CN109551068B - Machining method for dustpan hole structure with rotor blade profile and dustpan hole structure - Google Patents
Machining method for dustpan hole structure with rotor blade profile and dustpan hole structure Download PDFInfo
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- CN109551068B CN109551068B CN201811543808.9A CN201811543808A CN109551068B CN 109551068 B CN109551068 B CN 109551068B CN 201811543808 A CN201811543808 A CN 201811543808A CN 109551068 B CN109551068 B CN 109551068B
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- dustpan
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
- B23H11/00—Auxiliary apparatus or details, not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
- B23H9/00—Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
- B23H9/14—Making holes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Perforating, Stamping-Out Or Severing By Means Other Than Cutting (AREA)
Abstract
The application discloses rotor blade profile dustpan hole structure processing method includes following step: selecting a first dustpan hole in the same row of preprocessed dustpan holes on the molded surface of the rotor blade by adopting a preset cutter; before feeding, adjusting the feeding direction of the preset cutter to form a first preset angle r with the axis of the bottom hole at the first dustpan hole; adjusting the preset cutter to rotate by a second preset angle c around the central line of the bottom hole, wherein the length of two sides of the first dustpan hole is ensured to be equal; and feeding, wherein the depth of the feed is preset to be b, and the first dustpan hole is machined. The application also discloses a dustpan hole structure. The application discloses rotor blade profile dustpan hole structure processing method and dustpan hole structure can realize the matching design of different positions dustpan holes and profiles, make it have more unanimous dustpan hole limit length to improve the uniformity of dustpan hole air film cooling effect of same row.
Description
Technical Field
The application belongs to the field of design of an aircraft engine blade cooling structure, and particularly relates to a machining method of a dustpan hole structure of a rotor blade profile and the dustpan hole structure.
Background
The film cooling is an important means for reducing the surface temperature of the blade and improving the cooling efficiency, and the application of the dustpan hole enables the cool air flowing out of the film hole to have better wall adhesion and film covering effects, so the dustpan hole is widely applied to the guide blade and the rotor blade of the high-pressure turbine. At present, most dustpan holes are machined in an electric spark machining mode, and the dustpan holes and bottom holes in the existing structure are all in a tangent design, namely, during electric spark machining, feeding is carried out along the axis of a gas film hole; in order to facilitate the process and save the processing cost, the same row of dustpan holes are usually provided with the same structural size, namely the same angle a and depth b shown in fig. 1.
However, for a rotor blade with a complex profile, when the same exhaust film hole is processed by using a set of structural parameters, the difference of the processed film holes is large, as shown in fig. 2, L1 and L1' have a great difference, and thus the film covering effect of the dustpan holes at different positions is inconsistent; in general, the value b is basically unchanged, and the adjustment of the angle a (the angle of the cutter) can ensure that the air film holes reach better consistency, but the machining cutter is changed for each air film hole to be machined, so that the complexity of the machining process and the machining cost are greatly increased; when the curvature of the blade profile is greatly changed, a certain difference (long and short sides) exists between two sides of the same dustpan opening, and the shape of the dustpan opening deviates from the ideal dustpan opening shape (right) in fig. 1, such as L1, L2 shown in fig. 2. Therefore, in order to make the processed air film hole have better consistency (air film covering effect), it is necessary to design a dustpan hole structure matched with the blade profile and a processing method.
Disclosure of Invention
In order to solve at least one of the technical problems, the application provides a machining method of a dustpan hole structure of a rotor blade profile and a dustpan hole structure.
In a first aspect, the application discloses a machining method for a dustpan hole structure with a rotor blade profile, which comprises the following steps:
step one, selecting a first dustpan hole in a same row of preprocessed dustpan holes on the molded surface of a rotor blade by adopting a preset cutter;
adjusting the feeding direction of the preset cutter to form a first preset angle r with the bottom hole axis at the first dustpan hole before feeding;
step three, adjusting the preset cutter to rotate by a second preset angle c around the central line of the bottom hole, wherein the length of two sides of the first dustpan hole is ensured to be equal;
and step four, feeding, wherein the depth of the feed is preset to a depth b, and the first dustpan hole is machined.
According to at least one embodiment of the present application, the method for processing a dustpan hole structure of a rotor blade profile further includes:
and step five, sequentially selecting other dustpan holes in the same row of preprocessed dustpan holes, and sequentially processing the dustpan holes according to the step two to the step four by adopting the same preset cutter.
In a second aspect, the present application discloses a dustpan hole structure obtained by the method for processing a rotor blade profile dustpan hole structure according to any one of the above, wherein each dustpan hole structure comprises two side edges with the length of a first side edge L1 and a second side edge L2, respectively, and the first side edge L1 is equal to the second side edge L2.
According to at least one embodiment of the present application, a bottom surface of each of the dustpan hole structures is at a predetermined angle to an axis of the bottom hole.
According to at least one embodiment of the present application, the first side length L1 of the side of the dustpan opening structure at different positions in the same row is the same in length.
The application has at least the following beneficial technical effects:
according to the machining method of the dustpan hole structure with the rotor blade profile and the dustpan hole structure, matching design of dustpan holes at different positions and profiles (especially the rotor blade profiles with large curvature change) can be realized, so that the dustpan holes have relatively consistent hole edge lengths, and consistency of air film cooling effects of the dustpan holes in the same row is improved; in addition, the symmetry of two sides of the same dustpan hole is realized by adjusting the angle of the symmetrical surface of the dustpan hole (namely the feed angle of a tool for processing the dustpan hole); furthermore, the dustpan hole structure of this application can shorten dustpan hole production cycle, practice thrift the processing cost, has guaranteed the uniformity of processing back dustpan hole symmetry and with arranging dustpan hole air film covering effect again simultaneously.
Drawings
FIG. 1 is a schematic view of a blade structure in the method for manufacturing a dustpan hole structure of a rotor blade profile according to the present application;
FIG. 2 is a schematic view of a dustpan hole layout on a blade profile of a conventional rotor;
FIG. 3 is an enlarged schematic view at B in FIG. 2;
FIG. 4 is a schematic size view of a conventional dustpan opening structure;
FIG. 5 is a schematic view showing the structural arrangement of the dustpan opening on the blade profile of the rotor in the present application;
fig. 6 is a cross-sectional view taken along line M-M in fig. 5.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present 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 a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The method for machining the dustpan opening structure with the rotor blade profile and the dustpan opening structure according to the present invention will be described in further detail with reference to fig. 1 to 6.
In a first aspect, the application discloses a machining method for a dustpan hole structure with a rotor blade profile, which comprises the following steps:
step one, selecting a first dustpan hole in the same row of preprocessed dustpan holes on the molded surface of the rotor blade by adopting a preset cutter.
And step two, before feeding, adjusting the feeding direction of a preset cutter to form a first preset angle r with the axis of the bottom hole at the first dustpan hole.
And step three, adjusting the preset cutter to rotate by a second preset angle c around the central line of the bottom hole, wherein the second preset angle c is used for ensuring that the lengths of two sides of the first dustpan hole are equal.
And step four, feeding, wherein the depth of the feed is preset to a depth b, and the first dustpan hole is machined.
Further, the machining method of the dustpan hole structure with the rotor blade profile can further comprise the following steps:
and step five, sequentially selecting other dustpan holes in the same row of preprocessed dustpan holes, and sequentially processing the dustpan holes according to the step two to the step four by adopting the same preset cutter.
In the method for processing the dustpan hole structure with the rotor blade profile, all dustpan holes have the same angle a (for example, 20 degrees), and the angle r (namely, the feed angle) and the depth b (fine adjustment) are adjusted according to different positions, so that the dustpan holes with better consistency can be processed by adopting cutters of the same type; an angle c is formed between the symmetrical surface of the dustpan hole and the XOY surface (the XOY surface is parallel to the central line of the bottom hole), namely, during machining, the cutter rotates by the angle c around the central line of the bottom hole to ensure that two sides of the machined dustpan hole have the same length L1 and L2, the conformity of manufacturing and design is ensured, and further the rear air film covering effect of cold air outflow is ensured.
In a second aspect, the present application discloses a dustpan hole structure obtained by the method for processing a dustpan hole structure with a rotor blade profile according to any one of the above, wherein each dustpan hole structure comprises two side edges with the side edges respectively having a first side edge L1 and a second side edge L2, and the first side edge L1 is equal to the second side edge L2. Further, the bottom surface of each dustpan hole structure is at a predetermined angle (outward deviation) with the axis of the bottom hole, wherein the predetermined angle can be selected as needed to ensure that the sides L1 and L1' of the dustpan holes at different positions in the same row have the same length, i.e., the first sides L1 of the sides of the dustpan hole structures at different positions in the same row have the same length.
In summary, the dustpan hole structure and the processing method for the rotor blade profile dustpan hole structure can realize the matching design of the dustpan holes at different positions and profiles (especially for the rotor blade profiles with large curvature change), so that the dustpan holes have relatively consistent hole edge lengths, and the consistency of air film cooling effects of the dustpan holes in the same row is improved; in addition, the symmetry of two sides of the same dustpan hole is realized by adjusting the angle of the symmetrical surface of the dustpan hole (namely the feed angle of a tool for processing the dustpan hole); furthermore, the dustpan hole structure of this application can shorten dustpan hole production cycle, practice thrift the processing cost, has guaranteed the uniformity of processing back dustpan hole symmetry and with arranging dustpan hole air film covering effect again simultaneously.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (4)
1. A machining method for a dustpan hole structure of a rotor blade profile is characterized by comprising the following steps:
step one, selecting a first dustpan hole in a same row of preprocessed dustpan holes on the molded surface of a rotor blade by adopting a preset cutter;
step two, before feeding, adjusting the feeding direction of the preset cutter to form a first preset angle r with the axis of the bottom hole at the first dustpan hole, so that the first side length L1 of the side edge of the dustpan hole structure at different positions in the same row is the same in length;
step three, adjusting the preset cutter to rotate by a second preset angle c around the central line of the bottom hole, wherein the second preset angle c is used for ensuring that the lengths of two sides of the first dustpan hole are equal;
feeding, wherein the depth of the feeding is preset to a depth b, and the first dustpan hole is machined;
and step five, sequentially selecting other dustpan holes in the same row of preprocessed dustpan holes, and sequentially processing the dustpan holes according to the step two to the step four by adopting the same preset cutter.
2. A dustpan hole structure obtained by the method for processing a dustpan hole structure having a rotor blade profile according to claim 1, wherein each dustpan hole structure includes two side edges having a first side length L1 and a second side length L2, respectively, and wherein the first side length L1 is equal to the second side length L2.
3. The dustpan hole structure of claim 2, wherein the bottom surface of each dustpan hole structure is at a predetermined angle with respect to the axis of the bottom hole.
4. The dustpan hole structure of claim 2, wherein the first side lengths L1 of the sides of the dustpan hole structure at different positions in the same row are the same in length.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811543808.9A CN109551068B (en) | 2018-12-17 | 2018-12-17 | Machining method for dustpan hole structure with rotor blade profile and dustpan hole structure |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811543808.9A CN109551068B (en) | 2018-12-17 | 2018-12-17 | Machining method for dustpan hole structure with rotor blade profile and dustpan hole structure |
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| CN109551068A CN109551068A (en) | 2019-04-02 |
| CN109551068B true CN109551068B (en) | 2021-03-30 |
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| CN115130525B (en) * | 2022-07-21 | 2023-04-07 | 北京汉飞航空科技有限公司 | Automatic extraction method for digital-analog dustpan hole characteristics of turbine blade of engine |
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| JP2013167205A (en) * | 2012-02-15 | 2013-08-29 | Hitachi Ltd | Gas turbine blade, and tool for electrical discharge machining and machining method of the same |
| CN103406669A (en) * | 2012-04-19 | 2013-11-27 | 中国航空工业集团公司北京航空制造工程研究所 | Method for directly machining turbine blade air film abnormal-shaped hole through laser |
| CN102861956B (en) * | 2012-09-20 | 2014-06-18 | 清华大学 | Machining method of gravity-free smelting layer air membrane hole of aviation engine turbine blade |
| CN102996187A (en) * | 2012-12-06 | 2013-03-27 | 哈尔滨汽轮机厂有限责任公司 | Combustion engine turbine first-level guide blade lower end wall cooling system |
| CN105171158B (en) * | 2015-10-10 | 2017-11-14 | 贵阳中航动力精密铸造有限公司 | A kind of turborotor taper air film hole processing technology |
| CN205074819U (en) * | 2015-10-30 | 2016-03-09 | 沈阳黎明航空发动机(集团)有限责任公司 | Anchor clamps in processing guide blade blade air film hole |
| CN107506519B (en) * | 2017-07-07 | 2020-07-03 | 厦门大学 | Parametric machining method for gas film cooling hole of precision-cast turbine blade |
| CN207829957U (en) * | 2017-12-14 | 2018-09-07 | 中国航发商用航空发动机有限责任公司 | Blade tip groove air film hole cooling structure |
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