustion stage including a first plurality of fuel nozzles and a secondary combustion stage downstream from the primary combustion stage, the secondary combustion stage including a second plurality of fuel nozzles, the method comprising during unloading or loading of the GT system:

progressing through each of a plurality of progressive combustion modes that sequentially activate a different number of at least one of the first or second plurality of fuel nozzles than a preceding combustion mode;
and
during each combustion mode regardless of whether loading or unloading, controlling a primary combustion stage exit temperature of a combustion gas flow to be within a predefined target range corresponding to the respective combustion mode.

A gas turbine (GT) system, comprising:

a compressor;
a combustion section including a plurality of combustors, each combustor including a primary combustion stage including a first plurality of fuel nozzles and a secondary combustion stage downstream from the primary combustion stage, the secondary combustion stage including a second plurality of fuel nozzles;
a turbine section downstream of the combustion section;
a control system coupled to the combustion section and configured to, during a loading or unloading of the GT system:
progress through each of a plurality of progressive combustion modes that sequentially activate a different number of at least one of the first or second plurality of fuel nozzles;
and
during each combustion mode regardless of whether loading or unloading, control a primary combustion stage exit temperature of a combustion gas flow to be within a predefined target range corresponding to the respective combustion mode.

4 more elements

Dependencies are inferred from the claim text.

Gas turbine load/unload path control

Life of this patent

Gas turbine load/unload path control

Life of this patent

Abstract

Claims20