Method for monitoring the clearance of a kinematic link between a control member and a receiving member
View Patent ↗The method consists, based on an operating parameter of the turbojet engine, in: displacing said control member ( 11 ) in a direction as far as a first position (P 1 ) for which the receiving members ( 5 ) are rotated so as to take up the clearance of the kinematic link ( 12 ), then displacing said control member in the direction opposing the previous direction, as far as a second position (P 2 ) when a variation of the selected operating parameter is observed, and in ascertaining the travel of the control member ( 11 ) between the two positions corresponding to the total clearance of the kinematic link ( 12 ), and comparing the ascertained value of said travel of the control member with a predetermined limit value and, if it is observed that the ascertained value of the travel of the control member is greater than said limit value, to carry out monitoring of the kinematic link ( 12 ).
1. A method for monitoring the clearance of a kinematic link between a control member and receiving members of a turbomachine, the operation of the turbomachine depending of at least one operating parameter,
wherein said method comprises the steps of:
displacing said control member in a direction as far as a first position for which the receiving members are rotated so as to take up the clearance of the kinematic link,
then displacing said control member in the direction opposing the previous direction, as far as a second position when a variation of said operating parameter is observed, and ascertaining the travel of the control member between the two positions corresponding substantially to the total clearance of the kinematic link, and
comparing the ascertained value of said travel of the control member between the two positions with a predetermined limit value and, when it is observed that the ascertained value of the travel of the control member is greater than said predetermined limit value, monitoring the kinematic link.
2. The method as claimed in claim 1 , in which the steps are repeated according to an established timescale corresponding to a number of flights of an aircraft provided with turbojet engines.
3. The method as claimed in claim 1 , wherein the control member is a linear actuating cylinder and the receiving members are blades of a stator with variable spacing of a compressor, and wherein a rotational speed of the compressor is the operating parameter of the turbomachine.
4. The method as claimed in claim 3 , wherein the second position of the travel of the control member is estimated to be reached when the variation in the rotational speed is in the order of 100 r/min.
5. The method as claimed in claim 1 , wherein the control member is a linear actuating cylinder and the receiving members are blades of a stator with variable spacing of a compressor, and wherein an air pressure circulating in the compressor with the variable blade assembly is the operating parameter of the turbomachine.
6. The method as claimed in claim 1 , wherein the control member is a linear actuating cylinder and the receiving members are blades of a stator with variable spacing of a compressor, and wherein a temperature of exhaust gases is the operating parameter of the turbomachine.