System and method for controlling the modification of the pitch of the blades of a turbine engine

Patent metadata

Field	Value
Publication number	US-12246820-B2
Application number	US-202218261702-A
Country	US
Kind code	B2
Filing date	Mar 14, 2022
Priority date	Mar 25, 2021
Publication date	Mar 11, 2025
Grant date	Mar 11, 2025

Abstract

A system for controlling the modification of the pitch of the blades of a fan of a turbine engine, in particular for an aircraft. The turbine engine comprising blades mounted radially in a drive shaft and a setting device configured to modify the pitch of the blades on the basis of an axial force applied to said setting device. The control system comprises a hydraulic actuator, a hydraulic pump, a connecting ring connected mechanically to the hydraulic pump such that the flow rate of the hydraulic pump is proportional to the relative speed between the drive shaft and the connecting ring, and a magnetic coupling device designed to control the drive speed of the connecting ring in order to control the pitch of the blades independently of the speed of the drive shaft.

First claim

The invention claimed is:

1. A control system for controlling a pitch modification of blades of a fan of a turbomachine for an aircraft, the turbomachine including a drive shaft extending along a longitudinal axis and adapted to be rotatably driven about said longitudinal axis with respect to a fixed structure of said turbomachine, the blades are radially mounted with respect to said drive shaft and adapted to be oriented at a blade pitch, and an orientation device configured to modify the blade pitch as a function of an axial load applied to said orientation device, the control system comprising:
a hydraulic actuator coupled to the drive shaft to be rotatable therewith, in order to apply the axial load to said orientation device,
a hydraulic pump coupled to the drive shaft to be rotatable therewith and supplying the hydraulic actuator in order to apply the axial load to said orientation device as a function of the flow rate of the hydraulic pump,
a connecting ring gear mounted about said longitudinal axis with respect to the fixed structure of said turbomachine, said connecting ring gear being mechanically connected to the hydraulic pump so that the flow rate of the hydraulic pump is proportional to a relative speed between the drive shaft and the connecting ring gear, and
a magnetic coupling device configured to pilot the drive speed of the connecting ring gear in order to control the blade pitch independently of a speed of the drive shaft.

2. The control system according to claim 1 , wherein the hydraulic actuator comprises an actuator body having a first chamber and a second chamber configured to receive hydraulic fluid so as to translationally move the actuator body along the longitudinal axis as a function of a pressure in the first and second chambers.

3. The control system according to claim 1 , the hydraulic pump being configured to move the hydraulic actuator in a first direction, the control system comprises a return member configured to exert an axial return load in a second direction opposite to the first direction.

4. The control system according to claim 1 , wherein in the absence of magnetic coupling, the connecting ring gear is rotatably driven by the hydraulic pump.

5. The control system according to claim 1 , wherein the magnetic coupling device comprises a permanent magnet electric machine comprising stator members integral with the fixed structure and rotor members, integral with the connecting ring gear, which are magnetically coupled with the stator members so as to magnetically brake the connecting ring gear.

6. The control system according to claim 5 , wherein the magnetic coupling device further comprises a control unit configured to provide a control current to the stator members in order to vary a braking force.

7. The control system according to claim 6 , wherein the control unit is integral with the fixed structure.

8. The control system according to claim 6 , wherein the control unit comprises at least one variable resistor.

9. The control system according to claim 1 , further comprising a second hydraulic pump.

10. The control system according to claim 9 , wherein the hydraulic pump and the second hydraulic pump are connected in series.

11. The control system according to claim 9 , wherein the hydraulic pump and the second hydraulic pump are connected in parallel.

12. The control system according to claim 1 , comprising at least one overspeed management system configured to modify a power supply to the hydraulic actuator in the event of an overspeed detection.

13. A method for controlling the pitch modification of the blades of the fan of the turbomachine by means of the control system according to claim 1 , the method comprising:
modifying the drive speed of the connecting ring gear by the magnetic coupling device,
driving the hydraulic pump, by the connecting ring gear, in order to activate the hydraulic actuator and to apply the axial load to the orientation device, and
modifying the pitch of the blades as a function of the axial load applied to said orientation device.

14. The control system according to claim 1 , the hydraulic pump being configured to move the hydraulic actuator downstream, the control system comprises a return member configured to exert an axial return load upstream.

15. The control system according to claim 1 , wherein in the absence of magnetic coupling, the connecting ring gear is rotatably driven by the hydraulic pump at a same rotational speed.

Assignees

• Safran Aircraft Engines

Inventors

• Auriol Jacques

Classifications

• F04D27/002

  by varying geometry within the pumps, e.g. by adjusting vanes · CPC title

• B64C11/40 Primary

  automatic · CPC title

• B64C11/38 Primary

  fluid, e.g. hydraulic · CPC title