Turbomachine module for a variable pitch blade propeller and turbomachine comprising it

Patent metadata

Field	Value
Publication number	US-11428199-B2
Application number	US-202016929492-A
Country	US
Kind code	B2
Filing date	Jul 15, 2020
Priority date	Jul 15, 2019
Publication date	Aug 30, 2022
Grant date	Aug 30, 2022

Abstract

A turbomachine module with a longitudinal axis, the module comprising: a rotary casing rotatable around the longitudinal axis and arranged to carry a propeller provided with a plurality of blades; a system for changing the pitch of the blades of the propeller comprising: a control, and a mechanism for varying the pitch of the blades of the propeller connecting these blades to the control, wherein the control comprises a rotary actuator comprising a control body and a reference body which is integral with the rotary casing, and wherein the mechanism for varying the pitch comprises a synchronization ring which is driven in rotation around the longitudinal axis by the control body and which is guided in rotation on the rotary casing, the synchronization ring being connected to the blades.

First claim

The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows:

1. A turbomachine module with a longitudinal axis, the module comprising:
a rotary casing rotatable around the longitudinal axis and arranged to carry a propeller provided with a plurality of blades; and
a system for changing the pitch of the blades of the propeller comprising:
a control, and
a variable pitch mechanism for varying the pitch of the blades of the propeller connecting these blades to the control,

wherein said control comprises a rotary actuator comprising a control body and a reference body which is integral with said rotary casing, and wherein said variable pitch mechanism for varying the pitch comprises a synchronization ring which is driven in rotation around the longitudinal axis by said control body and which is guided in rotation on said rotary casing by a guide, said synchronization ring being intended to be connected to said blades, the rotary actuator being offset axially with respect to the synchronization ring.

2. The module according to claim 1 , wherein the synchronization ring is at least partly surrounded by means for positioning said blades fixed to the rotary casing.

3. The module according to claim 1 , wherein the synchronization ring comprises a substantially cylindrical wall connected to at least a first frustoconical wall.

4. The module according to claim 3 , wherein connecting rods connect said first frustoconical wall to means for positioning said blades.

5. The module according to claim 3 , wherein the guide for guiding in rotation the synchronization ring comprises at least one rolling bearing interposed between said cylindrical wall and said rotary casing.

6. The module according to claim 3 , wherein said cylindrical wall comprises a section for rotational coupling with said control body.

7. The module according to claim 1 , wherein the synchronization ring is connected to a blade feathering module.

8. The module according to claim 7 , wherein the feathering module comprises an annular row of flyweights which are carried by said rotary casing, each being integral with a rotational axis parallel to said longitudinal axis and meshed with the synchronization ring.

9. The module according to claim 8 , wherein the rotational axes of the flyweights are connected to pinions meshed with an annular toothing radially external to the synchronization ring.

10. The module according to claim 3 , wherein the synchronization ring is connected to a blade feathering module via a frustoconical wall opposite the first frustoconical wall with respect to the substantially cylindrical wall.

11. The module according to claim 10 , wherein the frustoconical walls and the substantially cylindrical wall at least partially accommodate the mechanism for varying the pitch.

12. The module according to claim 1 , in which the reference body is axially offset with respect to the synchronization ring.

13. An aircraft turbomachine comprising at least one module according to claim 1 .

14. A turbomachine module with a longitudinal axis, the module comprising:
a rotary casing rotatable around the longitudinal axis and arranged to carry a propeller provided with a plurality of blades; and
a system for changing the pitch of the blades of the propeller comprising:
a control, and
a variable pitch mechanism for varying the pitch of the blades of the propeller connecting these blades to the control,

wherein said control comprises a rotary actuator comprising a control body and a reference body which is integral with said rotary casing, and wherein said variable pitch mechanism for varying the pitch comprises a synchronization ring which is driven in rotation around the longitudinal axis by said control body and which is guided in rotation on said rotary casing by a guide, said synchronization ring being intended to be connected to said blades, the rotary actuator being offset axially with respect to the synchronization ring
wherein the synchronization ring comprises a substantially cylindrical wall connected to at least a first frustoconical wall and
wherein the synchronization ring is connected to a blade feathering module via a frustoconical wall opposite the first frustoconical wall with respect to the substantially cylindrical wall.

15. A turbomachine module with a longitudinal axis, the module comprising:
a rotary casing rotatable around the longitudinal axis and arranged to carry a propeller provided with a plurality of blades; and
a system for changing the pitch of the blades of the propeller comprising:
a control, and
a variable pitch mechanism for varying the pitch of the blades of the propeller connecting these blades to the control,

wherein said control comprises a rotary actuator comprising a control body and a reference body which is integral with said rotary casing, and wherein said variable pitch mechanism for varying the pitch comprises a synchronization ring which is driven in rotation around the longitudinal axis by said control body and which is guided in rotation on said rotary casing by a guide, said synchronization ring being intended to be connected to said blades, the rotary actuator being offset axially with respect to the synchronization ring,
wherein the synchronization ring is connected to a blade feathering module comprising an annular row of flyweights which are carried by said rotary casing, each being integral with a rotational axis parallel to said longitudinal axis and meshed with the synchronization ring, and
wherein the rotational axes of the flyweights are connected to pinions meshed with an annular toothing radially external to the synchronization ring.

Assignees

• Safran Aircraft Engines

Inventors

• Servant Régis Eugène Henri
• Cottet Clément
• Papin Thierry Georges Paul

Classifications

• B64C11/06 Primary

  for variable-pitch blades · CPC title

• F03B11/008

  Measuring or testing arrangements (in general G01) · CPC title

• F05D2260/79

  Bearing, support or actuation arrangements therefor · CPC title

• F05D2260/74

  by turning around an axis perpendicular the rotor centre line · CPC title

• F03B3/145 Primary

  Mechanisms for adjusting the blades (if the regulation aspect is preponderant, see F03B15/00 and subgroups) · CPC title