Rapid active clearance control system of inter stage and mid-seals
Example apparatus, systems, and methods for rapid active clearance control of inter-stage and mid-stage seals are disclosed. An example apparatus to control clearance for a turbine engine comprises a case surrounding at least part of the turbine engine and defining an opening therethrough; a nozzle, the nozzle including a reference pressure sensor and a static pressure sensor on a tip of the nozzle; an actuator including a multilayer stack of material, a rod coupled to the first actuator and coupled to the nozzle through the opening in the case, the rod to move the nozzle based on contraction or expansion of the multilayer stack of material; and a controller to calculate and set the clearance between the rotor and the nozzle by supplying an electrical current to the multilayer stack to cause the multilayer stack to at least one of expand or contract.
1. An apparatus to control clearance for a turbine engine, the apparatus comprising:
a case surrounding at least part of the turbine engine and defining an opening therethrough;
a nozzle of the turbine engine, the nozzle including a reference pressure sensor at a first location on a tip of the nozzle and a static pressure sensor at a second location on the tip of the nozzle;
an actuator including a multilayer stack of material, wherein the actuator is positioned at a third location outside of the case;
a rod coupled to the actuator at the third location and coupled to the nozzle through the opening in the case, the rod to move the nozzle based on contraction or expansion of the multilayer stack of material; and
a controller to calculate and set a clearance between a rotor and the nozzle by supplying an electrical current to the multilayer stack of material in the actuator to cause the multilayer stack of material to at least one of expand or contract.
2. The apparatus of claim 1 , wherein the multilayer stack of material is a first multilayer stack of material, wherein the opening is a first opening, wherein the actuator is a first actuator, wherein the rod is a first rod, and further including:
a second actuator to control a clearance between a blade and the nozzle, the second actuator including a second multilayer stack of material, wherein the second actuator is positioned at a fourth location outside of the case; and
a second rod coupled to the second actuator and the nozzle through a second opening in the case at the fourth location, the second rod to move the nozzle based on the second multilayer stack of material.
3. The apparatus of claim 1 , wherein the controller uses a closed loop system, the closed loop system to set a target clearance, the controller to manipulate the actuator to achieve the target clearance based on a clearance calculation, the clearance calculation including at least an engine speed, a turbine pressure, a turbine temperature, a compressor temperature, and a compressor pressure.
4. The apparatus of claim 1 , wherein a reference pressure measurement obtained from the reference pressure sensor and a static pressure measurement obtained from the static pressure sensor are used to develop a normalized pressure measurement, the normalized pressure measurement used to generate a conversion curve correlating the normalized pressure measurement with a clearance measurement, the conversion curve used to compare to real-time pressure measurements to adjust a blade tip clearance.
5. The apparatus of claim 4 , wherein the controller uses an open loop system, the open loop system to set a target clearance based on the conversion curve and the normalized pressure measurement, the open loop system to manipulate the actuator to achieve the target clearance.
6. The apparatus of claim 1 , wherein the multilayer stack of material includes at least one of a piezoelectric material or a shape memory alloy.
7. The apparatus of claim 1 , wherein the reference pressure sensor is disposed on at least one of a compressor exit location, an aft location on the nozzle, a middle location on the nozzle, or a forward location on the nozzle.
8. The apparatus of claim 1 , wherein the static pressure sensor is disposed on at least one of an aft location on the nozzle, a middle location on the nozzle, or a forward location on the nozzle.
9. The apparatus of claim 4 , wherein the conversion curve is generated during testing at a plurality of altitudes.
10. The apparatus of claim 4 , wherein the conversion curve is generated during testing at a plurality of power levels, the plurality of power levels including at least one of a low power or a high power.
11. An apparatus to control clearance in a turbine engine, the apparatus comprising:
a controller to determine, using an open loop system, a first target clearance between a rotor and a nozzle and a second target clearance between a blade and a shroud, the controller in communication with at least one pressure sensor, the controller to supply electrical power to a plurality of actuators, the open loop system to set the first and second target clearances based on a conversion curve and a normalized presure measurement;
a first actuator of the plurality of actuators to actuate a first rod to achieve the first target clearance based on the controller determination, the first actuator located outside of an engine case and coupled to a first end of the first rod, the first rod positioned through a first seal in the engine case, a second end of the first rod coupled to the nozzle; and
a second actuator of the plurality of actuators to actuate a second rod to achieve the second target clearance based on the controller determination, the second actuator located outside of the engine case and coupled to a first end of the second rod, the second rod positioned through a second seal in the engine case, a second end of the second rod coupled to a hanger from which the shroud hangs.
12. The apparatus of claim 11 , wherein the normalized pressure measurement is developed from reference and static pressure measurements, the normalized pressure measurement used to generate the conversion curve correlating the normalized pressure measurement with a clearance measurement, the conversion curve used to compare to real-time pressure measurements to achieve the first and second target clearances.
13. The apparatus of claim 12 , wherein the conversion curve is generated during testing at a plurality of altitudes.
14. The apparatus of claim 12 , wherein the conversion curve is generated during testing at a plurality of power levels, the plurality of power levels including at least one of a low power or a high power.
15. The apparatus of claim 12 , wherein the conversion curve is generated during testing for a plurality of flight cycles.
16. The apparatus of claim 11 , wherein the first actuator includes a multilayer stack of material including at least one of a piezoelectric material or a shape memory alloy.
17. The apparatus of claim 11 , wherein the at least one pressure sensor measures pressure at one of a compressor exit location, a forward location on the nozzle, an aft location on the nozzle, or a mid-point location on the nozzle.
18. An apparatus to control clearance for a turbine engine, the apparatus comprising:
a case surrounding at least part of the turbine engine;
a nozzle to contain airflow, the nozzle including a reference pressure sensor at a first location on a tip of the nozzle and a static pressure sensor at a second location on the tip of the nozzle;
a mechanical arm to control a clearance between a rotor and the nozzle, wherein the mechanical arm is positioned at a third location outside of the case;
a rod coupled to the mechanical arm and coupled to the nozzle through an opening in the case at the third location, the rod to move the nozzle based on pivoting movement of the mechanical arm; and
a controller to calculate and set the clearance between the rotor and the nozzle by supplying an electrical signal to an actuator to cause pivoting movement of the mechanical arm.