System and method for exhaust gas use in gas turbine engines
AssigneeGeneral Electric Company
InventorSamuel David Draper
Life of this patent
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Abstract
In one embodiment, a system is provided that includes a first gas turbine engine. The first gas turbine engine has a first compressor configured to intake air and to produce a first compressed air and a first combustor configured to combust a first mixture to produce a first combustion gas. The first mixture has a first fuel, at least a first portion of the first compressed air, and a second combustion gas from a second gas turbine engine. The first gas turbine engine also includes a first turbine configured to extract work from the first combustion gas.
Claims18
A system, comprising:
- a first gas turbine engine, comprising:
- a first combustor configured to stoichiometrically combust a first mixture to produce a first combustion gas;
- a first turbine configured to extract work from the first combustion gas and output a first exhaust gas;
- and
- a first compressor fluidly coupled to an output of the first turbine and configured to compress the first exhaust gas to produce a compressed exhaust gas, wherein the first gas turbine engine routes a first portion of the compressed exhaust gas to the first combustor, wherein the first gas turbine engine is configured to export a second portion of the compressed exhaust gas directly to additional combustors of additional gas turbine engines, and wherein the second portion of the compressed exhaust gas is between approximately 30 percent and 50 percent of a total amount of the compressed exhaust gas produced by the first gas turbine engine.
A system, comprising:
- a first gas turbine engine, comprising:
- a first compressor configured to intake air and produce a first compressed air;
- a first combustor configured to combust a first mixture to produce a first combustion gas, wherein the first mixture comprises a first fuel, at least a first portion of the first compressed air, and a first portion of a compressed exhaust gas output exported from an exhaust gas outlet of a second gas turbine engine, wherein the compressed exhaust gas output exported from the second gas turbine engine is between approximately 30 percent and 50 percent of a total amount of compressed exhaust gas generated by the second gas turbine engine;
- and
- a first turbine configured to extract work from the first combustion gas;
- and
- a conduit directly coupling the exhaust gas outlet of the second gas turbine engine to an exhaust gas inlet of the first combustor such that the first combustor receives the first portion of the compressed exhaust gas output.
A method of operation of a gas turbine engine system, comprising:
- combusting a fuel within a first combustor of a first gas turbine engine to produce a combustion gas;
- extracting work from the combustion gas using a first turbine of the first gas turbine engine to produce an exhaust gas;
- compressing the exhaust gas using a compressor of the first gas turbine engine to produce a compressed exhaust gas;
- providing a first portion of the compressed exhaust gas from the compressor back to the first combustor;
- providing a second portion of the compressed exhaust gas from the compressor directly to one or more separate gas turbine engines, wherein the second portion of the compressed exhaust gas is between approximately 30 percent and 50 percent of the compressed exhaust gas generated by the compressor of the first gas turbine engine;
- and
- using the second portion of the compressed exhaust gas in the one or more separate gas turbine engines as a diluent for combustion to control peak flame temperatures in respective combustors of the one or more separate gas turbine engines.
Dependencies are inferred from the claim text.