Device for lubricating a power gearbox with a variable orientation, particularly for a convertible tilt-rotor aircraft

• US 6,691,830 B2
• Filed: 09/24/2001
• Issued: 02/17/2004
• Est. Priority Date: 09/25/2000
• Status: Expired due to Term

• Current Assignee: Airbus Helicopters
• Original Assignee: Eurocopter
• Inventors: Thomassey, Lionel, Blanc, Maurice
• Primary Examiner(s): Bucci, David A.
• Assistant Examiner(s): VAN PELT, BRADLEY J
• Application Number:
  US09/960,392
• Publication Number:
  US 20020036119A1
• Time in Patent Office: 876 Days
• Field of Search: 184/6.2, 244/12.4, 244/17.25, 244/56, 415/72
• US Class Current: 184/6.2
• CPC Class Codes: B64C 27/12 Rotor drives
• CPC Class Codes: F16H 57/0421 on or within the casing, e.g. shields or baffles for collecting lubricant, tubes, pipes, grooves, channels or the like
• CPC Class Codes: F16H 57/0434 relating to lubrication supply, e.g. pumps arrangement of pumps F16H57/0441; Pressure control grooves with pumping effect for supplying lubricant F16H57/0428; generation and variation of line pressure for transmission control F16H61/0021

Abstract

A device for lubricating a power gearbox having a variable orientation and a closed space has a lubricating unit that supplies lubricant to at least one element of the gearbox, which needs to be lubricated. A collecting reservoir collects lubricant from the closed space. A drain screw chamber, within the closed space, has a number of orifices disposed between different zones of the closed space and the drain screw chamber for passing lubricant there between. At least one rotary drain screw, which is produced in the form of an Archimedean screw, is disposed in the drain screw chamber to convey the lubricant from the drain screw chamber to the collecting reservoir. A drive unit drives the drain screw in rotation for conveying the lubricant. The orifices open respectively different zones of the closed space to the drain screw chamber such that the drain screw chamber can always collect lubricant from the different zones regardless of the orientation of the gearbox.

Claims

1. A device for lubricating a power gearbox having a variable orientation and comprising a closed space, said lubricating device comprising:

lubricating means for supplying lubricant to at least one element of said gearbox that needs to be lubricated;

a collecting reservoir for collecting lubricant from said closed space;

at least one rotary drain screw member, which includes an Archimedean drain screw, equipped with a number of orifices and which is arranged in said closed space to convey lubricant from said closed space to said collecting reservoir, wherein said orifices are made in the drain screw member and are facing respectively different zones of said closed space such that said drain screw can always collect lubricant from said closed space regardless of the orientation of said gearbox; and

drive means for driving said drain screw in rotation.

2. The lubricating device as claimed in claim 1, wherein said drain screw is at least partially made of synthetic material.

3. The lubricating device as claimed in claim 1, wherein said drive means act on said drain screw by means of gears made of synthetic material.

4. The lubricating device as claimed in claim 1, wherein said orifices are fitted with magnetic plugs, intended to collect metallic contaminants found in the lubricant.

5. A transmission system for the transmission of power between a drive motor and a tilt rotor, which is capable of tilting between a first position in which it is capable of operating as a rotary wing, and a second position in which it is capable of operating as a propeller, said transmission system comprising a tilting reduction assembly:

which is produced in the form of a gearbox;

which is connected to a non-tilting reduction assembly connected to a shaft of said motor; and

which drives said rotor,

wherein said gearbox of the tilting reduction assembly comprises at least one lubricating device as specified in claim 1.

6. A convertible tilt-rotor aircraft capable of operating in airplane mode and in helicopter mode and comprising at least one fuselage, a fixed wing structure comprising at least two wings extending laterally one on each side of said fuselage and, in helicopter mode, a rotary wing structure comprising at least two rotors which in airplane mode act as propellers and each of which is mounted so that it can tilt on a respective fixed wing and is connected, by a respective transmission system, to a respective motor supported by the corresponding wing,

wherein at least one of said transmission systems is the one specified in claim 5.