Clamping device for checking fatigue property of high-pressure turbine blade of aero-engine
A technology for aero-engines and high-pressure turbines, which is applied in the direction of measuring devices, strength characteristics, and the use of applied repetitive force/pulsation force to test the strength of materials, etc. It can solve problems such as blade tenon tooth breakage, impossibility of testing, and inability to accurately evaluate blade strength performance. , to achieve the effect of correctly evaluating the strength performance and solving the problem of tenon tooth fracture
Inactive Publication Date: 2018-03-13
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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However, in the actual fatigue assessment test, the tenon teeth of the blade frequently broke, which made it impossible to carry out the test, so that the strength performance of the blade could not be accurately evaluated, which seriously affected the smooth progress of scientific research and production tasks
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[0010] The present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments, which are explanations rather than limitations of the present invention.
[0011] Such as figure 2 As shown, the specific embodiment of the present invention provides a clamping device for the fatigue performance assessment of high-pressure turbine blades of aero-engines, including a base 1, a clamping block 3, an upper pressing block 4 and a lower pressing block 5; the base 1 is provided with a gantry 2; the clamping block 3 is used to clamp the high-pressure turbine blade of the aero-engine and placed in the gantry 2, and a compression bolt 6 is also arranged above the clamping block 3; the upper pressing block 4 and the The lower pressing block 5 is respectively placed at the upper edge plate 10 and the lower edge plate 11 of the high-pressure turbine blade of the aero-engine, and plays the role of stabilizing the upper edge plate 1...
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The invention provides a clamping device for checking fatigue property of a high-pressure turbine blade of an aero-engine. The clamping device comprises a base, a clamping block, an upper pressing block and a lower pressing block, wherein the base is provided with a gantry, the clamping block is used for clamping a high-pressure turbine blade of the aero-engine and putting into the gantry, a firstcompression bolt is further arranged above the clamping block, the upper pressing block and the lower pressing block are respectively arranged on an upper margin plate and a lower margin plate of thehigh-pressure turbine blade of the aero-engine to achieve an effect of stabilizing the upper margin plate and the lower margin plate, a second compression bolt is further arranged above the upper pressing block, the first compression bolt and the second compression bolt respectively penetrate through the upper end of the base, and the base is provided with six fixed bolts at the lower end for being connected with an electromagnetic vibrating table. The clamping device disclosed by the invention fundamentally solves the problem that tenon tooth are frequently broken in a process of checking fatigue property of the high-pressure turbine blade of the aero-engine, so that strength performance of the blade can be accurately evaluated.
Description
technical field [0001] The invention belongs to the technical field of strength testing of aero-engines, and in particular relates to a clamping device for evaluating the fatigue performance of high-pressure turbine blades of aero-engines. Background technique [0002] A large number of fatigue performance assessment tests are required in the development and production of aeroengine compressors and turbine blades. However, in the actual fatigue assessment test, the tenon teeth of the blade frequently broke, which made it impossible to carry out the test, so that the strength performance of the blade could not be accurately evaluated, which seriously affected the smooth progress of scientific research and production tasks. Therefore, it is urgent to design a blade clamping device to assist in completing related fatigue performance tests. Contents of the invention [0003] The invention provides a clamping device for fatigue performance assessment of high-pressure turbine b...
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IPC IPC(8): G01N3/04G01N3/38
CPCG01N3/04G01N3/38G01N2203/005G01N2203/0073G01N2203/04
Inventor 范秀杰刘涛张荫鳌经留洋冯喆
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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