Method for processing rotor blade-shaped surface dustpan hole structure and dustpan hole structure
A rotor blade and processing method technology, applied in the field of aero-engine blade cooling structure design, can solve the problems of inconsistency in air film coverage of dustpan holes, increased processing complexity and processing costs, and large differences in air film holes. The effect of production cycle, saving processing cost and improving consistency
Active Publication Date: 2021-03-30
AECC SHENYANG ENGINE RES INST
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[0003] However, for rotor blades with complex profiles, when the same exhaust film hole is processed with a set of structural parameters, the processed air film holes are quite different, such as figure 2 As shown, L1 and L1' are quite different, which leads to inconsistencies in the air film coverage of dustpan holes in different positions; under normal circumstances, the value of b is basically unchanged, and adjusting the angle a (tool angle) can make the air film holes achieve better consistency , but this will lead to changing a processing tool for each air film hole, which greatly increases the complexity of the processing technology and processing cost; when the curvature of the blade surface changes greatly, there will also be certain The difference (long and short side), deviates from figure 1 Middle (right) ideal dustpan hole shape, such as figure 2 Shown L1>L2
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[0023] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with th...
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The invention discloses a rotor blade profile dustpan hole structure machining method. The machining method comprises following steps that a reversed tool is adopted, and a first dustpan hole in pre-machined dustpan holes, on the same row, of a rotor blade profile is selected; before feeding, the feeding direction of the reserved tool is adjusted to form a first reserved angle r with the bottom hole axis of the first dustpan hole; the reserved tool is adjusted to rotate around the bottom hole center line by the second reserved angle c, and it is ensured that the lengths of two sides of the first dustpan hole are equal; and feeding is performed, the reserved depth of the feeding depth is b, and machining of the first dustpan hole is finished. The invention further discloses a dustpan hole structure. According to the rotor blade profile dustpan hole structure machining method and the dustpan hole structure, matching design of dustpan holes in different positions and the profile can be achieved, the consistent dustpan hole side lengths are achieved, and consistency of cooling effect of same-row dustpan hole air films can be improved.
Description
technical field [0001] The application belongs to the field of aeroengine blade cooling structure design, and in particular relates to a method for processing a dustpan hole structure of a rotor blade profile and a dustpan hole structure. Background technique [0002] Air film cooling is an important means to reduce the surface temperature of the blade and improve cooling efficiency. The application of the dustpan hole makes the cold air flowing out of the air film hole have a better effect of sticking to the wall and covering the air film. Therefore, the dustpan hole has been widely used in high-pressure turbine guides. blades and rotor blades. At present, most of the dustpan holes are processed in the form of electric discharge machining. The dustpan holes and bottom holes of the existing structure are designed tangentially, that is, the knife is fed along the axis of the air film hole during EDM; in order to facilitate the process and save processing costs , often the sa...
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IPC IPC(8): B23H11/00B23H9/14
CPCB23H9/14B23H11/00
Inventor 周丽敏张志强曾令玉
Owner AECC SHENYANG ENGINE RES INST