System and method having flame stabilizers for isothermal expansion in turbine stage of gas turbine engine

Number of patents in Portfolio can not be more than 2000

United States of America

PATENT NO 11971170
SERIAL NO

18092120

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Abstract

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A system includes a gas turbine having a turbine shaft disposed along a rotational axis, a turbine casing disposed circumferentially about the turbine shaft, a combustion gas path disposed between the turbine shaft and the turbine casing, and a turbine stage disposed in the combustion gas path. The turbine stage includes a plurality of turbine vanes disposed upstream from a plurality of turbine blades. The gas turbine includes an isothermal expansion system coupled to the turbine stage, wherein the isothermal expansion system includes a plurality of flame stabilizers configured to vary axial positions of combustion within a turbine stage expansion of the turbine stage to reduce temperature variations over the turbine stage expansion. The flame stabilizers are disposed in different axial positions over an axial length between leading and trailing edges of the turbine blades, wherein at least one flame stabilizer is coupled to each of the turbine blades.

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Patent Owner(s)

  • GE INFRASTRUCTURE TECHNOLOGY, LLC

International Classification(s)

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  • 2022 Application Filing Year
  • F23R Class
  • 253 Applications Filed
  • 151 Patents Issued To-Date
  • 59.69 % Issued To-Date
Click to zoom InYear of Issuance% of Matters IssuedCumulative IssuancesYearly Issuances20222023202420250255075100

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Hall, Joel Meador Simpsonville, US 12 54
Woodall, John Farrior Greer, US 8 37

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  • 2 Citation Count
  • F23R Class
  • 97.22 % this patent is cited more than
  • 1 Age
Citation count rangeNumber of patents cited in rangeNumber of patents cited in various citation count ranges70201 - 10051015202530354045505560657075

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