Shaft shear detection for gas turbine engines
A system and a method for detecting a shaft shear event in a gas turbine engine are disclosed. The system comprises a sensor configured to detect a shaft shear force exerted by a shaft on a support structure supporting the shaft where the shaft shear force is indicative of shearing of the shaft. The system also comprises a controller operatively coupled to the sensor and configured to initiate a shutdown of the gas turbine engine in response to the detection of the shaft shear force by the sensor.
1. A system for detecting a shaft shear event in a gas turbine engine having a turbine supported by a shaft, the system comprising:
a sensor configured and located to detect a shaft shear force exerted by the shaft on a support structure of the gas turbine engine, the shaft shear force being indicative of shearing of the shaft and including a predetermined change in axial force exerted by the shaft of the gas turbine engine on the support structure as a function of time; and
a controller operatively coupled to the sensor and configured to initiate a shutdown of the gas turbine engine in response to the detection of the shaft shear force by the sensor.
2. The system of claim 1 , wherein the predetermined change in axial force comprises a 50% increase in the axial force exerted by the shaft of the gas turbine engine on the support structure in a predetermined period of time.
3. The system of claim 1 , wherein the sensor comprises a load cell disposed in a load path between the shaft of the gas turbine engine and the support structure.
4. The system of claim 1 , wherein the sensor comprises a load cell disposed in a load path between a thrust bearing supporting the shaft of the gas turbine engine and the support structure.
5. The system of claim 1 , wherein the sensor comprises a strain gauge configured to detect a strain of the support structure in response to the shaft shear force exerted by the shaft of the gas turbine engine on the support structure.
6. A gas turbine engine comprising:
a shaft having a first portion in torque-transmitting engagement with a load, and a second portion in torque-transmitting engagement with a turbine; and
a sensor configured and located to detect a shaft shear force exerted by the shaft on a support structure supporting the shaft, the shaft shear force being indicative of shearing of the shaft at a location axially between the first and second portions of the shaft, the shaft shear force including a predetermined change in axial force exerted by the shaft of the gas turbine engine on the support structure as a function of time; and
a controller operatively coupled to the sensor and configured to initiate a shutdown of the gas turbine engine in response to the detection of the shaft shear force by the sensor.
7. The gas turbine engine of claim 6 , wherein the predetermined change in axial force comprises a 50% increase in the axial force exerted by the shaft of the gas turbine engine on the support structure in a predetermined period of time.
8. The gas turbine engine of claim 6 , wherein the sensor comprises a load cell disposed in a load path between the shaft of the gas turbine engine and the support structure.
9. The gas turbine engine of claim 6 , wherein the sensor comprises a load cell disposed in a load path between a thrust bearing supporting the shaft of the gas turbine engine and the support structure.
10. The gas turbine engine of claim 6 , wherein the sensor comprises a strain gauge configured to detect a strain of the support structure in response to the shaft shear force exerted by the shaft of the gas turbine engine on the support structure.
11. A method for detecting a shaft shear event in a gas turbine engine, the method comprising:
detecting a shaft shear force exerted by a shaft of the gas turbine engine on a support structure supporting the shaft, the shaft shear force being indicative of shearing of the shaft and including a predetermined change in axial force exerted by the shaft of the gas turbine engine on the support structure as a function of time; and
initiating a shutdown of the gas turbine engine in response to the detection of the shaft shear force.
12. The method of claim 11 , wherein the predetermined change in axial force comprises a 50% increase in the axial force exerted by the shaft of the gas turbine engine on the support structure in a predetermined period of time.
13. The method of claim 11 , comprising detecting the shaft shear force using a load cell disposed in a load path between a thrust bearing supporting the shaft of the gas turbine engine and the support structure.
14. The method of claim 11 , comprising detecting the shaft shear force by detecting a strain of the support structure in response to the shaft shear force exerted by the shaft of the gas turbine engine on the support structure.
15. A system comprising:
a sensor configured and located to detect an axial force exerted by a shaft of a gas turbine engine on a support structure of the gas turbine engine supporting the shaft; and
a controller operatively coupled to the sensor and configured to initiate a control function associated with the gas turbine engine in response to the detection of the axial force by the sensor.
16. The system of claim 15 , wherein the axial force is indicative of an operation of a feathering system for a propeller coupled to the gas turbine engine.
17. The system of claim 15 , wherein the control function comprises an adjustment of a thrust or power setting of the gas turbine engine.
18. The system of claim 15 , wherein:
the change in axial force is indicative of an occurrence of damage to a fan coupled to the shaft; and
the control function comprises an adjustment of a thrust or power setting of the gas turbine engine.
19. The system of claim 15 , wherein the sensor comprises a load cell disposed in a load path between the shaft of the gas turbine engine and the support structure.
20. The system of claim 15 , wherein the sensor comprises a load cell disposed in a load path between a thrust bearing supporting the shaft of the gas turbine engine and the support structure.
21. The system of claim 15 , wherein the sensor comprises a strain gauge configured to detect a strain of the support structure in response to the axial force exerted by the shaft of the gas turbine engine on the support structure.
22. A method comprising:
detecting an axial force exerted by a shaft of a gas turbine engine on a support structure of the gas turbine engine supporting the shaft; and
initiating a control function associated with the gas turbine engine in response to the detection of the axial force.
23. The method of claim 22 , wherein the force is indicative of an operation of a feathering system for a propeller coupled to the gas turbine engine.
24. The method of claim 22 , wherein the control function comprises an adjustment of a thrust or power setting of the gas turbine engine.
25. The method of claim 22 , wherein:
the change in axial force is indicative of an occurrence of damage to a fan coupled to the shaft; and
the control function comprises an adjustment of a thrust or power setting of the gas turbine engine.
26. The method of claim 22 , wherein the axial force is in a load path between the shaft of the gas turbine engine and the support structure.
27. The method of claim 22 , wherein the axial force is in a load path between a thrust bearing supporting the shaft of the gas turbine engine and the support structure.
28. The method of claim 22 , comprising detecting the axial force by detecting a strain of the support structure in response to the axial force exerted by the shaft of the gas turbine engine on the support structure.