Parametric machining method of air film cooling holes for precision casting turbine blades

Abstract

A parametric machining method of air film cooling holes for precision casting turbine blades relates to turbine blades. The method provides errors including casting deformation of components, positioning errors of clamps, and blade movement and deformation during small hole machining so as to achieve parametric accurate machining of hollow turbine blade air film holes. Through solving and calculating propagation and accumulation of error during air film machining, correcting design parameters of air film holes and processing the air film holes according to air film hole shape and location parameters which are the center point of the film hole, the normal of the film hole, and the hole depth of the air film hole after correction, the processing accuracy of the air film holes is increased and the cooling efficiency of turbine blades is increased. This method has important theoretical significance and application value for precise forming of hollow turbine blade, avoids the present situation of air cooling efficiency reduction in the field of air film hole processing, ensures the precision of air film hole forming and achieves the air cooling effect consistent with the design requirements.

Description

technical field [0001] The invention relates to a turbine blade, in particular to a parametric processing method for a precision casting turbine blade air film cooling hole. Background technique [0002] Turbine blades are the key parts of aero-engines. In order to enable them to serve reliably for a long time under the conditions of strong thermal shock and complex cyclic thermal stress, effective cooling measures must be adopted. Among them, film cooling technology has been widely used as an effective means to improve the temperature bearing capacity of blades. [0003] Air film cooling is to design a large number of tiny holes arranged linearly on the curved surface of the hollow blade. Using the cold air released inside the turbine, a thin layer of cold air film is formed on the surface of the blade through several rows of tiny holes with a diameter of 0.3-0.8mm to achieve isolation. The purpose of protecting blades from high temperature gas flow. The film cooling effi...

AI Technical Summary

Problems solved by technology

[0009] In order to overcome the problem that the shape and position parameter changes cannot be accurately described in the existing air film hole processing process, resulting in low forming accuracy and unstable quality of the air film hole, the present invention provides components including casting deformation, clamping positioning error And the error including the movement and deformation of the blade during the processing of the small hole can realize the parameterized and precise machining of the air film hole of the hollow turbine blade. A parametric processing method for the air film cooling hole of the precision casting turbine blade

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