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Device for centring and rotationally guiding turbomachine shaft comprising means for axial retention of outer ring of bearing

A turbine shaft and rotating ground technology, which is applied in the direction of rotating bearings, shafts and bearings, turbine/propulsion device lubrication, etc., can solve problems such as the risk of material picking up, eliminate the risk of scrapping, simplify processing, and improve accuracy. Effect

Active Publication Date: 2020-01-03
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0025] Further, the embedding of the pin 60 on the finished part requires the operator to be careful not to damage the rolling bearing by contaminating it, especially because of the risk of material pick-up when embedding the pin 60

Method used

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  • Device for centring and rotationally guiding turbomachine shaft comprising means for axial retention of outer ring of bearing
  • Device for centring and rotationally guiding turbomachine shaft comprising means for axial retention of outer ring of bearing
  • Device for centring and rotationally guiding turbomachine shaft comprising means for axial retention of outer ring of bearing

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Embodiment Construction

[0059] It should be noted that in the specification, the directions of "upstream" and "downstream" are defined relative to the overall airflow direction, which is parallel to the axis 13 of the shaft 12 corresponding to the axis of the turbine, "inward" and "outward" The direction of is defined relative to the axis 13.

[0060] Figure 1~3 It has been described in the part related to the prior art and the technical content of the present invention.

[0061] Now according to Figure 4 ~ Figure 8 An example of the device 10 for centering and rotating the guiding of the turbine shaft 12 of the present application is described. It should be noted that the description in the aforementioned document Figure 1~3 The elements mentioned in the related part of the prior art and the technical content of the present invention will not be described again. Of course, in addition to the retaining device with retaining ring 72 and pin 60 specifically used in the prior art, the previous combinatio...

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Abstract

The main subject of the invention is a device (10) for centering and rotationally guiding a turbomachine shaft (12), comprising: a rolling bearing comprising an outer ring (18), a bearing mount (20),a band (28) interposed between the outer ring (18) and the bearing mount (20) and means (29) for connecting the outer ring (18) to the bearing mount (20), characterized in that it comprises means forthe axial retention of the outer ring (18) comprising an axial thrust flange (100) downstream of and in contact with the fixing flange (30) of the connecting means, and comprising a fixing hole (101)for fixing together the fixing flange (30), the bearing mount (20) and the axial thrust flange (100), which latter further comprises a lug (103) extending between two successive tabs (34) of the elastically deformable means (32).

Description

Technical field [0001] The present invention relates to the field of turbomachines, and more specifically to equipment for centering and rotationally guiding a turbomachine shaft, which includes bearings commonly referred to as "flexible ring bearings". In this type of bearing, the device for connecting the bearing outer ring to the bearing bracket includes a fastening clip installed to the bearing bracket and an elastic deformation device that couples the bearing outer ring to the fastening clip. The invention is particularly suitable for bearings that are damped by an oil film (also called "squeeze film"). [0002] The present invention is applicable to any type of ground or aerospace turbines, in particular, to aircraft turbines, such as jet turbine engines and propeller turbine engines. More preferably, the present invention is applicable to a dual-flow dual-spool turbofan engine. Background technique [0003] In the turbine, the occurrence of bearing frictional resistance ev...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D21/00F01D25/16F02C7/06F16C27/04
CPCF16C2360/23F01D21/00F01D25/162F02C7/06F16C27/045F01D25/164F05D2220/323F05D2230/64F05D2240/54F05D2260/30F16C23/08F16C27/066
Inventor 阿诺德·贝西劳伦·利德
Owner SAFRAN AIRCRAFT ENGINES SAS