System and method having fluid injectors for isothermal expansion in turbine stage of gas turbine engine
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, a turbine stage disposed in the combustion gas path, wherein the turbine stage includes a plurality of turbine vanes disposed upstream from a plurality of turbine blades. The system includes an isothermal expansion system coupled to the turbine stage. The isothermal expansion system includes a plurality of fluid injectors 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, wherein at least one fluid injector of the plurality of fluid injectors is coupled to each of the plurality of turbine vanes.
1 . 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 each of the plurality of turbine vanes has an airfoil body; and
an isothermal expansion system coupled to the turbine stage, wherein the isothermal expansion system comprises a plurality of fluid injectors having one or more variations configured to vary axial positions of combustion over an axial stage length of the plurality of turbine blades of the turbine stage to reduce temperature variations over the turbine stage, wherein at least one fluid injector of the plurality of fluid injectors is on the airfoil body of each of the plurality of turbine vanes, wherein the one or more variations comprise variations in an axial position of the at least one fluid injector relative to a leading edge of the airfoil body of a respective vane of the plurality of turbine vanes from one vane to another in the plurality of turbine vanes;
wherein the at least one fluid injector of a first turbine vane of the plurality of turbine vanes is an upstream-most fluid injector of the plurality of fluid injectors and the at least one fluid injector of a second turbine vane of the plurality of turbine vanes is a downstream-most fluid injector of the plurality of fluid injectors;
wherein the first turbine vane and the second turbine vane are diametrically opposed with respect to the turbine casing;
wherein the axial position of the at least one fluid injector of each of a first set of turbine vanes between the first turbine vane and the second turbine vane are positioned downstream of the at least one fluid injector of a respective preceding turbine vane along a first path from the first turbine vane to the second turbine vane; and
wherein the axial position of the at least one fluid injector of each of a second set of turbine vanes between the first turbine vane and the second turbine vane are positioned upstream of the at least one fluid injector of a respective preceding turbine vane along a second path from the second turbine vane to the first turbine vane.
2 . The system of claim 1 , wherein each of the plurality of fluid injectors comprises a fuel port.
3 . The system of claim 1 , comprising:
one or more combustors upstream from the gas turbine, wherein each of the one or more combustors comprise one or more fuel nozzles configured to output fuel into a combustion chamber for combustion to generate a primary combustion gas, wherein the isothermal expansion system in the gas turbine is configured to generate a secondary combustion gas with varying the axial positions of combustion to provide a substantially uniform temperature over the axial stage length of the plurality of turbine blades of the turbine stage; and
a compressor upstream from the one or more combustors.
4 . The system of claim 1 , wherein the at least one fluid injector further varies in a geometry of a fluid port from the one vane to the another in the plurality of turbine vanes to vary the axial positions of combustion within the turbine stage, wherein the geometry of the fluid port comprises a geometrical shape, a cross-sectional area, an angle of an injection axis, or a combination thereof.
5 . The system of claim 1 , wherein the at least one fluid injector varies in the fluid flow rate via active control by a controller from the one vane to the another in the plurality of turbine vanes to vary the axial positions of combustion within the turbine stage.
6 . The system of claim 5 , wherein the fluid flow rate comprises a fuel flow rate and an oxidant flow rate.
7 . The system of claim 1 , wherein at least five fluid injectors of the plurality of fluid injectors are on the airfoil body of each of the plurality of turbine vanes, and the at least five fluid injectors vary in the axial position relative to the leading edge of the airfoil body from the one vane to the another in the plurality of turbine vanes to vary the axial positions of combustion within the turbine stage.
8 . The system of claim 7 , wherein each vane of the plurality of turbine vanes comprises the at least five fluid injectors at a common axial position relative to the leading edge and different radial positions relative to a base of the respective vane of the plurality of turbine vanes, and wherein the common axial position varies from the one vane to the another of the plurality of turbine vanes.
9 . The system of claim 7 , wherein each vane of the plurality of turbine vanes comprises the at least five fluid injectors at different axial positions relative to the leading edge and different radial positions relative to a base of a respective vane of the plurality of turbine vanes, and wherein the different axial positions vary from the one vane to the another of the plurality of turbine vanes.
10 . The system of claim 1 , wherein the plurality of fluid injectors is disposed in different axial positions over an axial length between leading and trailing edges of the plurality of turbine vanes, and the different axial positions comprise different axial distances measured from the leading edge of the plurality of turbine vanes.
11 . The system of claim 10 , wherein the different axial positions range over at least 50 to 100 percent of the axial length between the leading and trailing edges.
12 . The system of claim 10 , wherein the plurality of turbine vanes is mounted in a circumferential arrangement around the rotational axis of the turbine shaft.
13 . The system of claim 1 , wherein the at least one fluid injector of the plurality of fluid injectors is coupled to a suction side of the airfoil body of each of the plurality of turbine vanes.
14 . The system of claim 1 , wherein the plurality of turbine blades comprises a first plurality of turbine blades disposed in a first annular arrangement and a second plurality of turbine blades disposed in a second annular arrangement, wherein the first plurality of turbine blades is configured to rotate in a first rotational direction about the rotational axis via a first shaft portion of the turbine shaft, wherein the second plurality of turbine blades is configured to rotate in a second rotational direction about the rotational axis via a second shaft portion of the turbine shaft, wherein the first and second rotational directions are opposite to one another.
15 . The system of claim 1 , comprising a controller having a processor, a memory, and instructions stored on the memory and executable by the processor to control the isothermal expansion system based on an isothermal control scheme to vary the axial positions of combustion within the turbine stage to reduce the temperature variations over the turbine stage at least by varying one or more parameters of fluid injection from the plurality of fluid injectors from the one vane to the another on the respective plurality of turbine vanes.
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, the turbine stage comprises a plurality of turbine vanes disposed upstream from a plurality of turbine blades, and each of the plurality of turbine vanes has an airfoil body; and
varying axial positions of combustion over an axial stage length of the plurality of turbine blades of the turbine stage to reduce temperature variations over the turbine stage via one or more variations in a plurality of fluid injectors of an isothermal expansion system coupled to the turbine stage, wherein at least one fluid injector of the plurality of fluid injectors is on the airfoil body of each of the plurality of turbine vanes, wherein the one or more variations comprise variations in an axial position of the at least one fluid injector relative to a leading edge of the airfoil body of a respective vane of the plurality of turbine vanes from one vane to another in the plurality of turbine vanes;
wherein the at least one fluid injector of a first turbine vane of the plurality of turbine vanes is an upstream-most fluid injector of the plurality of fluid injectors and the at least one fluid injector of a second turbine vane of the plurality of turbine vanes is a downstream-most fluid injector of the plurality of fluid injectors;
wherein the first turbine vane and the second turbine vane are diametrically opposed with respect to the turbine casing;
wherein the axial position of the at least one fluid injector of each of a first set of turbine vanes between the first turbine vane and the second turbine vane are positioned downstream of the at least one fluid injector of a respective preceding turbine vane along a first path from the first turbine vane to the second turbine vane; and
wherein the axial position of the at least one fluid injector of each of a second set of turbine vanes between the first turbine vane and the second turbine vane are positioned upstream of the at least one fluid injector of a respective preceding turbine vane along a second path from the second turbine vane to the first turbine vane.
17 . The method of claim 16 , wherein varying the axial positions of combustion comprises executing an isothermal control scheme via a controller to vary one or more parameters of fluid injection from the one vane to the another in the plurality of turbine vanes to vary the axial positions of combustion within the turbine stage.
18 . The method of claim 16 , wherein at least five fluid injectors of the plurality of fluid injectors are on the airfoil body of each of the plurality of turbine vanes, wherein the at least five fluid injectors vary in the axial position relative to the leading edge of the airfoil body from the one vane to the another in the plurality of turbine vanes, and the axial position is at an axial distance measured from leading edge.
19 . A system, comprising:
a controller having a processor, a memory, and instructions stored on the memory and executable by the processor to:
control combustion in a combustor to generate a combustion gas flow that flows 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, the turbine stage comprises a plurality of turbine vanes disposed upstream from a plurality of turbine blades, and each of the plurality of turbine vanes has an airfoil body; and
control an isothermal expansion system comprising a plurality of fluid injectors having one or more variations to vary axial positions of combustion over an axial stage length of the plurality of turbine blades of the turbine stage to reduce temperature variations over the turbine stage, wherein at least one fluid injector of the plurality of fluid injectors is on the airfoil body of each of the plurality of turbine vanes, wherein the one or more variations comprise variations in an axial position of the at least one fluid injector relative to a leading edge of the airfoil body of a respective vane of the plurality of turbine vanes from one vane to another in the plurality of turbine vanes;
wherein the at least one fluid injector of a first turbine vane of the plurality of turbine vanes is an upstream-most fluid injector of the plurality of fluid injectors and the at least one fluid injector of a second turbine vane of the plurality of turbine vanes is a downstream-most fluid injector of the plurality of fluid injectors;
wherein the first turbine vane and the second turbine vane are diametrically opposed with respect to the turbine casing;
wherein the axial position of the at least one fluid injector of each of a first set of turbine vanes between the first turbine vane and the second turbine vane are positioned downstream of the at least one fluid injector of a respective preceding turbine vane along a first path from the first turbine vane to the second turbine vane; and
wherein the axial position of the at least one fluid injector of each of a second set of turbine vanes between the first turbine vane and the second turbine vane are positioned upstream of the at least one fluid injector of a respective preceding turbine vane along a second path from the second turbine vane to the first turbine vane.
20 . The system of claim 19 , wherein the controller is configured to execute an isothermal control scheme to vary the axial positions of combustion at least by varying one or more parameters of fluid injection from the one vane to the another in the plurality of turbine vanes.