Guiding ring for variable-pitch blades and method of mounting said ring

Patent metadata

Field	Value
Publication number	US-11149571-B2
Application number	US-201916541757-A
Country	US
Kind code	B2
Filing date	Aug 15, 2019
Priority date	Aug 17, 2018
Publication date	Oct 19, 2021
Grant date	Oct 19, 2021

Abstract

A ring for guiding variable-pitch blades and supporting an abradable coating for an aircraft turbomachine ring extends about an axis (X) and includes substantially radial orifices for mounting guiding sleeves intended each to receive a pivot of one of the blades. The ring may include a radially inner crown divided into sectors and supports the abradable coating. A radially outer annular ferrule may be divided into sectors and include the orifices for mounting the sleeves. In some embodiments, each ferrule sector is mounted about a crown sector by a circumferential sliding connection. The crown sector may include an immobilizer for rotationally immobilizing the sleeves of this ferrule sector about the axis.

First claim

The invention claimed is:

1. A ring for guiding variable-pitch blades and supporting an abradable coating for an aircraft turbomachine, the ring extending about an axis (X), the ring comprising:
substantially radial orifices in which are mounted guiding sleeves each configured to receive a pivot of one of the blades;
a radially inner crown divided into sectors and supporting the abradable coating; and
a radially outer annular ferrule divided into sectors and the orifices for mounting the sleeves located in the outer ferrule, each ferrule sector mounted about a crown sector by a circumferential sliding connection, the crown sector comprising an immobilizer configured to immobilize in rotation the sleeves of the ferrule sector about the axis (X);
wherein the immobilizer of each crown sector of the crown sectors comprises a cylindrical tab unitary with the respective crown sector and configured to be engaged in a transverse notch of the guiding sleeves of each ferrule sector mounted around the crown sector.

2. The ring according to claim 1 , wherein the cylindrical tab cooperates with a complementary cylindrical groove provided in the ferrule sector, to form an element of the circumferential sliding connection of the ferrule sector around the crown sector.

3. The ring according to claim 1 , wherein each crown sector comprises at least one of a cylindrical wall and a frustoconical wall, the at least one wall being configured to support the abradable coating which is connected by a first axial end to a first annular wall and by a second axial end to a second annular wall, the cylindrical tab being supported by the first annular wall and extending towards the second annular wall.

4. The ring according to claim 3 , wherein the first and second annular walls define an annular space in which the ferrule sectors are at least partially housed.

5. The ring according to claim 1 , wherein a quantity of crown sectors is less than a quantity of ferrule sectors, and at least two ferrule sectors are mounted on each crown sector.

6. The ring according to claim 5 , wherein the crown comprises two semi-circular crown sectors and the ferrule comprises at least six ferrule sectors, wherein at least three of the at least six ferrule sector is supported by each crown sector.

7. The ring according to claim 5 , wherein the crown comprises two semi-circular crown sectors and the ferrule comprises at least ten ferrule sectors, wherein at least five of the at least ten ferrule sectors are supported by each crown sector.

8. The ring according to claim 1 , wherein each crown sector comprises at least one of a radially outer cylindrical surfaces and a radial annular support surface configured to cooperate with one or more complementary annular surfaces of each ferrule sector.

9. The ring according to claim 1 , wherein each crown sector comprises a radially outer cylindrical surface and a radial annular support surface configured to cooperate with one or more complementary annular surfaces of each ferrule sector.

10. A method of mounting a ring according to claim 1 , comprising the steps of:
mounting the sleeves in the orifices of the ferrule sectors,
mounting the ferrule sectors by circumferential sliding around the crown sectors, to ensure that the sleeves are in rotational immobilization about their axes of revolution.

11. The ring according to claim 3 , wherein the at least one wall comprises a radially outer cylindrical surface forming a radial stop, arranged to cooperate with an inner radial end of an annular structure supporting the radial orifices and a radially outer annular surface forming an axial stop cooperating with a transverse wall of the annular structure supporting the radial orifices, the axial and radial stop being arranged between the first and second annular walls.

Assignees

• Safran Aircraft Engines

Inventors

• Delahaye Thomas Nolwenn Emmanuel
• Benderradji Kamel
• Parent Delphine Hermanee Maxime
• Quevreux Sandrine Hélène

Classifications

• F04D29/644

  especially adapted for elastic fluid pumps · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F04D27/002

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

• F01D17/162 Primary

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F04D29/323

  adjustable · CPC title