Template used for measuring thickness of wall of high pressure turbine blade and application thereof
A technology for high-pressure turbines and blades, applied to measuring devices, using ultrasonic/sonic/infrasonic waves, instruments, etc., can solve the problem of inability to accurately determine the wall thickness measurement point, the complex structure of the high-pressure turbine blade inner cavity, and the inability to ensure accurate wall thickness values Sexuality and other issues, to reduce the number of returns to the factory, ensure the production progress of overhaul, and achieve the effects of major social and economic benefits
Inactive Publication Date: 2014-02-05
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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Problems solved by technology
Due to the complexity of the blade basin and blade back profile of the high-pressure turbine blade, there is no obvious reference point in the measurement process; and the structure of the inner cavity of the high-pressure turbine blade is complex, and it is impossible to accurately determine the wall thickness measurement point by relying on general measurement methods, and the measurement accuracy cannot be guaranteed. Accuracy of Wall Thickness Values
Method used
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Embodiment Construction
[0023] Such as figure 1 with 2 As shown, a template for measuring the wall thickness of a high-pressure turbine blade, the template includes a leaf pot template and a blade back template; the leaf pot template includes a template-1, a hook-2 and a positioning block-3, the The profile of the template-1 is based on the coordinate point of the blade pot profile of the standard high-pressure turbine blade, and is processed according to the curvature of the blade pot profile of the standard high-pressure turbine blade. The profile of the template-1 It can closely fit with the blade basin profile of the standard high-pressure turbine blade; the hook-2 is provided at the end of the template-1 attached to the inlet edge 9 of the standard high-pressure turbine blade, and the hook-1 2 can be attached to the blade back 8 of the standard high-pressure turbine blade; the lower end of the template-1 is provided with the positioning block-3, and the positioning block-3 is attached to the e...
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The invention relates to a template used for measuring the thickness of the wall of a high pressure turbine blade and application of the template. According to the technical scheme, the template used for measuring the thickness of the wall of the high pressure turbine blade comprises a concave blade template and a convex blade template; the concave blade template comprises a first shaping plate, a first clamping hook and a first positioning block, and the convex blade template comprises a second shaping plate, a second clamping hook and a second positioning block. According to the template, a wall thickness measuring point of a concave blade of the high pressure turbine blade and a wall thickness measuring point of a convex blade of the high pressure turbine blade can be determined, the thickness of the wall of the high pressure turbine blade can be accurately measured with the template, and the measured thickness of the wall is compared with a standard value to determined whether the high pressure turbine blade is qualified or not.
Description
technical field [0001] The invention relates to a measuring template, in particular to a template for measuring the wall thickness of a high-pressure turbine blade and its application. Background technique [0002] After working for a certain period of time, the aeroengine needs to be repaired. It is particularly important to repair high-pressure turbine blades during maintenance. High-pressure turbine blades such as image 3 As shown, its part names are leaf pot, leaf back, air intake edge, edge plate, and the leaf pot is behind the leaf back. When repairing, the blade basin and blade back of the high-pressure turbine blade whose seepage layer exceeds the standard are removed by pickling. After large-scale removal, the residual seepage layer on the surface of the blade basin and blade back of the high-pressure turbine blade relies on local grinding and polishing. method to remove. According to technical requirements, ultrasonic measurement must be carried out on the blade...
Claims
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IPC IPC(8): G01B17/02
Inventor 于萍常敏张德权
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION