Hub for radial housing of a helical ring of a turbomachine with variable-pitch blades and assembly comprising such a hub

• US 9,429,031 B2
• Filed: 07/02/2013
• Issued: 08/30/2016
• Est. Priority Date: 07/02/2012
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: Perdrigeon, Christophe, Jablonski, Laurent, Joly, Philippe Gerard Edmond
• Primary Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US13/933,538
• Publication Number:
  US 20140003945A1
• Time in Patent Office: 1,155 Days
• Field of Search: 415/66, 415 68- 69, 416/244.R, 416/244.A, 416/174, 416128-130, 416/147, 416/204.A, 416/205, 416/124, 416/126
• US Class Current: 1/1
• CPC Class Codes: F01D 5/3023 of radial insertion type, e.g. in individual recesses
• CPC Class Codes: F01D 7/00 Rotors with blades adjustable in operation; Control thereof for reversing F01D1/30
• CPC Class Codes: F02C 3/067 having counter-rotating rotors F02C3/073 takes precedence
• CPC Class Codes: F02C 6/206 the vehicles being airscrew driven
• CPC Class Codes: F05D 2220/324 to drive unshrouded, low solidity propeller
• CPC Class Codes: F05D 2220/325 to drive unshrouded, high solidity propeller
• CPC Class Codes: F05D 2260/33 with a bayonet coupling
• CPC Class Codes: F05D 2260/79 Bearing, support or actuation arrangements therefor

Abstract

A helical ring including a polygonal body and a plurality of cylindrical radial housings arranged in the body is provided. Each housing includes a surface adapted to receive a support of a blade of a helix. The surface of each housing is arranged on a radially internal surface of a corresponding hub. Each hub is a separate piece attached to the body of the ring, intended to be received in a radial housing of the body of the ring. The hub includes two projecting pins relative to its external surface to be fastened to the edges of a housing of the annular body, the two projecting pins forming a centering axis.

Claims

1. A hub for a radial housing of a helical ring of a turbomachine with variable-pitch blades, said ring comprising an annular rotor body and a plurality of radial housings distributed over said annular rotor body around a central axis, said hub comprising:

a piece separate from the annular rotor body, configured to be received in the radial housing of the annular rotor body, an internal surface of said piece being adapted to receive a cylindrical blade support crown and at least one of centering or guiding means for rotation of the cylindrical blade support crown; and

two pins projecting relative to an external surface of the hub to fasten said external surface to edges of the radial housing of the annular rotor body, the two projecting pins forming a centering axis,

wherein said internal surface comprises a machined area adapted to receive bearing rings of the cylindrical blade support crown, and

wherein the hub further comprises two rims adapted to be supported on the edges of the radial housing when the pins are in place on the edges of the radial housing.

2. An assembly for the helical ring of the turbomachine with the variable-pitch blades comprising the annular rotor body and the plurality of radial housings distributed over said annular rotor body around the central axis, said assembly comprising a plurality of hubs constituted by pieces separate from the annular rotor body, said pieces being hubs according to claim 1 adapted to be received in the radial housings of said annular rotor body,

wherein edges of one of the radial housings have U-shapes forming a stirrup for the pins of the hub and defining centering holes for said pins with a blocking hood attached to said one of the radial housings.

3. An assembly according to claim 2, further comprising detent forks comprising pieces separate from the annular rotor body and the hub, said forks forming a stirrup for the pins of the hub and being fixed to an internal wall of said annular rotor body.

4. An assembly according to claim 2, wherein the pins have a curved surface and a rectilinear surface opposite said curved surface, wherein an edge of each housing of the annular rotor body has curved surfaces adapted to receive a respective pin of the hub, and further comprising hood elements, comprising pieces separate from the annular rotor body and the hub, said hood elements comprising a rectilinear portion adapted to keep the pins supported against the curved surfaces.

5. An open-rotor helix for the turbomachine with the variable-pitch blades comprising the assembly according to claim 2, and a plurality of blades mounted on said assembly.

6. A turbomachine comprising:

a helical ring comprising an annular rotor body and a plurality of radial housings distributed over said annular rotor body around a central axis,

a plurality of variable-pitch blades; and

a hub for each of the radial housings, said hub comprising;

a piece separate from the annular rotor body, configured to be received in the radial housing of the annular rotor body, an internal surface of said piece being adapted to receive a cylindrical blade support crown and at least one of centering or guiding means for rotation of the cylindrical blade support crown, and

two pins projecting relative to an external surface of the hub to fasten said external surface to edges of the radial housing, the two projecting pins forming a centering axis,

wherein said internal surface comprises a machined area adapted to receive bearing rings of the cylindrical blade support crown, and

wherein the hub further comprises two rims adapted to be supported on the edges of the radial housing when the pins are in place on the edges of the radial housing.