Impeller positioning structure and impeller blade fatigue test device
A technology of positioning structure and impeller, applied in the field of aero-engine, can solve the problems of fatigue damage of other blades, and achieve the effect of avoiding energy loss
Active Publication Date: 2021-11-09
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 disclosure relates to the technical field of aero-engines, and proposes an impeller positioning structure and an impeller blade fatigue test device. The impeller positioning structure is used to fix the impeller. The impeller includes test blades and non-test blades. The impeller positioning structure includes a mounting seat and a fixing ring. The impeller is fixedly arranged on the mounting seat; the fixed ring has an accommodating chamber for accommodating the impeller, the fixed ring is provided with an opening, and the test blade is arranged opposite to the opening and spaced apart from the fixed ring; wherein the fixed ring includes an elastic The elastic ring is used to limit the contact with the non-test blade to limit the movement of the non-test blade relative to the fixed ring. By setting the test blades of the impeller in the air and fixing the non-test blades, the fatigue damage of the non-test blades will not be caused during the high-cycle fatigue test of the integral impeller blades, which solves the problem of the overall impeller blades in the prior art. Other blade fatigue damage problems will be caused during the high cycle fatigue test.
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...
Claims
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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