Impeller positioning structure and impeller blade fatigue test device
A positioning structure and impeller technology, applied in the field of aero-engines, can solve problems such as fatigue damage of other blades, and achieve the effect of avoiding energy loss
Active Publication Date: 2020-08-11
AECC HUNAN AVIATION POWERPLANT RES INST
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Problems solved by technology
[0003] The disclosure provides an impeller positioning structure and an impeller blade fatigue test device to solve the problem in the prior art that fatigue damage to other blades may be caused during the high-cycle fatigue test of the overall impeller blade
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[0033] Typical embodiments that embody the features and advantages of the present disclosure will be described in detail in the following description. It should be understood that the present disclosure can have various changes in different embodiments without departing from the scope of the present disclosure, and that the description and drawings therein are illustrative in nature and not intended to limit the present disclosure. public.
[0034] In the following description of various exemplary embodiments of the present disclosure, reference is made to the accompanying drawings, which form a part hereof, and in which are shown by way of example various exemplary structures, systems and procedures that may implement aspects of the present disclosure . It is to be understood that other specific arrangements of components, structures, exemplary devices, systems and steps may be utilized and structural and functional modifications may be made without departing from the scope ...
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The invention relates to the technical field of aero-engines, and provides an impeller positioning structure and an impeller blade fatigue test device, the impeller positioning structure is used for fixing an impeller, the impeller comprises a test blade and a non-test blade, the impeller positioning structure comprises a mounting base and a fixing ring piece, and the impeller is fixedly arrangedon the mounting base; the fixing ring piece is provided with a containing cavity used for containing the impeller, an opening is formed in the fixing ring piece, and the test blades are opposite to the opening and spaced from the fixing ring piece; the fixed ring piece comprises an elastic ring, and the elastic ring is used for being in limiting contact with the non-test blade so as to limit the non-test blade to move relative to the fixed ring piece. The test blades of the impeller are suspended, and the non-test blades are fixedly arranged, so that fatigue damage of the non-test blades cannot be caused in the high-cycle fatigue test process of the blades of the integral impeller, and the problem that fatigue damage of other blades can be caused in the high-cycle fatigue test process of the blades of the integral impeller in the prior art is solved.
Description
technical field [0001] The disclosure relates to the technical field of aero-engines, in particular to an impeller positioning structure and an impeller blade fatigue test device. Background technique [0002] The working environment of aeroengine blades is harsh. During the entire life cycle of aeroengines, fatigue cracks often occur on the blades. Therefore, it is necessary to conduct high-cycle fatigue tests on the blades to assess whether they meet the strength and vibration design requirements. Usually, the high cycle fatigue test of the blade can be divided into the high cycle fatigue test of a single blade and the high cycle fatigue test of the whole impeller blade. The high-cycle fatigue test of a single blade first needs to cut the whole blade disk, which will inevitably change the original working state of the blade. The whole blade disc is taken as the research object, that is, the high cycle fatigue test is carried out on the blade on the whole blade disc withou...
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IPC IPC(8): G01M15/14
CPCG01M15/14
Inventor 边杰郑锦妮陈亚农徐友良
Owner AECC HUNAN AVIATION POWERPLANT RES INST