Positional control of fuel injection into gas turbine combustors
A system includes a combustor for a gas turbine defining a main axis extending in an upstream-downstream direction, the combustor including a combustor dome bounding an upstream portion of the combustor, wherein a plurality of injector openings are defined through the combustor dome. An injector defines a spray axis aligned with one of the plurality of injector openings for issuing a spray into the combustor along the spray axis. An actuator is operatively connected to the injector for movement of the injector relative combustor dome to adjust a relative position of the spray axis relative to the main axis to alter the position and/or direction of the spray injector during operation of the gas turbine engine.
1. A system comprising:
a combustor for a gas turbine defining a main axis extending in an upstream-downstream direction, the combustor including a combustor dome bounding an upstream portion of the combustor, wherein a plurality of injector openings are defined through the combustor dome;
an injector defining a spray axis aligned with one of the plurality of injector openings for issuing a spray into the combustor along the spray axis;
an actuator operatively connected to the injector for movement of the injector relative combustor dome to adjust a relative position of the spray axis relative to the main axis; and
a high pressure case of a gas turbine engine outboard of the combustor, wherein the actuator is positioned outside the high pressure case.
2. The system as recited in claim 1 , wherein the actuator is operatively connected to the injector for rotation of the injector relative combustor dome to adjust a relative angle of the spray axis relative to the main axis.
3. The system as recited in claim 2 , wherein the actuator and injector are configured to sweep the spray axis over a range of angles relative to the main axis, wherein the range includes a position wherein the spray axis is aligned parallel to the main axis.
4. The system as recited in claim 2 , wherein the actuator is configured to rotate the injector about a rotation axis that is radial relative to the main axis.
5. The system as recited in claim 2 , wherein the actuator is configured to rotate the injector about a rotation axis that is perpendicular to and radially offset from the main axis.
6. The system as recited in claim 2 , wherein the actuator is configured to rotate the injector about a rotation axis that is oblique relative to radials of the main axis, and offset from the main axis.
7. The system as recited in claim 1 , wherein the actuator is configured to move the injector linearly relative to the combustor dome.
8. The system as recited in claim 7 , wherein the actuator is configured to move the injector linearly along an actuation axis that is perpendicular to the main axis.
9. The system as recited in claim 7 , wherein the injector includes a nozzle with a sliding top hat seal interfacing and sealing between the nozzle and the combustor dome, wherein the sliding top hat seal is configured to slide relative to the combustor dome and to be stationary relative to the nozzle.
10. A system comprising:
a combustor for a gas turbine defining a main axis extending in an upstream-downstream direction, the combustor including a combustor dome bounding an upstream portion of the combustor, wherein a plurality of injector openings are defined through the combustor dome;
a plurality of injectors, each defining a respective spray axis aligned with one of the plurality of injector openings for issuing a spray into the combustor along the respective spray axis;
at least one actuator operatively connected to at least a subset of the plurality of injectors for movement of the subset relative combustor dome to adjust a relative position of the respective spray axes of the subset relative to the main axis, wherein the at least one actuator is a plurality of individual actuators, each operatively connected to move at least one respective injector of the plurality of injectors; and
a controller operatively connected to the at least one actuator, wherein the at least one actuator and the controller are configured to actuate the plurality of injectors in banks of injectors, wherein the controller is configured to actuate the plurality of actuators to move each of the injectors in the plurality of injectors identically to one another based on phase of engine operation, and/or the controller is configured to actuate the plurality of actuators to move each of the injectors in the plurality of injectors identically to one another for correcting for adverse combustion conditions.
11. The system as recited in claim 10 , wherein the at least one actuator is a single actuator operatively connected for movement of the at least the subset of the plurality of injectors.
12. The system as recited in claim 10 , wherein the at least one actuator includes a plurality of actuators, one for each one of the injectors in the plurality of injectors.
13. The system as recited in claim 10 , wherein the controller is configured to actuate the plurality of actuators in a regular, circumferential pattern based on phase of engine operation, and/or the controller is configured to actuate the plurality of actuators in a regular, circumferential pattern for correcting for adverse combustion conditions.
14. The system as recited in claim 10 , wherein the controller is configured to sweep the plurality of injectors through a range of converging and diverging positions of the spray axes relative to the main axis.
15. The system as recited in claim 14 , wherein the controller is configured to sweep the plurality of injectors through a range of clock-wise/counter clock-wise tangential positions of the spray axes relative to the main axis.
16. A system comprising:
a combustor for a gas turbine defining a main axis extending in an upstream-downstream direction, the combustor including a combustor dome bounding an upstream portion of the combustor, wherein a plurality of injector openings are defined through the combustor dome;
a plurality of injectors, each injector of the plurality of injectors defining a respective spray axis aligned with one injector opening of the plurality of injector openings for issuing a spray into the combustor along the respective spray axis;
at least one actuator operatively connected to at least a subset of the plurality of injectors for movement of the subset relative to the combustor dome to adjust a relative position of the respective spray axis of each injector in the subset relative to the main axis, wherein the at least one actuator is a plurality of individual actuators, wherein each individual actuator of the plurality of individual actuators is operatively connected to move at least one respective injector of the plurality of injectors; and
a controller operatively connected to the at least one actuator, wherein the at least one actuator and the controller are configured to actuate the plurality of injectors in banks of injectors, wherein the controller is configured to actuate the plurality of actuators to compensate for a faulty one of the injectors, and wherein injectors circumferentially neighboring the faulty injector are moved and actuators circumferentially remote from the faulty one of the injectors are moved less than the injectors circumferentially neighboring the faulty injector.