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Plain self-centering bearing

An inner surface and outer surface technology, applied in the field of deceleration transmission, can solve the problems of increasing the complexity and cost of the system, regardless of the real state of the system, and achieve the effects of reducing vibration, increasing energy efficiency and prolonging life.

Active Publication Date: 2017-08-01
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0013] In general, however, this uneven distribution of oil is either a static correction, which therefore does not take into account the real state of the system, or a dynamic correction which requires the provision of sensors, actuators and electronic controllers so that Significantly increases system complexity and cost

Method used

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  • Plain self-centering bearing
  • Plain self-centering bearing
  • Plain self-centering bearing

Examples

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Embodiment Construction

[0054] In order to make the present invention more concrete, exemplary transmission members are described in detail below with reference to the accompanying drawings. It should be kept in mind that the present invention is not limited to this embodiment.

[0055] figure 1 A bypass turbojet engine with a reduction transmission as described in the introduction and comprising a transmission member 3 of the invention is shown.

[0056] The transmission member 3 comprises similar to that referenced in the introduction figure 2 The planetary gear train 30.

[0057] It should be noted in particular that in this embodiment the ring 31 is fixed to the housing 60 via a flexible shroud 61, the planet carrier 35 is connected to the fan shaft 2a in order to drive the fan 2 by a rigid connection, and the sun gear 32 is flexibly connected to The fluted end 10 a of the low pressure shaft 10 .

[0058] In this embodiment of the invention, and as image 3 , Figure 4A with Figure 4B As...

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Abstract

The present description relates to a mechanical assembly of two mechanical components rotating one with respect to the other making it possible to obtain a self-centring fluid bearing. The mechanical assembly comprises a first component provided with a cylindrical cavity; a second component (34) comprising at least one cylindrical portion engaged in the cylindrical cavity of the first component; a space separating the cylindrical portion and the wall of the cylindrical cavity so as to allow relative movement of rotation between the first and the second component (34); and a lubricant distribution network (37, 38) configured to supply the gap with a fluid lubricant so as to form a fluid bearing. A first surface (34s) out of the lower surface of the cylindrical cavity of the first component and the outer surface of the cylindrical portion of the second component is equipped with at least two lubricant inlet orifices (39a, 39b) distant from one another by more than 120 degrees about the main axis (F) of the first surface (34s), and the first surface (34s) also has at least one circumferential groove (40a) extending circumferentially, in the direction of relative rotation of the second of the surfaces with respect to the first surface (34s), from the vicinity of a first lubricant inlet orifice (39a) over at least 100 degrees.

Description

technical field [0001] The present disclosure relates to a mechanical assembly of two mechanical parts, which rotates one mechanical part relative to the other, making it possible to obtain a self-centering fluid bearing. [0002] Such mechanical assemblies are particularly useful within transmission members of the planetary gear train type, for example. In particular, such an invention may find application in the field of aeronautics, in aircraft turbojets or helicopter turboshafts: it may in particular be applied to the reduction gears of those turbojets with transmissions. Background technique [0003] Today, the turbojet engine commonly found in civil aviation is the twin-rotor bypass turbojet. However, due to increasing constraints on operating costs, which are closely related to today's very high fuel costs, new projects have been proposed for turbojet engines which benefit from a smaller specific consumption . [0004] A potential option consists in installing a tu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16C17/02F16C33/10
CPCF16C17/02F16C33/1055F16C33/1065F16C33/1085F16C2360/23F16C2361/61F16C2240/42F16C3/02F16C32/06F16C33/10F16H57/08F01D11/00F01D11/04F16C32/00F16C32/067F16J15/00F16J15/342F01L11/00
Inventor 瑟奇·雷内·莫莱利
Owner SAFRAN AIRCRAFT ENGINES SAS