Aircraft engine and fusing method of aircraft engine under loads caused by FOB (fan blade off)

A technology of aero-engine and fan blades, which is applied in the direction of engine function, engine components, engine manufacturing, etc., can solve the problems of long fan blade radius, misalignment of fan center line and engine center line, and large mass, so as to achieve simplified structural design and high Structural design flexibility and the effect of improving design reliability

Active Publication Date: 2017-10-10
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For the high-bypass turbofan engines commonly used in commercial aircraft, the fan blades have long radius and high mass, and the FBO event will cause the center of gravity of the fan to be misaligned with the center line of the engine, causing huge unbalanced loads

Method used

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  • Aircraft engine and fusing method of aircraft engine under loads caused by FOB (fan blade off)
  • Aircraft engine and fusing method of aircraft engine under loads caused by FOB (fan blade off)
  • Aircraft engine and fusing method of aircraft engine under loads caused by FOB (fan blade off)

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Embodiment Construction

[0019] 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.

[0020] It should be noted that the drawings are only examples, and they are not drawn according to the same scale, and should not be taken as limitations on the protection scope of the actual claims of the present invention.

[0021] Such as figure 1 and figure 2 As shown, the aero-engine includes a fan rotor 100, a stator intermediary casing 9, a first bearing 3 and a second...

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Abstract

The invention provides a fusing structure and method of an aircraft engine under loads caused by FOB (fan blade off). The aircraft engine comprises a fan rotor, a stator piece intermediate case, a first bearing, a second bearing, a first supporting conical arm and a second supporting wall, wherein the fan rotor is supported by the first bearing and the second bearing, the first bearing is supported on the stator piece intermediate case through the first supporting conical arm, and the second bearing is supported on the stator piece intermediate case through the second supporting wall. The first supporting conical arm is of a thin-wall annular structure and comprises an upper conical arm body and a lower conical arm body. The upper conical arm body is provided with an upper combining surface. The lower conical arm body is provided with a lower combining surface. One of the upper combining surface and the lower combining surface is a concave spherical surface, and the other one is a convex spherical surface. The upper combining surface and the lower combining surface are complementary and are welded into the fusing structure with the strength lower than that of a parent material. The spherical center of the fusing structure is located at the axis of the fan rotor.

Description

technical field [0001] The invention relates to an aero-engine, in particular to a fusing structure and a fusing method of a bearing support structure of an aero-engine. Background technique [0002] The aircraft engine may be hit by foreign objects such as flying birds, causing one or more fan blades to break or fall off, that is, FBO (Fan Blade Off). After an FBO event, the center of gravity of the fan will deviate from the centerline of the low pressure rotor. However, the fan still rotates about the centerline of the low pressure rotor due to bearing constraints. Rotation of a fan about an axis offset from its center of gravity excites one or more modes of oscillation in the low pressure rotor system, creating unbalanced loads. For the high-bypass turbofan engines commonly used in commercial aircraft today, the fan blades have long radii and large masses. FBO events will cause the center of gravity of the fan to be misaligned with the centerline of the engine, causing ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D21/00F01D21/14F01D25/16F02C7/06
CPCF01D21/00F01D21/14F01D25/16F02C7/06F05D2260/15F01D21/045F05D2220/36F05D2230/236F01D21/08F01D25/162F05D2240/54F05D2250/711F05D2250/712F05D2250/241Y02T50/60
Inventor 柴象海韦勇王少辉宋会英侯亮
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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