초록 ▼

Methods and systems for controlling a combustor for a gas turbine engine are provided. According to one example embodiment, a system includes an air control assembly associated with at least one air path of a combustor for a gas turbine engine. Additionally, the system also includes at least one sen

Methods and systems for controlling a combustor for a gas turbine engine are provided. According to one example embodiment, a system includes an air control assembly associated with at least one air path of a combustor for a gas turbine engine. Additionally, the system also includes at least one sensor for sensing at least one operating parameter of the gas turbine engine. Further, the system also includes a controller operable to receive at least one operating parameter sensed by the at least one sensor, and further operable to selectively control an air control assembly based at least in part on the at least one operating parameter sensed by the at least one sensor.

대표청구항 ▼

1. A system for controlling a combustor of a turbine engine, comprising: an air control assembly operably associated with at least one air path of a combustor of a turbine engine;at least one sensor operable to sense at least one operating parameter of the turbine engine; anda controller operable to

1. A system for controlling a combustor of a turbine engine, comprising: an air control assembly operably associated with at least one air path of a combustor of a turbine engine;at least one sensor operable to sense at least one operating parameter of the turbine engine; anda controller operable to selectively control the air control assembly based at least in part on the at least one operating parameter sensed by the at least one sensor, wherein the controller is further operable to determine an effective flow area of a variable air path associated with the combustor based at least in part on the at least one operating parameter, and is further operable to selectively control the air control assembly based at least in part on the effective flow area determined by the controller. 2. The system of claim 1, wherein the at least one sensor comprises a plurality of sensors, and wherein the controller is operable to selectively control the air control assembly based at least in part on the at least one operating parameter sensed by at least one of the plurality of sensors. 3. The system of claim 1, wherein the at least one sensor comprises at least one of an exhaust temperature sensor, a dynamic pressure sensor, a turbine inlet air temperature sensor, a turbine mass flow sensor, a compressor exit temperature sensor, a compressor exit pressure sensor, an emissions sensor, a flame detector, a static air pressure sensor, a static air temperature sensor, a flame optical emissions sensor, an ionization detector, an ambient air temperature sensor, a power meter, a delta pressure sensor, a single-point fluid flow meter, or an ultraviolet sensor. 4. The system of claim 1, wherein the controller is further operable to determine an effective flow area associated with the combustor during operation of the turbine engine and to adjust operation of the combustor based at least in part on the effective flow area determined by the controller. 5. The system of claim 4, wherein the controller is operable to selectively control the air control assembly to adjust operation of the combustor based at least in part on the effective flow area determined by the controller. 6. The system of claim 1, wherein the combustor comprises a first combustor and the air control assembly comprises a first air control assembly operably associated with an air path of the first combustor, the system further comprising: a second combustor of the turbine engine; anda second air control assembly operably associated with an air path of the second combustor;wherein the controller is operable to selectively control the first air control assembly independent of the second air control assembly based at least in part on the at least one operating parameter sensed by the at least one sensor. 7. The system of claim 1, wherein the air control assembly comprises at least one collar arranged proximate to a flow sleeve of the combustor, and wherein the controller is operable to selectively adjust the at least one collar to alter airflow through the flow sleeve by altering an effective flow area associated with the flow sleeve. 8. The system of claim 1, wherein the air control assembly comprises a restrictor positioned within an annulus of the combustor through which air may flow into at least one fuel premixer or combustion chamber, and wherein the controller is operable to selectively adjust the restrictor to alter airflow through the annulus. 9. The system of claim 8, wherein the restrictor comprises at least one vane or foil positioned within the annulus of the combustor upstream of a combustion liner. 10. The system of claim 1, wherein the air control assembly comprises at least one cover arranged proximate to an air inlet of at least one fuel premixer or fuel injector, and wherein the controller is operable to selectively adjust the at least one cover to alter airflow through the at least one fuel premixer or fuel injector. 11. A method for controlling a turbine engine, comprising: receiving at least one operating parameter from at least one sensor associated with a turbine engine; determining an effective flow area of a variable flow path associated with the combustor, wherein the effective flow area is based at least in part on the at least one operating parameter; andselectively controlling, based at least in part on the effective flow area, an air control assembly operably associated with an air path of a combustor of the turbine engine. 12. The method of claim 11, further comprising: determining an effective flow area associated with the combustor during operation of the turbine engine; and:adjusting operation of the combustor based at least in part on the effective flow area determined during operation of the turbine engine. 13. The method of claim 11, wherein the combustor comprises a first combustor and the air control assembly comprises a first air control assembly; the method further comprising: selectively controlling a second air control assembly associated with an air path of a second combustor of the turbine engine independent of the first air control assembly. 14. The method of claim 13, wherein the at least one operating parameter comprises a first operating parameter associated with the first combustor and a second operating parameter associated with the second combustor; the method further comprising: selectively controlling the first air control assembly based at least in part on the first operating parameter; andselectively controlling the second air control assembly based at least in part on the second operating parameter. 15. The method of claim 11, wherein selectively controlling the air control assembly operably comprises at least one of: altering airflow through a flow sleeve, altering airflow through an annulus of the combustor through which air may flow into at least one fuel premixer, fuel injector, or combustion chamber, or altering airflow through at least one fuel premixer or fuel injector. 16. The method of claim 11, wherein receiving the at least one operating parameter comprises receiving at least one of: an exhaust temperature, a dynamic pressure, a turbine inlet air temperature, a turbine mass flow, a compressor exit temperature, a compressor exit pressure, an emissions indication, a flame detection indication, a static air pressure, a static air temperature, a flame optical emissions indication, an ionization indication, an ambient air temperature, a power indication, a delta-pressure sensor, a single-point fluid flow meter, or an ultraviolet indication. 17. A method for controlling a turbine engine, comprising: receiving a first operating parameter from a first sensor associated with a first combustor of a turbine engine;receiving a second operating parameter from a second sensor associated with a second combustor of the turbine engine;based at least in part on the first operating parameter, determining a first effective flow area of a first variable flow path associated with the first combustor;based at least in part on the second operating parameter, determine a second effective flow area of a second variable flow path associated with the second combustor;selectively controlling, based at least in part on the first effective flow area, a first air control assembly operably associated with the first combustor; andselectively controlling, based at least in part on the second effective flow area, a second air control assembly operably associated with the second combustor. 18. The method of claim 17, further comprising: adjusting an operating profile of the first combustor based at least in part the first operating parameter; andadjusting an operating profile of the second combustor based at least in part on the second operating parameter.