Engine rotor blade disassembly equipment
A technology for rotor blades and engines, applied in the field of aero-engines, can solve the problems of large force dispersion of blades, easy existence of stress, blade crown damage, etc., and achieve the effect of improving the safety of parts and avoiding excessive impact force.
Active Publication Date: 2020-11-06
AECC SHENYANG ENGINE RES INST
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Problems solved by technology
[0002] In the prior art, the method of knocking on the edge plate is used for blade disassembly, which mainly has the following disadvantages: Potential safety hazard: the blade disassembly adopts the impact loading method of knocking and smashing, although a soft material tool such as a rubber hammer is used, However, if the knocking load is too large, it may still cause deformation of the edge plate or other damage; Wrong teeth on the blade crown: When the operator knocks, the blade is subjected to rapid impact, and the adjacent blades may move different axial distances. When it is too large, the blade crown will be misaligned. At this time, not only the damage to the blade crown may be caused, but also the required re-assembly work will also reduce the work efficiency; Assembly quality: due to the large force dispersion of the blade under the knocking method, the assembly The state is unstable, and the internal stress is easy to exist, which will affect the assembly quality to a certain extent
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[0019] The application will be further described in detail below with reference to the drawings and embodiments. It is understandable that the specific embodiments described here are only used to explain the related application, but not to limit the application. In addition, it should be noted that for ease of description, only the parts related to the present application are shown in the drawings.
[0020] It should be noted that the embodiments in the application and the features in the embodiments can be combined with each other if there is no conflict. Hereinafter, the present application will be described in detail with reference to the drawings and in conjunction with embodiments.
[0021] It should be noted that in the description of this application, the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. The term of the indicated direction or positional relationship is based on the direction or positional relationship shown...
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The invention provides engine rotor blade disassembling and assembling equipment. The equipment comprises a chassis; a blade support ring fixedly connected with the chassis; a center shaft, which is perpendicular to the chassis and is arranged at the center of the chassis; a rotor supporting disk movably disposed on the central shaft and can reciprocate along an extending direction of the centralaxis; and a blade assembling and disassembling component arranged on the central shaft and can rotate by taking the central shaft as a center.
Description
Technical field [0001] The application relates to the technical field of aeroengines, and specifically provides an engine rotor blade disassembly equipment. Background technique [0002] In the prior art, the blade assembly and disassembly adopt the method of knocking the edge plate, which mainly has the following disadvantages: safety hazards: the disassembly and assembly of the blade adopts the impact loading method of knocking, although the soft material tool such as a rubber hammer is used, However, if the percussion load is too large, it may still cause deformation of the edge plate or other damage; wrong teeth on the crown: When the operator performs percussion, the blade is quickly impacted, and adjacent blades may move different axial distances. When the distances are different When it is too large, the blade crown will have wrong teeth. At this time, it may not only cause damage to the blade crown and the required re-assembly work also reduces the work efficiency; assemb...
Claims
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IPC IPC(8): H02K15/02
CPCH02K15/0006H02K15/02
Inventor 杨洋龙洋孙贵青
Owner AECC SHENYANG ENGINE RES INST