CN112222551A - Gas film hole positioning tool and machining method thereof, and gas film hole machining and detecting method - Google Patents
Gas film hole positioning tool and machining method thereof, and gas film hole machining and detecting method Download PDFInfo
- Publication number
- CN112222551A CN112222551A CN202011125968.9A CN202011125968A CN112222551A CN 112222551 A CN112222551 A CN 112222551A CN 202011125968 A CN202011125968 A CN 202011125968A CN 112222551 A CN112222551 A CN 112222551A
- Authority
- CN
- China
- Prior art keywords
- hole
- turbine blade
- film hole
- machining
- air film
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- 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
- B23H7/00—Processes or apparatus applicable to both electrical discharge machining and electrochemical machining
- B23H7/02—Wire-cutting
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
Abstract
The invention discloses an air film hole positioning tool, which is used for processing an air film hole of a turbine blade by electric spark. The invention can improve the position precision of the air film hole, reduce the hole position error of the air film hole, improve the production efficiency and improve the cooling effect of the turbine blade.
Description
Technical Field
The invention relates to the technical field of turbine blade machining, in particular to an air film hole positioning tool and a machining method thereof, and an air film hole machining and detecting method.
Background
Turbine blades are important components of the turbine section of a gas turbine engine. The blades rotating at high speed are responsible for drawing high-temperature and high-pressure airflow into the combustor to maintain the operation of the engine. The turbine blades are generally subjected to high operating stress and high operating temperature, and the stress and temperature change is frequent and severe, and in order to improve the efficiency of the turbine, the surface shape of the turbine blades is usually designed to be a twisted variable cross-section curved surface, and the shape is complex. In order to cool the turbine blades and extend their useful life, the turbine blades are provided with film holes.
However, the existing gas film hole machining generally adopts electric spark punching machining, when the electrode wire is used for punching, the positioning of the electrode wire, namely the position of the gas film hole on the blade, is observed by naked eyes, and the manual positioning mode has the defects of low electrode wire positioning precision, large gas film hole position error, low production efficiency, influence on the cooling effect of the turbine blade and reduction of the service life of the turbine engine.
Disclosure of Invention
The invention aims to provide a gas film hole positioning tool which is designed aiming at the positioning tool, is convenient for the electric spark machining of a turbine blade gas film hole, and can improve the position precision of the gas film hole, reduce the hole position error of the gas film hole, improve the production efficiency and improve the cooling effect of the turbine blade.
The invention aims to provide a processing method of a positioning tool for processing an air film hole, which is designed aiming at the processing method of the positioning tool, can improve the processing precision of the positioning tool and can provide precision guarantee for the processing of the air film hole of a turbine blade.
The invention aims to provide a gas film hole machining method which is designed aiming at the gas film hole machining method, can improve the position precision of a gas film hole, reduce the hole position error of the gas film hole, improve the production efficiency and improve the cooling effect of a turbine blade.
The invention aims to provide a detection method for air film hole machining, which is designed aiming at the air film hole detection method, can improve the detection efficiency and detection quality of the air film hole, is beneficial to improving the machining quality of the air film hole and is beneficial to improving the cooling effect of a turbine blade.
The embodiment of the invention is realized by the following technical scheme:
the utility model provides an air film hole location frock for the air film hole of spark-erosion machining turbine blade, is equipped with the guiding hole that is used for the wire electrode to pass including the location portion that is used for this turbine blade of centre gripping, this location portion.
In an embodiment of the present invention, the positioning portion includes a positioning surface for adhering to the turbine blade body, and the positioning surface is used for clamping the turbine blade body.
A machining method of a positioning tool for machining an air film hole is characterized in that a theoretical model of a turbine blade is adopted to machine the positioning surface and the guide hole.
In an embodiment of the invention, the positioning tool is processed by a high-precision processing center.
A method for machining the air film hole of turbine blade by electric spark machining features that the locating tool for machining the air film hole is used to clamp the turbine blade to be machined, and the electrode wire is inserted in the guide hole for machining the air film hole of turbine blade.
In an embodiment of the invention, the positioning tool is clamped to a machine tool, a guide hole is selected on the positioning tool, and the wire electrode is manually inserted into the guide hole to perform punching processing on a first air film hole; under the control of a preset numerical control machining program of the machine tool, the wire electrode automatically completes punching machining of the residual air hole film along a preset running track.
A detection method for machining an air film hole is used for detecting the position degree and the aperture of the air film hole of a turbine blade.
In an embodiment of the invention, a plurality of guide holes are selected optionally during detection, when the plug needles are inserted into the guide holes respectively, if the plug needles can be inserted into the film holes below the guide holes, the film holes of the turbine blade meet the design requirements.
In one embodiment of the invention, the stopper needle is provided with a scale for indicating the depth of insertion of the stopper needle into the guide hole.
In an embodiment of the invention, the distance between the scale and the end of the plug needle is equal to the sum of the depth of the guide hole and the preset depth of the plug needle inserted into the air film hole.
The technical scheme of the embodiment of the invention at least has the following advantages and beneficial effects:
according to the embodiment of the invention, the positioning tool is arranged and processed and molded according to the theoretical model of the turbine blade, the positioning tool is processed to form the guide hole, the positioning tool is sleeved on the turbine blade and fixed on the turbine blade when the air film hole is processed, and the electrode wire is inserted into the guide hole to process the air film hole. Compare with the location of punching of visual observation affirmation wire electrode on turbine blade among the prior art, this technical scheme utilizes frock auxiliary positioning to replace original artifical visual observation location with the location frock auxiliary electrode silk location that has the guiding hole, has improved the positioning accuracy of wire electrode, has improved the position accuracy in air film hole, has reduced the hole site error in air film hole, has improved production efficiency, has improved turbine blade's cooling effect.
According to the embodiment of the invention, the positioning tool is arranged and is processed and molded according to the theoretical model of the turbine blade, the guide hole is processed on the positioning tool, the plug needle with the specified diameter is inserted into the guide hole in the detection after the air film hole is processed, if the depth of the plug needle inserted into the guide hole is greater than that of the guide hole, the plug needle is shown to penetrate through the guide hole and is inserted into the air film hole, the position of the air film hole is shown to be the same as that of the guide hole, the position of the air film hole meets the design requirement, and the aperture of the air film hole also meets the requirement.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
FIG. 1 is a schematic view of a positioning tool of the present invention clamping a turbine blade;
FIG. 2 is a partial schematic view of FIG. 1;
FIG. 3 is a schematic structural view of a positioning tool for clamping a turbine blade according to the present invention;
FIG. 4 is a partial schematic view of FIG. 3;
FIG. 5 is a schematic view of the present invention illustrating the use of a positioning tool to detect a gas film hole.
Icon: 1-guide hole, 2-positioning surface, 3-wire electrode, 4-turbine blade, 5-air film hole, 6-plug needle, 7-wire electrode and 8-positioning portion.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. 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 invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it should be noted that if the terms "inside", "outside", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings or the orientation or positional relationship which is usually placed when the product of the present invention is used, the description is merely for convenience of describing the present invention and simplifying the description, but the indication or suggestion that the referred device or element must have a specific orientation, be constructed in a specific orientation and operation, and thus, cannot be understood as the limitation of the present invention.
In the description of the present invention, it should be further noted that unless otherwise explicitly stated or limited, the terms "disposed," "mounted," "configured," and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Referring to fig. 1 to 4, an air film hole positioning tool for an air film hole 5 of a turbine blade 4 in an electric discharge machining process includes a positioning portion 8 for clamping a blade body of the turbine blade 4, and a guide hole 1 for a wire electrode 7 to pass through is formed in the positioning portion 8. The positioning part 8 comprises a positioning surface 2 for fitting the blade body of the turbine blade 4, and the positioning surface 2 is used for clamping the blade body of the turbine blade 4.
A machining method of a positioning tool for machining an air film hole is characterized in that a theoretical model of a turbine blade 4 is adopted to machine the positioning surface 2 and the guide hole 1. The positioning tool is processed by a high-precision processing center.
In order to facilitate the electric spark machining of the air film holes 5 of the turbine blades 4, the position precision of the air film holes 5 can be improved, the hole site errors of the air film holes 5 are reduced, the production efficiency is improved, and the cooling effect of the turbine blades 4 is improved. This technical scheme sets up the location frock including location portion 8 and guiding hole 1, adopts turbine blade 4's theoretical model processing locating surface 2 with guiding hole 1 has higher machining precision in order to guarantee this location frock moreover, can provide the precision assurance for turbine blade 4's 5 processing in the air film hole, and this location frock can adopt high accuracy machining center to process. The theoretical model of the turbine blade 4 refers to a model of the turbine blade 4 drawn by a designer using three-dimensional modeling software, the blade body of the turbine blade 4 model is designed with the film hole 5 as required, and a person skilled in the art can machine the turbine blade 4 according to the theoretical model or a two-dimensional engineering drawing made according to the theoretical model. The guide hole 1 of the positioning portion 8 can be understood as: when the positioning portion 8 clamps the blade body of the theoretical model, the air film hole 5 in the theoretical model extends to the outside of the turbine blade 4 and penetrates through the through hole formed by the positioning portion 8. The locating surface 2 of the locating part 8 can be understood as a curved surface similar to the appearance of the turbine blade 4, when the locating tool clamps the blade body of the high turbine blade 4, the locating surface 2 is attached to the blade body of the turbine blade 4, and the locating surface 2 also plays a role in clamping the blade body of the turbine blade 4. Through the positioning surface 2 and the blade body laminating, the electrode wire 7 can directly act on the surface of the turbine blade 4 after penetrating out of the guide hole 1, the coaxiality of the free end of the electrode wire 7 and the guide hole 1 is ensured, and the hole site precision of the air film hole 5 is improved. Because the turbine blade is a twisted variable cross-section curved surface, the positioning tool can be a structure formed by assembling two or more parts, and before the air film hole 5 of the turbine blade 4 is machined, the parts of the positioning tool are assembled into a whole and the turbine blade 4 is surrounded in the positioning tool. When the air film hole 5 is processed, the positioning part 8 is used for clamping the blade body of the turbine blade 4, then the electrode wire 7 is inserted into the guide hole 1, because the hole position and the inclination angle of the guide hole 1 are the same as the theoretical model of the turbine blade 4, the guide hole 1 can provide a positioning reference for the positioning of the electrode wire 7 on the turbine blade 4, compared with the prior art in which the punching positioning of the electrode wire 7 on the turbine blade 4 is determined by visual observation, the technical scheme uses the positioning tool with the guide hole 1 to position the electrode wire 7 relative to the turbine blade 4, and utilizes the positioning tool to position instead of the original manual visual observation positioning, thereby facilitating the electric spark machining of the air film hole 5 of the turbine blade 4, and the positioning tool can provide precision guarantee for the machining of the air film hole 5 of the turbine blade 4, improve the positioning precision of the electrode wire 7, improve the position precision of the air film hole 5, and reduce the error of, the production efficiency is improved, the cooling effect of the turbine blades 4 is improved, and the service life of the turbine engine is prolonged.
It should be noted that, the same batch of turbine blades 4, only need make one or a small amount of this location frock can, reach the effect of once and for all, the processing of the air film hole 5 of this batch of turbine blades 4, the machining precision of its air film hole 5 is guaranteed by this location frock, and can be used to process on the lower lathe of machining precision, compared with the prior art, improved the position accuracy of air film hole 5, reduced the hole site error of air film hole 5, and improved production efficiency, the cooling effect of turbine blade 4 has been improved, the life of turbine engine has been prolonged.
A machining method of an air film hole is used for machining an air film hole 5 of a turbine blade 4 through electric spark machining, the turbine blade 4 to be machined is clamped by the positioning tool for machining the air film hole 5, an electrode wire 7 penetrates into a guide hole 1, and machining of the air film hole 5 is conducted on the turbine blade 4.
In order to improve the position accuracy of the air film hole 5, reduce the hole site error of the air film hole 5, improve the production efficiency, and improve the cooling effect of the turbine blade 4, the processing of the air film hole 5 of the technical scheme is used for clamping the turbine blade 4 to be processed by the positioning tool, the air film hole 5 in the turbine blade 4 is used for cooling the turbine blade 4, the influence on the cooling effect of the turbine blade 4 is considered by the position design and the angle design of each air film hole 5, if the position degree and the inclination angle error of the processed air film hole 5 are large, the cooling effect of the turbine blade 4 can be influenced, and the service life of the blade is shortened. When the air film hole 5 is machined, clamping the positioning tool to a machine tool, selecting a guide hole 1 on the positioning tool, and manually operating to enable the electrode wire 7 to penetrate into the guide hole 1 and carry out punching machining on a first air film hole 5; under the control of a preset numerical control machining program of the machine tool, the wire electrode 7 automatically completes punching machining of other pore membranes along a preset running track. It should be noted that, under the control of the numerical control machining program preset in the machine tool, the machine tool may also control the positioning tool to move or rotate in a direction adapted to the position of the wire electrode 7, so that the wire electrode 7 machines the gas film hole 5 meeting the designed hole position and the designed inclination angle, for example, a five-axis electric discharge machine is used to machine the gas film hole 5. Compare with visual observation confirms the location of punching of wire electrode 7 on turbine blade 4 among the prior art, this technical scheme is with the location frock location wire electrode 7 that has guiding hole 1 for the position of turbine blade 4, utilize location frock location to replace original artifical visual observation location, the electric spark machining of turbine blade 4 air film hole 5 of being convenient for, the positioning accuracy of wire electrode 7 has been improved, the position accuracy of air film hole 5 has been improved, the hole site error of air film hole 5 has been reduced, the production efficiency is improved, the cooling effect of turbine blade 4 has been improved, turbine engine's life has been prolonged.
In some embodiments, the positioning tool includes a clamping portion and a positioning portion 8, the clamping portion is clamped to the tenon of the turbine blade 4, the positioning portion 8 is provided with the guide hole 1, and the positioning portion 8 surrounds the outer portion of the blade body of the turbine blade 4. The location frock is according to turbine blade 4's theoretical model machine-shaping, and this location frock is whole can be by the split type structure that two parts amalgamation formed, when clamping turbine blade 4, places turbine blade 4 in this location frock to assemble this location frock completely, so that turbine blade 4 is wrapped up in this location frock. This location frock still includes clamping part and location portion 8, clamping part and location portion 8 connect into a whole or clamping part and 8 integrated into one piece settings in location portion, location portion 8 has preset guiding hole 1 according to turbine blade 4's theoretical model, this guiding hole 1 extends to turbine blade 4's position and angle, all the same with turbine blade 4's 5 theoretical models in air film hole, after the location frock amalgamation, this clamping part centre gripping is in turbine blade 4's tenon, location portion 8 is corresponding to this turbine blade 4's blade body. When the air film hole 5 is processed, the electrode wire 7 is inserted into the guide hole 1, and the air film hole 5 is processed by electric spark drilling.
Referring to fig. 5, a method for detecting a position and a diameter of an air film hole 5 of a turbine blade 4 includes inserting a stopper pin 6 into a guide hole 1 by the positioning tool sleeved on the turbine blade 4, and if the depth of the stopper pin 6 inserted into the guide hole 1 is greater than the depth of the guide hole 1, the position and the diameter of the air film hole 5 below the guide hole 1 meet design requirements.
In order to improve the detection efficiency of the air film hole 5 and the detection quality, the processing quality of the air film hole 5 is favorably improved, and the cooling effect of the turbine blade 4 is favorably improved, the technical scheme is provided with a positioning tool which is the same as the positioning tool in the air film hole 5 processing method. The positioning tool is machined and molded according to a theoretical model of the turbine blade 4, a guide hole 1 is machined in the positioning tool, the position distribution of the guide hole 1 on the positioning tool is determined according to the theoretical model of the turbine blade 4, and the inner wall of the positioning tool is attached to the outer surface of the turbine blade 4. And after the positioning tool is sleeved on the turbine blade 4, the positioning tool is fixed with the turbine blade 4 through a bolt. In the prior art, generally, first piece is processed earlier, regard this first piece as the reference, the turbine blade 4 of the air film hole 5 of follow-up processing is compared with first piece one by one again, and because the air film hole 5 on the turbine blade 4 is the equipartition, it is qualified product roughly the same with the angle through the air film hole 5 position on two turbine blades 4 of visual observation during quality testing, however, the detection method through visual observation can't realize the detection of higher accuracy, but when the machining error of air film hole 5 surpassed the design requirement but the naked eye can't observe in turbine blade 4, make unqualified turbine blade 4 flow in the application link, influence turbine engine's life.
The method for detecting the turbine blade 4 comprises the steps of selecting a plurality of guide holes 1 optionally during detection, and when the plug needles 6 are inserted into the guide holes 1 respectively, if the plug needles 6 can be inserted into the film holes 5 below the guide holes 1, processing the film holes 5 of the turbine blade 4 to meet design requirements. The positioning tool is a high-precision tool processed through a processing center, if the stopper needle 6 is inserted into the guide hole 1, the insertion depth of the stopper needle 6 is equal to the insertion depth of the guide hole 1, which indicates that the position of the film hole 5 below the guide hole 1 is deviated from the position of the guide hole 1, or the diameter of the film hole 5 below the guide hole 1 is smaller than the diameter of the stopper needle 6, the processing of the film hole 5 of the turbine blade 4 does not meet the design requirements, and the turbine blade is an unqualified product. Compared with the detection method of visual comparison in the prior art, the detection efficiency of the air film hole 5 is improved, the detection quality is improved, the processing quality of the air film hole 5 is improved, and the cooling effect of the turbine blade 4 is improved. When the stopper needle 6 is used to detect the air film hole 5, the same operations as the insertion of the wire electrode 7 into the guide hole 1 and the insertion of the wire electrode 7 into the air film hole 5 can be referred to fig. 1 to 4.
In some embodiments, the stopper needle 6 is provided with a scale for indicating the depth of insertion of the stopper needle 6 into the guide hole 1. The distance between the scale and the tail end of the plug needle 6 is equal to the sum of the depth of the guide hole 1 and the preset depth of the plug needle inserted into the air film hole 5. Insert the degree of depth that gas film hole 5 was predetermine can be set for 3mm, this predetermined degree of depth also can be set for according to actual conditions, for more convenient and fast's detection, set up the scale at stopper needle 6, when examining, if stopper needle 6 inserts guiding hole 1 back, this scale is located guiding hole 1, then show that the position degree and the aperture of this guiding hole 1 below gas film hole 5 all satisfy the designing requirement, if this scale is located outside guiding hole 1, this stopper needle 6 inserts the degree of depth that guiding hole 1 was less than the degree of depth that the scale was located promptly, show that stopper needle 6 does not insert to gas film hole 5 in, the position degree or the aperture of this guiding hole 1 below gas film hole 5 do not satisfy the designing requirement.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. The utility model provides an air film hole location frock for the air film hole of spark-erosion machining turbine blade, its characterized in that, including the location portion that is used for this turbine blade body of centre gripping, this location portion wears to be equipped with the guiding hole that passes for the wire electrode.
2. The film hole positioning tool according to claim 1, wherein the positioning portion comprises a positioning surface for fitting the turbine blade body, and the positioning surface is used for clamping the turbine blade body.
3. The machining method of the positioning tool according to claim 2, characterized in that the positioning surface and the guide hole are machined by using a theoretical model of the turbine blade.
4. An air film hole machining method for machining an air film hole of a turbine blade through electric spark machining is characterized in that the positioning tool of claim 1 or 2 is used for clamping the turbine blade to be machined, an electrode wire penetrates into the guide hole, and air film hole machining is conducted on the turbine blade.
5. The method for machining the gas film hole according to claim 4, wherein the positioning tool is clamped to a machine tool, a guide hole is selected in the positioning tool, and the wire electrode is manually inserted into the guide hole to perform the first gas film hole punching;
under the control of a preset numerical control machining program of the machine tool, the wire electrode automatically completes punching machining of the residual air hole film along a preset running track.
6. A detection method for machining an air film hole is used for detecting the position degree and the aperture of the air film hole of a turbine blade and is characterized in that the positioning tool of claim 1 or 2 is adopted to clamp the turbine blade to be detected, a plug needle penetrates into a guide hole, and if the depth of the plug needle inserted into the guide hole is larger than that of the guide hole, the position degree and the aperture of the air film hole below the guide hole meet the design requirements.
7. The inspection method for film hole machining according to claim 6, wherein a plurality of guide holes are selected optionally during inspection, and when the plug pins are inserted into the guide holes respectively, if the plug pins can be inserted into the film holes below the guide holes, the film hole machining of the turbine blade meets the design requirements.
8. The detection method for the gas film hole processing according to claim 7, wherein the stopper needle is provided with a scale for indicating the depth of the stopper needle inserted into the guide hole.
9. The method for detecting the machining of the gas film hole according to claim 8, wherein the distance between the scale and the tail end of the plug needle is equal to the sum of the depth of the guide hole and the preset depth of the plug needle inserted into the gas film hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011125968.9A CN112222551A (en) | 2020-10-20 | 2020-10-20 | Gas film hole positioning tool and machining method thereof, and gas film hole machining and detecting method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011125968.9A CN112222551A (en) | 2020-10-20 | 2020-10-20 | Gas film hole positioning tool and machining method thereof, and gas film hole machining and detecting method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112222551A true CN112222551A (en) | 2021-01-15 |
Family
ID=74118201
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011125968.9A Pending CN112222551A (en) | 2020-10-20 | 2020-10-20 | Gas film hole positioning tool and machining method thereof, and gas film hole machining and detecting method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112222551A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114192911A (en) * | 2021-12-03 | 2022-03-18 | 中国航发北京航空材料研究院 | Turbine blade electric spark drilling penetration detection method |
| CN114226898A (en) * | 2022-02-24 | 2022-03-25 | 成都和鸿科技股份有限公司 | Method for determining hole site of air film hole |
| CN117506043A (en) * | 2024-01-02 | 2024-02-06 | 成都和鸿科技股份有限公司 | Guide blade dustpan hole machining tool and machining method |
| CN117506043B (en) * | 2024-01-02 | 2024-05-03 | 成都和鸿科技股份有限公司 | Guide blade dustpan hole machining tool and machining method |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02243223A (en) * | 1989-03-15 | 1990-09-27 | Toshiba Corp | Guide for electrode for discharge process |
| US20140048515A1 (en) * | 2012-08-15 | 2014-02-20 | Ivan F. Oliver Vargas | Template for forming cooling passages in a turbine engine component |
| CN203725943U (en) * | 2014-01-15 | 2014-07-23 | 西安航空动力股份有限公司 | Electrode guiding device for machining turbine guide vane air film holes |
| 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 |
| CN105965067A (en) * | 2015-03-12 | 2016-09-28 | 通用电气公司 | Machining tool positioning template for airfoil |
| CN106563856A (en) * | 2015-10-09 | 2017-04-19 | 常州市海富莱机械厂 | Spark erosion drilling machine of tire molds and working method thereof |
| WO2019050110A1 (en) * | 2017-09-05 | 2019-03-14 | 한화에어로스페이스(주) | Component hole machining method |
| CN208758758U (en) * | 2018-08-24 | 2019-04-19 | 哈尔滨汽轮机厂有限责任公司 | A kind of 30MW Compressor Set burner inner liner insert electric spark-erosion perforation built-up jig |
| CN110465710A (en) * | 2019-08-28 | 2019-11-19 | 东莞台一盈拓科技股份有限公司 | A kind of method that aerial blade puncher installs air film hole hole location aperture on-line checking additional |
| CN110582367A (en) * | 2017-05-08 | 2019-12-17 | 通用电气公司 | Automatic plugged hole identification |
-
2020
- 2020-10-20 CN CN202011125968.9A patent/CN112222551A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02243223A (en) * | 1989-03-15 | 1990-09-27 | Toshiba Corp | Guide for electrode for discharge process |
| US20140048515A1 (en) * | 2012-08-15 | 2014-02-20 | Ivan F. Oliver Vargas | Template for forming cooling passages in a turbine engine component |
| CN104582887A (en) * | 2012-08-15 | 2015-04-29 | 西门子能量股份有限公司 | Template for forming cooling passages in a turbine engine component |
| CN203725943U (en) * | 2014-01-15 | 2014-07-23 | 西安航空动力股份有限公司 | Electrode guiding device for machining turbine guide vane air film holes |
| CN105965067A (en) * | 2015-03-12 | 2016-09-28 | 通用电气公司 | Machining tool positioning template for airfoil |
| CN106563856A (en) * | 2015-10-09 | 2017-04-19 | 常州市海富莱机械厂 | Spark erosion drilling machine of tire molds and working method thereof |
| 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 |
| CN110582367A (en) * | 2017-05-08 | 2019-12-17 | 通用电气公司 | Automatic plugged hole identification |
| WO2019050110A1 (en) * | 2017-09-05 | 2019-03-14 | 한화에어로스페이스(주) | Component hole machining method |
| CN208758758U (en) * | 2018-08-24 | 2019-04-19 | 哈尔滨汽轮机厂有限责任公司 | A kind of 30MW Compressor Set burner inner liner insert electric spark-erosion perforation built-up jig |
| CN110465710A (en) * | 2019-08-28 | 2019-11-19 | 东莞台一盈拓科技股份有限公司 | A kind of method that aerial blade puncher installs air film hole hole location aperture on-line checking additional |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114192911A (en) * | 2021-12-03 | 2022-03-18 | 中国航发北京航空材料研究院 | Turbine blade electric spark drilling penetration detection method |
| CN114226898A (en) * | 2022-02-24 | 2022-03-25 | 成都和鸿科技股份有限公司 | Method for determining hole site of air film hole |
| CN117506043A (en) * | 2024-01-02 | 2024-02-06 | 成都和鸿科技股份有限公司 | Guide blade dustpan hole machining tool and machining method |
| CN117506043B (en) * | 2024-01-02 | 2024-05-03 | 成都和鸿科技股份有限公司 | Guide blade dustpan hole machining tool and machining method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112222551A (en) | Gas film hole positioning tool and machining method thereof, and gas film hole machining and detecting method | |
| CN105081691B (en) | Diamond shaped tooth form circular-arc roots of vanes movable vane slice processing method | |
| CN112388263A (en) | Processing technology of rhombic surface tooth-shaped blade root blade without blade crown for steam turbine | |
| CN106271469A (en) | A kind of processing method of elongated hollow many cavity thin-walls compressor blade | |
| EP3957826A2 (en) | Adaptive machining of cooled turbine airfoil | |
| CN104462807B (en) | A kind of hot investment casting formula spray pushes away the blade offset method of inspection of impeller | |
| CN110315295A (en) | Propeller processing technique | |
| CN103111824B (en) | Synchronized process of flow debugging and aperture machining | |
| CN202166400U (en) | Coaxiality detection device for complex parts | |
| CN112484600B (en) | Method for inspecting multi-tooth shrouded turbine blade in aircraft engine | |
| US10569382B2 (en) | Abrasive tool indicator system, method and apparatus | |
| CN110026594A (en) | The processing method of turbine spindle stream expansion machine rotor movable vane piece early warning slot | |
| CN109408936B (en) | Method for processing and online measuring deep blind cavity of gliding radome | |
| CN109062136B (en) | Closed impeller machining tool receiving mark control method based on online measurement | |
| CN104454027A (en) | Machining method of power turbine guider | |
| CN113806890A (en) | Verification method for machining process of turbine disc parts | |
| CN203405141U (en) | Position detecting device for inclined oil hole of engine camshaft hole | |
| CN106017254B (en) | A kind of electro spindle collet detection device | |
| CN217256255U (en) | Processing correcting needle for runner blade of hydraulic generator | |
| CN214291649U (en) | Handheld welding positioning tool | |
| CN110362038A (en) | Identify the test specimen and detection method of 5-shaft linkage numerical control lathe on-line checking ability | |
| CN219347560U (en) | Pin hole position degree gauge | |
| CN217096720U (en) | Device for preventing deformation of thin-wall deep hole caused by broaching | |
| CN104607699B (en) | Multi-ladder contoured reamer | |
| CN211740183U (en) | New energy automobile connecting piece axiality detection device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210115 |
|
| RJ01 | Rejection of invention patent application after publication |