Method and system for operating an engine in a multi-engine aircraft
Systems and methods for operating an engine in a multi-engine rotorcraft are described herein. A first parameter indicative of torque of a first engine is obtained. A decrease of the first parameter is detected. In response to detecting the decrease of the first parameter, an autorotation of the rotorcraft is accommodated, A second parameter indicative of torque of a second engine of the rotorcraft is assessed while accommodating the autorotation. If the second parameter has not decreased, a shaft shear of the first engine is identified and accommodating of the autorotation is ended. If the second parameter has decreased, the accommodating is maintained.
1. A method for operating an engine in a multi-engine rotorcraft, the method comprising:
obtaining a first parameter indicative of torque of a first engine;
detecting a decrease of the first parameter indicative of torque of the first engine;
initially accommodating an autorotation of the first engine in response to detecting the decrease of the first parameter and maintaining a rotational speed of the first engine below an overspeed threshold;
concurrently with accommodating the autorotation of the first engine, assessing a second parameter indicative of torque of a second engine of the rotorcraft to distinguish between the autorotation and a shaft shear of the first engine;
when the second parameter has not decreased, identifying a shaft shear of the first engine and transitioning from the accommodating of the autorotation to an accommodating of the shaft shear of the first engine; and
when the second parameter has decreased, maintaining the accommodating of the autorotation of the first engine.
2. The method of claim 1 , wherein the first parameter is torque of the first engine and the second parameter is torque of the second engine.
3. The method of claim 1 , wherein the first parameter is a rate of change of the torque of the first engine and the second parameter is a rate of change of the torque of the second engine.
4. The method of claim 2 , further comprising detecting an increase of a rotational speed of the first engine, and wherein the autorotation is accommodated in response to detecting the decrease of the first parameter and the increase in the rotational speed.
5. The method of claim 4 , further comprising assessing a rotational speed of the second engine, and wherein the accommodating is maintained when the second parameter has decreased and the rotational speed of the second engine has increased.
6. The method of claim 1 , wherein accommodating the shaft shear of the first engine comprises commanding a shut-off of fuel to the first engine.
7. The method of claim 1 , wherein maintaining the rotational speed of the first engine below the overspeed threshold comprises reducing fuel flow to the first engine.
8. The method of claim 1 , wherein accommodating the autorotation comprises reducing fuel flow to the first engine and maintaining a rotational speed of the first engine to a rotational speed target.
9. The method of claim 1 , further comprising obtaining the second parameter from an engine computer associated with the second engine.
10. The method of claim 1 , further comprising determining the second parameter based on measurements obtained from at least one sensor of the second engine.
11. A system for operating an engine in a multi-engine rotorcraft, the system comprising:
at least one processing unit; and
at least one non-transitory computer-readable memory having stored thereon program instructions executable by the at least one processing unit, which when executed, cause the processing unit to:
obtain a first parameter indicative of torque of a first engine;
detect a decrease of the first parameter indicative of torque of the first engine;
initially accommodate an autorotation of the first engine in response to detecting the decrease of the first parameter and maintain a rotational speed of the first engine below an overspeed threshold;
concurrent, with accommodating the autorotation of the first engine, assess a second parameter indicative of torque of a second engine of the rotorcraft to distinguish between the autorotation and a shaft shear of the first engine;
when the second parameter has not decreased, identify a shaft shear of the first engine and transition from the accommodating of the autorotation to an accommodating of the shaft shear of the first engine; and
when the second parameter has decreased, maintain the accommodating of the autorotation of the first engine.
12. The system of claim 11 , wherein the first parameter is torque of the first engine and the second parameter is torque of the second engine.
13. The system of claim 11 , wherein the first parameter is a rate of change of the torque of the first engine and the second parameter is a rate of change of the torque of the second engine.
14. The system of claim 12 , wherein the program instructions are further executable by the at least one processing unit to detect an increase of a rotational speed of the first engine, and wherein the autorotation is accommodated in response to detecting the decrease of the first parameter and the increase in the rotational speed.
15. The system of claim 14 , wherein the program instructions are further executable by the at least one processing unit to assess a rotational speed of the second engine, and wherein the accommodating is maintained when the second parameter has decreased and the rotational speed of the second engine has increased.
16. The system of claim 11 , wherein accommodating the shaft shear of the first engine comprises commanding a shut-off of fuel to the first engine in response to identifying the shaft shear of the first engine.
17. The system of claim 11 , wherein maintaining the rotational speed of the first engine below the overspeed threshold in response to identifying the shaft shear of the first engine comprises reducing fuel flow to the first engine.
18. The system of claim 11 , wherein accommodating the autorotation comprises reducing fuel flow to the first engine and maintaining a rotational speed of the first engine to a rotational speed target.
19. The system of claim 11 , wherein the program instructions are further executable by the at least one processing unit to obtain the second parameter from an engine computer associated with the second engine.
20. A method for operating an engine in a multi-engine rotorcraft, the method comprising:
obtaining a first parameter indicative of torque of a first engine;
detecting a decrease of the first parameter indicative of torque of the first engine;
in response to detecting the decrease of the first parameter, initially accommodating an autorotation of the first engine by adjusting fuel flow to the first engine to maintain a rotational speed of the first engine substantially at a rotational speed target;
concurrently with accommodating the autorotation of the first engine, assessing a second parameter indicative of torque of a second engine of the rotorcraft to distinguish between the autorotation and a shaft shear of the first engine;
when the second parameter has not decreased, identifying a shaft shear of the first engine and transitioning from the accommodating of the autorotation to an accommodating of the shaft shear of the first engine; and
when the second parameter has decreased, maintaining the accommodating of the autorotation of the first engine.