Method and apparatus for adjusting variable vanes
According to one aspect of the present disclosure, a gas turbine engine is disclosed that includes an engine section comprising a plurality of stages of variable vanes, and also includes first and second synchronizing rings (sync-rings). Movement of the first sync-ring adjusts vane angles of a first one of the stages of variable vanes, and movement of the second sync-ring adjusts vane angles of a second one of the stages of variable vanes. At least one sensor is configured to measure a condition of the gas turbine engine. A controller is configured to move the first sync-ring independently of the second sync-ring based on data from the at least one sensor.
1. A gas turbine engine comprising:
an engine section comprising a plurality of stages of variable vanes;
first and second synchronizing rings (sync-rings), wherein movement of the first sync-ring adjusts vane angles of a first one of the stages of variable vanes, and movement of the second sync-ring adjusts vane angles of a second one of the stages of variable vanes;
at least one sensor configured to measure a condition of the gas turbine engine; and
a controller configured to move the first sync-ring independently of the second sync-ring based on data from the at least one sensor;
wherein the second stage of variable vanes is aft of the first stage of variable vanes, and permits a smaller range of vane angle adjustment than the first stage.
2. The gas turbine engine of claim 1 , comprising:
a first actuator configured to rotate the first sync-ring, and a different, second actuator configured to rotate the second sync-ring;
wherein to move the first sync-ring independently of the second sync-ring, the controller is configured to actuate the first actuator independently of the second actuator.
3. The method of claim 2 , wherein the first and second actuators are electric actuators.
4. The gas turbine engine of claim 2 , wherein each sync-ring comprises:
first gear teeth situated on a first side of the sync-ring that engage an actuator gear of the actuator; and
second gear teeth situated on an opposite, second side of the sync-ring that engage vane gears of the stage of variable vanes associated with the sync-ring.
5. The gas turbine engine of claim 1 , wherein the at least one sensor includes a pressure sensor.
6. The gas turbine engine of claim 1 , wherein the at least one sensor includes a temperature sensor.
7. The gas turbine engine of claim 1 , wherein the at least one sensor includes a sensor situated at an inlet or an outlet of the engine section.
8. The gas turbine engine of claim 1 , wherein the engine section is a compressor.
9. The gas turbine engine of claim 1 , wherein the engine section is a turbine.
10. A method for adjusting variable vanes of a gas turbine engine comprising:
obtaining sensor data that indicates a condition of the gas turbine engine; and
moving a first synchronizing ring (sync-ring) independently of a second sync-ring based on the sensor data;
wherein the first and second sync-rings are part of an engine section that comprises a plurality of stages of variable vanes, wherein movement of the first sync-ring adjusts vane angles of a first one of the stages of variable vanes, and wherein movement of the second sync-ring adjusts vane angles of a second one of the stages of variable vanes;
wherein the second stage of variable vanes is aft of the first stage of variable vanes, and permits a smaller range of vane angle adjustment than the first stage.
11. The method of claim 10 , wherein said moving the first sync-ring independently of the second sync-ring comprises rotating the first sync-ring independently of the second sync-ring.
12. The method of claim 11 , wherein rotating the first sync-ring independently of the second sync-ring comprises controlling a first actuator to rotate the first sync-ring independently of a second actuator that is configured to rotate the second sync-ring.
13. The method of claim 12 , wherein each actuator is an electrical actuator, and controlling each actuator to rotate its associated sync-ring comprises applying a voltage to the actuator.
14. The method of claim 12 , wherein rotating the first sync-ring independently of the second sync-ring comprises rotating an actuator gear that engages first gear teeth situated on a first side of the sync-ring, and thereby rotates both the sync-ring and vane gears that engage second gear teeth on an opposite, second side of the sync-ring.
15. The method of claim 10 , wherein obtaining sensor data that indicates a condition of the gas turbine engine comprises measuring a pressure of the gas turbine engine.
16. The method of claim 10 , wherein obtaining sensor data that indicates a condition of the gas turbine engine comprises measuring a temperature of the gas turbine engine.
17. The method claim 10 , wherein obtaining sensor data that indicates a condition of the gas turbine engine comprises performing a measurement at an inlet or an outlet of the engine section.
18. The method of claim 10 , wherein the engine section is a compressor or a turbine.