US 10,502,088 B2Granted

Mechanism for driving members for adjusting the orientation of blades

AssigneeSafran Aircraft Engines

InventorPierre-Alain Francis Claude Sebrecht

Life of this patent

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Abstract

A drive mechanism (10) for driving a first adjustment member (12) for adjusting the orientation of the blades (14) of a first turbomachine rectifier stage (16) and a second adjustment member (18) for adjusting the orientation of the blades (20) of a second turbomachine rectifier stage (22), which comprises a mechanism for simultaneously moving the two adjustment members (12, 18) in the turbomachine, characterised in that it comprises a single drive wheel (24) that simultaneously drives the first adjustment member (12) and the second adjustment member (18) and comprises two gear stages (26, 28) that are arranged between the drive wheel (24) and one or the other of the first adjustment member (12) and the second adjustment member (18) and that have different transmission ratios.

Claims9

Dependent claims

A drive mechanism for driving a first adjustment member for adjusting an orientation of a first set of blades of a first turbomachine splitter stage and a second adjustment member for adjusting an orientation of a second set of blades of a second turbomachine splitter stage, which includes means for simultaneously driving both first and second adjustment members into movement in a turbomachine,

wherein the drive mechanism includes a single drive wheel which simultaneously drives the first adjustment member and the second adjustment member and includes a first gear stage and a second gear stage which are arranged between the drive wheel and either of the first adjustment member and the second adjustment member and which have different transmission ratios, and
wherein the transmission ratio of the second gear stage associated with the second adjustment member varies as a function of an angular position of the drive wheel in the turbomachine.

Dependencies are inferred from the claim text.

Facts

Application: 15/508,751Filed 3 Sep 2015
Priority: FR 14 583445 Sep 2014
Published: US 2017/0260870 A114 Sep 2017
Granted: 10 Dec 2019
Term ends: Not estimatedThe source records don’t support an estimate.

Classification8 codes

F01D 17/162
By means of nozzle vanes: for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
F04D 29/563
Adjustable: specially adapted for elastic fluid pumps
F05D 2220/323
In gas turbines: for aircraft propulsion, e.g. jet engines
F05D 2260/4031
Through the shape of the drive components: as in toothed gearing

Family

US 2017/0260870 A1Pre-grant publication · published 14 Sep 2017
US 10,502,088 B2This patent

From the US filing history. Foreign family members aren’t listed.

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