Integrated bearing supporting structure used for aviation engine

An aero-engine and bearing support technology, which is applied to the rigid support of bearing components, bearing elements, shafts and bearings, etc., can solve the problems of complex structure of bearing fulcrum components, increased weight of bearing support structure, and increased number of assembly parts, etc., to achieve optimization Axial arrangement, reduced number of parts, and reduced occupied space

Inactive Publication Date: 2016-03-30
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the problem brought by such a technical solution is that the structure of the bearing fulcrum assembly becomes complicated, the number of assembly parts increases, and the weight of the bearing support structure also increases
[0003] For example, if figure 1 As shown, in a typical double bearing support scheme, the rotor axial force and radial force borne by the ball bearing 4 and the roller bearing 5 are reasonably distributed, which greatly improves the working environment of the bearing, but the bearing support structure can be seen It also becomes more complicated, requiring independent ball bearing support structure 11 and independent roller bearing support structure 12, increasing the number of parts

Method used

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  • Integrated bearing supporting structure used for aviation engine
  • Integrated bearing supporting structure used for aviation engine
  • Integrated bearing supporting structure used for aviation engine

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Embodiment Construction

[0044] The present invention will be further described below in conjunction with specific embodiment and accompanying drawing, set forth more details in the following description so as to fully understand the present invention, but the present invention can obviously be implemented in many other ways different from this description, Those skilled in the art can make similar promotions and deductions based on actual application situations without violating the connotation of the present invention, so the content of this specific embodiment should not limit the protection scope of the present invention.

[0045] figure 2 It is the installation schematic diagram of the integrated bearing support structure for aero-engine of the present invention. Fig. 3(a) is a cross-sectional view of an integrated bearing support structure for an aero-engine according to an embodiment of the present invention. Fig. 3(b) is a perspective view of an integrated bearing support structure for an ae...

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Abstract

The invention relates to an integrated bearing supporting structure for an aviation engine. The integrated bearing supporting structure comprises a mounting edge, a first bearing supporting spoke, a second bearing supporting spoke, a first bearing supporting seat and a second bearing supporting seat, one end of the first bearing supporting spoke is connected to the mounting edge, the other end of the first bearing supporting spoke is connected to the first bearing supporting seat, one end of the second bearing supporting spoke is connected to the mounting edge, the other end of the second bearing supporting spoke is connected to the second bearing supporting seat, the first bearing supporting seat is used for supporting a first bearing, the second bearing supporting seat is used for supporting a second bearing, and the quantity of the mounting edge is 1. The integrated bearing supporting structure for an aviation engine has the advantages of part quantity reduction, occupied space reduction, reduced weight, and convenience for dismounting and maintaining.

Description

technical field [0001] The present invention relates to an integrated bearing support structure for an aeroengine. Background technique [0002] In aero-engines, the combination of two or more bearings at the same fulcrum can improve the working environment of the bearing and increase the life of the bearing. One of the bearings bears more axial force, and the other bearing bears more radial force. Such a technical solution greatly improves the working environment and life of the bearing. However, the problem brought by such a technical solution is that the structure of the bearing fulcrum assembly becomes complicated, the number of assembly parts increases, and the weight of the bearing support structure also increases. [0003] For example, if figure 1 As shown, in a typical double bearing support scheme, the rotor axial force and radial force borne by the ball bearing 4 and the roller bearing 5 are reasonably distributed, which greatly improves the working environment o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16C35/06
Inventor 娄俊岭彭刚王少波李敏王秋阳
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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