Patent ID: 11971170
Assignee: GE INFRASTRUCTURE TECHNOLOGY LLC
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 15:
16. A method, comprising:
routing a combustion gas through a turbine stage along a combustion gas path disposed between a turbine shaft and a turbine casing of a gas turbine, wherein the turbine shaft is disposed along a rotational axis, the turbine casing is disposed circumferentially about the turbine shaft, and the turbine stage comprises a plurality of turbine vanes disposed upstream from a plurality of turbine blades; and
varying axial positions of combustion within the turbine stage to reduce temperature variations over the turbine stage at least by varying one or more parameters of fluid injection from a plurality of fluid injectors on the respective plurality of turbine vanes, and by varying flame stabilization via different axial positions of a plurality of flame stabilizers of an isothermal expansion system coupled to the turbine stage, wherein the plurality of flame stabilizers are disposed in the different axial positions over an axial length between leading and trailing edges of the plurality of turbine blades, wherein at least one of the plurality of flame stabilizers is coupled to each of the plurality of turbine blades.