Method for controlling a hybrid turbomachine incorporating a time-limiting torque, associated hybrid turbomachine and aircraft comprising such a turbomachine.

Abstract

The invention relates to a method for controlling a hybrid turbomachine according to the following steps: a) providing a torque control signal (CEEC) to a control device to change the operating mode of the electric machine from generator mode to motor mode or vice versa, said device comprising a module configured to limit the time evolution of the torque between two threshold values ​​of opposite signs; b) retrieving a torque value from the output of the module and injecting said value into the input of the module so as to obtain a renewed torque value at the output of said limiter; c) repeating step b) N times, such that when the torque value injected into the input of the limiter is between the two threshold values, the renewed torque value at the output of said limiter exhibits, with respect to said input value, a limited time evolution. Figure for the abstract: Figure 3

Claims

9. Hybrid turbomachine comprising a propulsion shaft (AHP, ABP), an electric machine (MEHP, MEBP) configured to operate in a generator operating mode or a motor operating mode, a control device (DCEHP, DCEBP) for the electric machine and a mechanical transmission line (LTMHP, LTMBP) connecting the shaft to the electric machine, said mechanical transmission line (LTMhp, LTMbp) comprising at least two gears having teeth capable of contacting each other via corresponding bearing faces in an operating mode of the electric machine, characterized in that the control device (DCEHP, DCEBP) for the electric machine is configured to receive a torque command (CEEC, hp, Ceec, bp) whose value is adapted to change the operating mode of the electric machine,This implies that the corresponding bearing faces of the teeth of said at least two gears of the mechanical transmission line are to change, the control device (DCEHP, DCEBP) comprising a torque time evolution limiting module (MLC) configured to limit the time evolution of the torque between two threshold values ​​(V threshold, 1, V*Seuii_ 1, Vseuii_ 2, V*seuii_ 2), of opposite signs, of said torque, and the control device (DCE) comprising a feedback loop (BRE) at the output of the torque time evolution limiting module (MLC) to an input of said torque time evolution limiting module, such that when the torque value injected at the input of the torque time evolution limiting module (MLC) is between the two torque threshold values ​​of said limiter (MLC), the renewed torque value at the output of said limiter (MLC) is applied, by reference to the torque value injected at the input of the limiter (MLC),a temporal evolution limited by said limiter.

10. Aircraft comprising at least one hybrid turbomachine according to the preceding claim. [Fig. 2] [Fig. 3] [Fig. 4] [Fig. 5] C (Nm) [Fig. 7]

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