Integrated fuel nozzle connection
AssigneeGeneral Electric Company
InventorsSubramanian Annamalai, Lucas John Stoia, Mohan Krishna Bobba
Life of this patent
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Abstract
A gas turbine includes a compressor, a turbine, and a combustor disposed downstream from the compressor and upstream from the turbine. The combustor includes an end cover. The combustor also includes a flange. The flange includes an internal fluid passage defined within the flange and the flange is coupled to an internal face of the end cover. A fuel port is integrally joined with the flange. The fuel port extends through the end cover between the flange and an inlet positioned outside of the end cover. The inlet of the fuel port is in fluid communication with the internal fluid passage of the flange.
Claims20
A gas turbine, comprising:
- a compressor;
- a turbine;
- a combustor disposed downstream from the compressor and upstream from the turbine, the combustor comprising:
- an end cover;
- a flange comprising an internal fluid passage defined within the flange, the flange coupled to an internal face of the end cover;
- and
- a fuel port integrally joined with the flange, the fuel port extending through the end cover between the flange and an inlet positioned outside of the end cover, the inlet of the fuel port in fluid communication with the internal fluid passage of the flange.
A combustor for a turbomachine, the combustor comprising:
- an end cover;
- a flange comprising an internal fluid passage defined within the flange, the flange coupled to an internal side of the end cover;
- and
- a fuel port integrally joined with the flange, the fuel port extending through the end cover between the flange and an inlet positioned outside of the end cover, the inlet of the fuel port in fluid communication with the internal fluid passage of the flange.
Dependencies are inferred from the claim text.