US 12,077,279 B2
System and method for detecting and mitigating a propeller failure condition
Jagoda Krzywon, Longueuil (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on Apr. 27, 2021, as Appl. No. 17/241,915.
Prior Publication US 2022/0340260 A1, Oct. 27, 2022
Int. Cl. B64C 11/38 (2006.01); B64C 11/30 (2006.01); B64D 45/00 (2006.01); F01D 7/02 (2006.01); F01D 21/00 (2006.01)
CPC B64C 11/385 (2013.01) [B64C 11/301 (2013.01); B64D 45/00 (2013.01); F01D 7/02 (2013.01); F01D 21/003 (2013.01); B64D 2045/0085 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A method for detecting and mitigating a failure condition of a propeller driven by an engine of an aircraft, the propeller having a plurality of variable pitch propeller blades, the method comprising:
at a controller,
obtaining one or both of an actual value of a rotational speed of the propeller and an actual value of a pitch angle of the blades;
in response to one or both of:
determining, based on the actual value of the rotational speed, that the rotational speed is below a reference rotational speed for the propeller and
determining, based on the actual value of the pitch angle, that the pitch angle is above a pitch angle threshold,
commanding an actuator operatively connected to the blades to decrease the pitch angle to increase the rotational speed towards the reference rotational speed;
obtaining, after the commanding of the actuator to decrease the pitch angle, one or both of a subsequent value of the rotational speed and a subsequent value of the pitch angle; and
commanding the actuator to hold the pitch angle in response to one or both of:
determining, based on the subsequent value of the rotational speed, that the rotational speed has failed to increase towards the reference rotational speed, and
determining, based on the subsequent value of the pitch angle, that the pitch angle has failed to decrease.
 
11. A system for detecting and mitigating a failure condition of a propeller driven by an engine of an aircraft, the propeller having a plurality of variable pitch propeller blades, the system comprising:
a processing unit; and
a non-transitory computer readable medium having stored thereon program code executable by the processing unit for:
obtaining one or both of an actual value of a rotational speed of the propeller and an actual value of a pitch angle of the blades;
in response to one or both of:
determining, based on the actual value of the rotational speed, that the rotational speed is below a reference rotational speed for the propeller and
determining, based on the actual value of the pitch angle, that the pitch angle is above a pitch angle threshold,
commanding an actuator operatively connected to the blades to decrease the pitch angle to increase the rotational speed towards the reference rotational speed;
obtaining, after the commanding of the actuator to decrease the pitch angle, one or both of a subsequent value of the rotational speed and a subsequent value of the pitch angle; and
commanding the actuator to hold the pitch angle in response to one or both of:
determining, based on the subsequent value of the rotational speed, that the rotational speed has failed to increase towards the reference rotational speed and
determining, based on the subsequent value of the pitch angle, that the pitch angle has failed to decrease.