CN109551068A - A kind of rotor blade type face dustpan pore structure processing method and dustpan pore structure - Google Patents
A kind of rotor blade type face dustpan pore structure processing method and dustpan pore structure Download PDFInfo
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- CN109551068A CN109551068A CN201811543808.9A CN201811543808A CN109551068A CN 109551068 A CN109551068 A CN 109551068A CN 201811543808 A CN201811543808 A CN 201811543808A CN 109551068 A CN109551068 A CN 109551068A
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- China
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- dustpan
- pore structure
- hole
- rotor blade
- blade type
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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
-
- 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
This application discloses a kind of rotor blade type face dustpan pore structure processing method, include the following steps: to choose first dustpan hole on rotor blade type face in the dustpan hole of same row's preprocessing using predetermined cutter；Before feed, adjusting the direction of feed of the predetermined cutter and the bottom outlet axis at first dustpan hole is in the first predetermined angular r；It adjusts the predetermined cutter and rotates the second predetermined angular c around the bottom outlet center line, wherein is described for guaranteeing the both sides equal length in first dustpan hole；Feed, and depth of cut predetermined depth b, and complete first dustpan hole machined.Disclosed herein as well is a kind of dustpan pore structures.The rotor blade type face dustpan pore structure processing method and dustpan pore structure of the application, it can be realized the matched design in different location dustpan hole Yu type face, more consistent dustpan hole hole edge lengths are made it have, to improve the consistency with row's dustpan hole Film Cooling.
Description
Technical field
The application belongs to blade of aviation engine cooling structure design field, in particular to a kind of rotor blade type face dustpan
Pore structure processing method and dustpan pore structure.
Background technique
Gaseous film control is the important means for reducing blade surface temperature, improving cooling efficiency, and the application in dustpan hole makes to bring about the desired sensation
Fenestra, which goes out the cold air flowed, has preferably adherent and air film coverage effect, therefore dustpan hole has been widely used in high-pressure turbine and has led
To on blade and rotor blade.Currently, most of dustpan holes are processed using electrical discharge machining form, existing structure dustpan hole
It is all tangent design with bottom outlet, i.e. electrical spark working working hour is along air film axially bored line feed；In order to facilitate technique, saves and be processed into
This, often same row's dustpan hole uses identical structure size, i.e. identical a angle and depth b shown in Fig. 1.
But for the rotor blade of complex profile, when same exhaust fenestra is processed using a set of structural parameters,
The air film hole processed differs greatly, as shown in Fig. 2, L1 with L1' phase is far short of what is expected, and then different location dustpan hole air film is caused to cover
Lid effect is inconsistent；Under normal conditions, b value is basically unchanged, and adjusting the angle a (cutting-tool angle) can make air film hole reach preferable
Consistency, but will lead to one air film hole of every processing in this way and change a process tool, considerably increase the complexity of processing technology
Property and processing cost；When blade profile Curvature varying is larger, two sides in same dustpan hole can also have a certain difference (long
Short side), (right side) ideal dustpan hole shape, L1 > L2 as shown in Figure 2 in slip chart 1.Therefore, in order to make processing after air film hole
With preferable consistency (film overcast effect), need to design a kind of dustpan pore structure both to have matched with blade profile and
Processing method.
Summary of the invention
At least one in order to solve the above-mentioned technical problem, this application provides a kind of rotor blade type face dustpan pore structures to add
Work method and dustpan pore structure.
In a first aspect, including the following steps: this application discloses a kind of rotor blade type face dustpan pore structure processing method
Step 1: choosing first on rotor blade type face in the dustpan hole of same row's preprocessing using predetermined cutter
Dustpan hole；
Step 2: before feed, the direction of feed and the bottom outlet axis at first dustpan hole that adjust the predetermined cutter
Line is in the first predetermined angular r；
Step 3: the adjustment predetermined cutter rotates the second predetermined angular c around the bottom outlet center line, wherein the use
In the both sides equal length for guaranteeing first dustpan hole；
Step 4: feed, and depth of cut predetermined depth b, and complete first dustpan hole machined.
According at least one embodiment of the application, the rotor blade type face dustpan pore structure processing method is also wrapped
It includes:
Step 5: successively choosing other dustpan holes in the dustpan hole of same row's preprocessing, and using same described pre-
Stationary knife tool, is successively processed according to the step 2 to step 4.
Second aspect adds this application discloses a kind of according to rotor blade type described in any of the above embodiments face dustpan pore structure
The dustpan pore structure that work method obtains, each dustpan pore structure include two sides, and side length is respectively the first side length L1
It is equal to the second side length L2 with the second side length L2, the first side length L1.
According at least one embodiment of the application, the bottom surface of each dustpan pore structure and the axis of bottom outlet are at pre-
Determine angle.
According at least one embodiment of the application, the institute of the side of dustpan pore structure described in the different location of same row
It is identical to state the first side length L1 length.
At least there are following advantageous effects in the application:
The rotor blade type face dustpan pore structure processing method and dustpan pore structure of the application, can be realized different location and winnows with a dustpan
The matched design in dustpan hole and type face (especially for Curvature varying biggish rotor blade type face), makes it have more consistent
Dustpan hole hole edge lengths, to improve the consistency with row's dustpan hole Film Cooling；In addition, symmetrical by adjusting dustpan hole
The angle (namely processing the feed angle of dustpan spot facing cutter) in face, realizes the symmetry on same dustpan hole both sides；Into one
Step, the dustpan pore structure of the application can shorten the dustpan hole production cycle, save processing cost, while after in turn ensuring processing
The consistency of dustpan hole symmetry and same row's dustpan hole film overcast effect.
Detailed description of the invention
Fig. 1 is blade construction schematic diagram in the rotor blade type face dustpan pore structure processing method of the application；
Fig. 2 is dustpan hole arrangement schematic diagram on existing rotor blade type face；
Fig. 3 is enlarged diagram at B in Fig. 2；
Fig. 4 is existing dustpan pore structure scale diagrams；
Fig. 5 is dustpan pore structure schematic layout pattern on the application rotor blade type face；
Fig. 6 is M-M cross-sectional view in Fig. 5.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the application
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
In explanation the application, and it should not be understood as the limitation to the application.Based on the embodiment in the application, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall in the protection scope of this application.Under
Face is described in detail embodiments herein in conjunction with attached drawing.
In the description of the present application, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown is merely for convenience of description the application and simplifies description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the application
The limitation of range.
Rotor blade type face dustpan pore structure processing method and dustpan pore structure of the 1- Fig. 6 to the application with reference to the accompanying drawing
It is described in further details.
In a first aspect, including the following steps: this application discloses a kind of rotor blade type face dustpan pore structure processing method
Step 1: choosing first on rotor blade type face in the dustpan hole of same row's preprocessing using predetermined cutter
Dustpan hole.
Step 2: adjusting the bottom outlet axis at the direction of feed and first dustpan hole of predetermined cutter in first before feed
Predetermined angular r.
The second predetermined angular c is rotated around bottom outlet center line Step 3: adjusting predetermined cutter, wherein for guaranteeing first
The both sides equal length in dustpan hole.
Step 4: feed, and depth of cut predetermined depth b, and complete first dustpan hole machined.
Further, the rotor blade type face dustpan pore structure processing method of the application can also include:
Step 5: successively choosing other dustpan holes in the dustpan hole of same row's preprocessing, and using same described pre-
Stationary knife tool, is successively processed according to the step 2 to step 4.
In the rotor blade type face dustpan pore structure processing method of the application, all dustpan hole angle a (examples having the same
Such as 20 degree), angle r (namely feed angle) and depth b (fine tuning) are adjusted according to the difference of position, guaranteeing in this way can
The preferable dustpan hole of consistency can be processed using the cutter of the same model；The dustpan hole plane of symmetry and the face the XOY (face XOY
It is parallel to bottom outlet center line) c at an angle, that is, when processing, cutter is processed around bottom outlet center line rotational angle c with guarantee
Dustpan hole both sides length L1 and L2 having the same guarantees the accordance of manufacture and design, and then guarantees that cold air goes out the rear gas flowed
Film coverage effect.
Second aspect, this application discloses a kind of rotor blade type face dustpan pore structure processing sides according to any of the above-described
The dustpan pore structure that method obtains, each dustpan pore structure include two sides, and side length is respectively the first side length L1 and the second side
Long L2, wherein the first side length L1 is equal to the second side length L2.Further, the axis of the bottom surface of each dustpan pore structure and bottom outlet
At predetermined angular (outward partially), wherein, predetermined angular is to can according to need to carry out suitable selection, to ensure same row's
The side L1 and L1' length in different location dustpan hole is identical, i.e., and the first of the side of the different location dustpan pore structure of same row
Side length L1 length is identical.
In conclusion the rotor blade type face dustpan pore structure processing method and dustpan pore structure of the application, can be realized
The matched design in different location dustpan hole and type face (especially for Curvature varying biggish rotor blade type face), makes it have
More consistent dustpan hole hole edge lengths, to improve the consistency with row's dustpan hole Film Cooling；In addition, by adjusting
The angle (namely processing the feed angle of dustpan spot facing cutter) of the dustpan hole plane of symmetry, realizes pair on same dustpan hole both sides
Title property；Further, the dustpan pore structure of the application can shorten the dustpan hole production cycle, save processing cost, while guarantee again
Dustpan hole symmetry and the consistency with row's dustpan hole film overcast effect after processing.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (5)
1. a kind of rotor blade type face dustpan pore structure processing method, which comprises the steps of:
Step 1: choosing first dustpan on rotor blade type face in the dustpan hole of same row's preprocessing using predetermined cutter
Hole；
Step 2: before feed, the direction of feed for adjusting the predetermined cutter is in the bottom outlet axis at first dustpan hole
First predetermined angular r；
Step 3: the adjustment predetermined cutter rotates the second predetermined angular c around the bottom outlet center line, wherein described for protecting
Demonstrate,prove the both sides equal length in first dustpan hole；
Step 4: feed, and depth of cut predetermined depth b, and complete first dustpan hole machined.
2. rotor blade type according to claim 1 face dustpan pore structure processing method, which is characterized in that further include:
Step 5: successively choosing other dustpan holes in the dustpan hole of same row's preprocessing, and use the same pre- stationary knife
Tool, is successively processed according to the step 2 to step 4.
3. a kind of dustpan that -2 described in any item rotor blade types face dustpan pore structure processing methods obtain according to claim 1
Pore structure, each dustpan pore structure include two sides, and side length is respectively the first side length L1 and the second side length L2, spy
Sign is that the first side length L1 is equal to the second side length L2.
4. dustpan pore structure according to claim 3, which is characterized in that the bottom surface of each dustpan pore structure and bottom outlet
Axis at predetermined angular.
5. dustpan pore structure according to claim 3, which is characterized in that dustpan pore structure described in the different location of same row
Side the first side length L1 length it is identical.
Priority Applications (1)
| 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 |
Applications Claiming Priority (1)
| 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109551068A true CN109551068A (en) | 2019-04-02 |
| CN109551068B CN109551068B (en) | 2021-03-30 |
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| CN201811543808.9A Active 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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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115130525A (en) * | 2022-07-21 | 2022-09-30 | 北京汉飞航空科技有限公司 | Automatic extraction method for digital-analog dustpan hole characteristics of engine turbine blade |
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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 |
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| CN105171158A (en) * | 2015-10-10 | 2015-12-23 | 贵阳中航动力精密铸造有限公司 | Technology for machining conical gas film holes of turbine guide blade |
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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 |
| CN102861956A (en) * | 2012-09-20 | 2013-01-09 | 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 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115130525A (en) * | 2022-07-21 | 2022-09-30 | 北京汉飞航空科技有限公司 | Automatic extraction method for digital-analog dustpan hole characteristics of engine turbine blade |
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| CN109551068B (en) | 2021-03-30 |
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