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

Claim 20:
21. A system, comprising:
a gas turbine, comprising:
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;
a turbine stage disposed in the combustion gas path, wherein the turbine stage comprises a plurality of turbine vanes disposed upstream from a plurality of turbine blades; and
an isothermal expansion system coupled to the turbine stage, wherein the isothermal expansion system comprises a plurality of flame stabilizers disposed in different axial positions to vary axial positions of combustion within the turbine stage to reduce temperature variations over 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 each of the plurality of turbine blades comprises multiple flame stabilizers of the plurality of flame stabilizers, wherein the multiple flame stabilizers are disposed in only one axial position and different radial positions on each of the plurality of turbine blades, wherein the one axial position varies from one turbine blade to another of the plurality of turbine blades.