Turbomachine module equipped with a blade pitch-changing system of a stator vane

Patent metadata

Field	Value
Publication number	US-2023079110-A1
Application number	US-202117800067-A
Country	US
Kind code	A1
Filing date	Feb 17, 2021
Priority date	Feb 19, 2020
Publication date	Mar 16, 2023
Grant date	—

Abstract

A turbomachine module with a longitudinal axis comprising an unducted propeller rotated about the longitudinal axis and at least one straightener. The module includes a plurality of unducted variable-pitch stator blades extending along a radial axis, perpendicular to the longitudinal axis, from a fixed casing. The module includes a first stator blade pitch-changing system. The pitch-changing system includes at least one first control that includes a first fixed body connected to the fixed casing and a first body which is axially mobile in relation to the first fixed body and at least one first joining mechanism joining each stator blade to the first mobile body of the first control. The first joining mechanism includes: a joining ring centered on the longitudinal axis, joined to the feet of each stator blade and at least one lever joined, on one hand, to the joining ring and, on the other hand, to the first mobile body of the first control.

First claim

1 . A turbomachine module with longitudinal axis, comprising:
an unducted propeller driven in rotation about the longitudinal axis; and at least one straightener comprising a plurality of unducted variable pitch stator vanes extending along a radial axis perpendicular to the longitudinal axis from a stationary casing, wherein the at least one straightener comprises a first pitch change system for changing the pitches of the blades of the stator vanes which comprises: at least one first control means comprising a first stationary body connected to the stationary casing and a first movable body axially movable with respect to the first stationary body, and at least one first connection mechanism connecting each stator vane to the first movable body of the first control means, the first connection mechanism comprising:
a connection annulus, centered on the longitudinal axis and connected to the roots of each stator vane, and
at least one lever connected to the connection annulus and to the first movable body of the first control means.

2 . The module according to claim 1 , wherein the at least one first connection mechanism further comprises a plurality of arms, each of which is connected to a stator vane and to the connection annulus.

3 . The module according to claim 2 , wherein each arm comprises a first end which is provided with a ball joint connection passed through by a first hinge axis carried by the connection annulus and a second end connected to the root of a stator vane according to an embedded connection.

4 . The module according to claim 1 , wherein the at least one lever is held by a support secured to the stationary casing and is pivotally connected to the support.

5 . The module according to claim 1 , wherein the at least one lever has an L shape with a first branch and a second branch comprising respectively a first and a second distal end, the first distal end of the first branch is connected in a pivot connection with an axial rod of the first movable body of the first control means, and the second distal end of the second branch comprises a ball joint through which passes a second hinge axis carried by the connection annulus.

6 . The module according to claim 1 , wherein the first pitch change system comprises two first control means and two levers connected respectively to the first control means and to the connection annulus.

7 . The module according to claim 1 , wherein the first pitch change system is installed in an annular space of an external casing partly delimiting a primary duct in which a primary air flow circulates.

8 . The module according to claim 7 , wherein the external casing carries a splitter nose and the first control means are arranged at the level of the splitter nose.

9 . The module according to claim 1 , wherein the stator vanes are configured to pivot between −10° and +10°.

10 . The module according to claim 1 , wherein the connection annulus is unique.

11 . The module according to claim 1 , further comprising a second pitch change system for changing the pitch of the movable blades of the propeller which comprises:
a second control means comprising a second body axially movable with respect to a second stationary body mounted on an internal casing, the movable blades being mounted on a rotating casing carried by the internal casing; at least one load transfer bearing comprising an internal ring connected to the second movable body and an external ring; and a second mechanism for connecting the external ring to the blades of the propeller.

12 . The module according to claim 11 , wherein the internal casing and the external casing delimit, at least partly, a primary duct in which a primary air flow circulates.

13 . An aircraft turbomachine comprising at least one module according to claim 1 and a gas generator intended to drive the unducted propeller in rotation.

Assignees

• Safran Aircraft Engines

Inventors

• Lima Christophe

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• B64C11/32

  mechanical · CPC title

• F05D2260/74

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

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title

• F01D17/141 Primary

  by means of shiftable members or valves obturating part of the flow path · CPC title