SYSTEM AND METHOD HAVING FLAME STABILIZERS FOR ISOTHERMAL EXPANSION IN TURBINE STAGE OF GAS TURBINE ENGINE
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United States of America Patent
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Issued Date -
Aug 1, 2024
app pub date -
Apr 12, 2024
filing date -
Dec 30, 2022
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Abstract
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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