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Patexia Research
Issue Date Sep 30, 2021
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Patent Application - GAS TURBINE ASSEMBLIES AND METHODS > Claims

  • 1. A gas turbine assembly comprising: a dome having an aperture configured to surround an injector assembly for a combustor, the dome having a front panel radially extending from the aperture and having a first cavity including a series of ducts, wherein a first duct of the series of ducts is configured to receive airflow into the first cavity from a compressor and a second set of ducts of the series of ducts and a third duct of the series of ducts are configured to direct airflow to the combustor from the first cavity, wherein the third duct has a larger diameter than the second set of ducts.
    • 2. The gas turbine assembly of claim 1, wherein the first cavity extends along a circumference of a backside of the front panel.
    • 3. The gas turbine assembly of claim 1, wherein the first cavity extends along a portion of a circumference of a backside of the front panel.
      • 4. The gas turbine assembly of claim 3, wherein a volume of the first cavity and the diameter of the third duct are based on a target frequency indicative of a resonance.
      • 5. The gas turbine assembly of claim 3, wherein the dome includes a second cavity extending along a portion of a circumference of a backside of the front panel, the second cavity further having a second series of ducts, wherein a volume of the first cavity is based on a first target frequency and a volume of the second cavity is based on a second target frequency.
    • 6. The gas turbine assembly of claim 1, wherein the second set of ducts are configured to direct an airflow to reduce a thermal temperature of the dome.
    • 7. The gas turbine assembly of claim 1, wherein the first cavity is configured to adjust an amount of air pressure delivered to the combustor.
  • 8. A method comprising: providing a dome having aperture configured to surround an injector assembly for a combustor, the dome having a front panel extending radially from the aperture; andcoupling a first cavity to the front panel, wherein the first cavity includes a series of ducts, wherein a first duct is configured to receive airflow into the first cavity from the compressor, a second set of ducts are configured to direct an airflow to reduce a thermal temperature of the dome.
    • 9. The method of claim 8, wherein the first cavity includes a third duct configured to direct airflow to the combustor from the first cavity, wherein the third duct has a diameter larger than the second set of ducts.
      • 10. The method of claim 9, wherein the first cavity extends along a circumference of a backside of the front panel.
      • 11. The method of claim 9, wherein the first cavity extends along a portion of a circumference of a backside of the front panel.
      • 12. The method of claim 9, further comprising adjusting a volume of the first cavity and the diameter of the third duct based on a target frequency indicative of a resonance.
      • 13. The method of claim 9, wherein the second set of ducts are positioned about the third duct.
        • 15. The method of claim 13, wherein the third duct interconnects the first and second cavities and is configured to direct airflow from the first cavity to the second cavity.
        • 16. The method of claim 13, wherein the front panel is angled to direct the airflow of the second set of ducts and the fourth duct away from the aperture.
    • 14. The method of claim 8, further comprising coupling a second cavity to the first cavity, the second cavity having a third duct configured to receive airflow into the second cavity from the compressor, and a fourth duct configured to direct airflow to a combustor, wherein the fourth duct has a diameter larger than the second set of ducts.
  • 17. A dome assembly of a gas turbine assembly, the dome assembly comprising: a front panel radially extending from an aperture that surrounds an injector assembly of the gas turbine assembly, the front panel having first and second cavities with the first cavity having a first set of ducts configured to receive airflow into the first cavity from the compressor and a second set of ducts configured to direct airflow to a combustor, the second cavity having a third duct configured to receive airflow into the second cavity and a fourth duct configured to direct airflow to a combustor, wherein the fourth duct has a diameter larger than the second set of ducts.
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