A positioning correction method for turbine blade film cooling holes
نویسندگان
چکیده
Abstract It is significant to improve the machining accuracy of film cooling holes on aero-engine turbine blades. This paper presents a method correct position In this method, pre-positioning algorithm and precise positioning are proposed. The introduces blade structure information. algorithm, 3D coordinate transformation, ∠B ∠C 5-axis machine tool updating, iteration points creating based normal vector designed. operation gas hole correcting by given. Experiment shows that, after 7 iterations, error reduced 0.0344mm, achieving high-precision Furthermore, coordinates corrected realize holes, which can performance
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ژورنال
عنوان ژورنال: Journal of physics
سال: 2022
ISSN: ['0022-3700', '1747-3721', '0368-3508', '1747-3713']
DOI: https://doi.org/10.1088/1742-6596/2365/1/012008