Determination method for interference film hole machining angle

A technology of processing angle and determination method, applied in the direction of program control, instrument, computer control, etc., can solve problems such as unfavorable interference gas film hole processing

Active Publication Date: 2021-06-29
GUIYANG AVIC POWER PRECISION CASTING
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, at present, the angle conversion of the curved guide tube is mostly carried out by manual experience, and there is still a problem of large errors, which is not conducive to the processing of the interference gas film hole

Method used

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  • Determination method for interference film hole machining angle
  • Determination method for interference film hole machining angle
  • Determination method for interference film hole machining angle

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Embodiment

[0045] Such as Figure 1-Figure 4 As shown, this embodiment provides a method for determining the machining angle of the interference gas film hole.

[0046] By bending the linear guide according to a certain size and angle to form a curved guide, avoiding the interference area of ​​the turbine guide vane blade body or the mounting plate, the electrode wire can conduct electric sparks on the gas film hole along a certain curved track processing. Therefore, it is necessary to convert the machining angle of the machine tool according to the angle of the bending guide, so that it can be used for machining interference air film holes.

[0047] Since there is no mature product for the bending guide, it must be independently designed and prepared. Based on UG software and other design platforms, a specific curved guide model is designed on the three-dimensional modeling of turbine guide vanes. The bending guide should not only avoid the interference between the blade body and the...

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Abstract

The invention relates to a determination method for an interference film hole machining angle, and belongs to the technical field of aero-engine turbine blade machining. The determination method comprises the following steps that, a machine tool coordinate system (x, y, z) is established according to a position axis of a machine tool, a horizontal rotation axis of the machine tool serves as a B axis, and a vertical rotation axis of the machine tool serves as a C axis; according to the machine tool coordinate system (x, y, z), an initial coordinate of the interference air film hole and an initial coordinate of a bending guider are determined; and according to the initial coordinate of the interference film hole and the initial coordinate of the bending guider, when the B axis and the C axis are rotated to drive the interference film hole to rotate towards the bending guider, the rotation angle of the B axis and the rotation angle of the C axis are the machining angle of the interference film hole. According to the determination method, on the premise that the design performance of a turbine blade air cooling system is not reduced, shielding of a blade structure is effectively avoided, electric spark machining of the interference film hole is achieved, and therefore the design performance of an advanced aero-engine is met.

Description

technical field [0001] The invention belongs to the technical field of machining turbine blades of aero-engines, and in particular relates to a method for determining the machining angle of an interference gas film hole. Background technique [0002] The air film hole is a design structure used to reduce the thermal shock of the turbine blade at the hot end of the engine and increase the temperature limit of the turbine blade to ensure the stable operation of the turbine blade. Due to the complexity of the turbine blades, in order to achieve sufficient cooling effect, the design elements of the air film holes are often blocked with the blade structure, which is called interference air film holes. [0003] Interference gas film hole is a typical design feature of high temperature performance turbine blades. The center line of the gas film hole passes through the blade structure or is too close to the blade structure, which causes machining shielding and leads to traditional E...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23H9/14B23H1/00G05B19/408
CPCB23H9/14B23H1/00G05B19/4086
Inventor 谭其松赵前松贾敬惠王林伟张吉阳熊宗平代祥勇汪立白晓富李跃飞汤飞龙付秋伟龙再云郑兴林
Owner GUIYANG AVIC POWER PRECISION CASTING
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