CN109693006A - A kind of inner cavity means of defence of blade gaseous film control hole machined - Google Patents
A kind of inner cavity means of defence of blade gaseous film control hole machined Download PDFInfo
- Publication number
- CN109693006A CN109693006A CN201811539312.4A CN201811539312A CN109693006A CN 109693006 A CN109693006 A CN 109693006A CN 201811539312 A CN201811539312 A CN 201811539312A CN 109693006 A CN109693006 A CN 109693006A
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- blade
- inner cavity
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- filled
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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
- B23H3/00—Electrochemical machining, i.e. removing metal by passing current between an electrode and a workpiece in the presence of an electrolyte
-
- 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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to a kind of inner cavity means of defences of blade gaseous film control hole machined.This method comprises: the structure based on double-wall structure blade designs, using ultrasound detection, the wall thickness value of each Section Point of blade is measured, the double wall inner cavity gap width at each section of blade is obtained；It selects the higher hydrocarbon compound of relative melting points under semi-molten state as packing material, the protective action for being similar to enclosure wall is formed to being filled at the both ends open region of blade inner cavity according to double-wall structure feature；It after hydrocarbon compound solidification, selects the paraffin under fine melt state as packing material, cavity gap in double wall is filled up completely, the paraffin of filling is flowed to empty band, and solidification filling can be completed after region to be filled is sufficiently spread；Based on the actually detected wall thickness value and double wall inner cavity gap width at each section of blade, in cooling hole machined, the machined parameters that setting matches with detection data process the film cooling holes for meeting design requirement.
Description
Technical field
The present invention relates to technical field of electrolysis processing, protect more particularly to a kind of inner cavity of blade gaseous film control hole machined
Method.
Background technique
High to improve aero engine turbine blades operating temperature, great changes have occurred in blade cooling structure, from earliest
The cooling gaseous film control till now of the convection current of use allows inner cavity of the cooling air-flow from blade by many apertures or narrow slot
The outer surface for flowing to blade forms the lower air film of a channel temp in blade surface, can increase substantially cooling efficiency.And in leaf
On the inner-cavity structure of piece, in order to keep the distribution of cooling air-flow more reasonable, pushing away than 12 and the high-pressure turbine leaf of the above engine
In piece design, using double-wall structure, following Fig. 1.Gap between its inside and outside two layers of walls is only 0.6-0.8mm.Compared to single layer
The cooling duct being much made of intensive turbulence columns is distributed in double-wall structure blade small lumen in wall construction, complex-shaped,
It can further improve cooling efficiency.But new construction brings new problem to the processing of air film hole.
By taking existing electro-hydraulic beam, electric spark drill process as an example, main problem is that in processing feeding control very
Greatly, after machining small penetrates, because the gap to wall is minimum, it may appear that wound phenomenon, or even perforation can be processed.In order to completely eliminate
It is this that wall is wounded, it is ensured that for small lumen to wall without machining damage, most effective method is exactly physical protection, blocking electric spark,
The effect of electro-hydraulic beam and laser processing.
Therefore, for double wall small lumen structure blade, a kind of blade gaseous film control hole machined is inventor provided
Inner cavity means of defence.
Summary of the invention
Deficiency existing for technical method for the problem that existing processing double-layer wall construction blade, is damaged to inner cavity to wall,
Inventive embodiments provide a kind of inner cavity means of defence of blade gaseous film control hole machined, solve inner cavity to wall due to gap is small
The problem of wounding.
The embodiment of the present invention proposes a kind of inner cavity means of defence of blade gaseous film control hole machined, this method comprises:
Blade wall thickness is detected, the structure design based on double-wall structure blade is measured blade and each cut using ultrasound detection
The wall thickness value of millet cake obtains the double wall inner cavity gap width at each section of blade；
Pre-filled hydrocarbon compound selects the higher hydrocarbon compound of relative melting points under semi-molten state as filling material
Material, to being filled at the both ends open region of blade inner cavity, forms the protection work for being similar to enclosure wall according to double-wall structure feature
With；
Secondary filling paraffin selects the paraffin under fine melt state as filling after pre-filled hydrocarbon compound solidification
Material is filled up completely cavity gap in double wall, due to aforementioned pre-filled hydrocarbon compound inhibition, fills at this time
Paraffin to empty band flow, can be completed after region to be filled sufficiently spread solidify fill；
Machined parameters are set, based on the actually detected wall thickness value and double wall inner cavity gap width at each section of blade,
In cooling hole machined, the machined parameters that setting matches with detection data process the film cooling holes for meeting design requirement.
Further, in the method for the pre-filled hydrocarbon compound, in the filling process, which is in fritting
Melt, semi-solid state, selective filling is carried out to blade inner cavity, after it is fully cured, is similar in empty band formation
The protective action of enclosure wall, to stop the flow direction of secondary filling paraffin.
Further, in the method for the secondary filling paraffin, blade to be filled is placed into stone in the molten state
In wax, the paraffin of liquid is made to be completely filled with blade inner cavity, under the barrier effect of hydrocarbon compound, the paraffin of liquid is enclosed in double
Then cool down in cavity gap without overflowing in layer wall, paraffin is made to solidify and be full of cavity gap in entire.
Further, in the setting machined parameters, need to according to actually detected wall thickness value and double wall inner cavity gap width,
By cooling hole machined feed distance parameter setting corresponding at different wall thickness into processing program.
To sum up, the method closed and filled respectively using the different two media of heat fusion joint has been invented, has made to fill material
Material can preferably play insulating effect, in cooling hole machined, form effective protection to wall to double wall inner cavity, it is ensured that small
The processing quality in hole.
Detailed description of the invention
In order to illustrate the technical solution of the embodiments of the present invention more clearly, will make below to required in the embodiment of the present invention
Attached drawing is briefly described, it should be apparent that, drawings described below is only some embodiments of the present invention, for
For those of ordinary skill in the art, without creative efforts, it can also be obtained according to these attached drawings other
Attached drawing.
Fig. 1 is a kind of double-wall structure blade.
Fig. 2 is the blade section thickness schematic diagram of blade.
Fig. 3 is blade double-wall structure and surface air film hole.
Specific embodiment
Embodiments of the present invention are described in further detail with reference to the accompanying drawings and examples.Following embodiment it is detailed
Thin description and attached drawing cannot be used to limit the scope of the invention for illustratively illustrating the principle of the present invention, i.e., of the invention
It is not limited to described embodiment.
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.The application is described in detail below with reference to accompanying drawings and in conjunction with the embodiments.
If the double-wall structure of Fig. 1 is the innovation that high-pressure turbine blade structure designs, heat exchange efficiency is compared with single-wall structure
It greatly improves, is remarkably improved the temperature capability of blade, be the development of the following advanced aero engine high-pressure turbine blade structure
Trend.
Electric spark drilling is the relatively broad technology of domestic application, in Multiple Type engine turbine blade drilling
It is applied.Electro-hydraulic beam technology as cold machining process is with its " three nothing " (no recast layer, non-microcracked, without heat affected area)
High-quality is widely applied in the processing of China's Multiple Type aero-engine monocrystalline high-pressure turbine blade air film hole,
The processing for realizing the big aspect ratio aperture in various apertures becomes the potential technique for solving double-wall structure blade air film hole machined.
It is limited to narrow interior cavity gap, using existing electric spark, electro-hydraulic beam method for drilling to avoid wounding wall, only
The stroke of machined electrode can be accurately controlled, to terminate processing at once in the moment that machining small penetrates.But the nothing in actual processing
Method is realized.First is the outer wall of blade for thickness design, and the stroke penetrated can not accurately make a reservation for；Second is based on blade inner cavity
Complexity, especially processing high inclination-angle aperture.After just penetrating, current hole is often had not been completed, it is necessary to exit
Tilting section continues to process, and wounding to wall for small―gap suture inner cavity not can avoid substantially.And in laser punching, howsoever accurate control
System processing stroke, it is more serious to the damage of wall if do not blocked to laser beam.
Deficiency existing for technical method of the present invention for existing processing double-layer wall construction blade, is damaged to inner cavity to wall
Problem proposes a kind of complicated cooling structure-double-wall structure blade air film hole forming method, solves inner cavity to wall " back is hurt "
The problem of.
Referring to FIG. 1 to FIG. 3, a kind of inner cavity means of defence for blade gaseous film control hole machined that the embodiment of the present invention provides
At least include the following steps S110~step S150:
Step S110 is detection blade wall thickness, the structure design based on double-wall structure blade, using ultrasound detection, measurement
The wall thickness value of each Section Point of blade obtains the double wall inner cavity gap width at each section of blade.
Step S120 is pre-filled hydrocarbon compound, selects the higher hydrocarbon compound of relative melting points under semi-molten state
As packing material, according to double-wall structure feature, to being filled at the both ends open region of blade inner cavity, is formed to be similar to and be enclosed
The protective action of wall can sufficiently be expanded with hindering the filler of subsequent paraffin to flow to empty band in region to be filled
Solidification filling is completed after dissipating.
Bis- filling paraffin of step S130 select the paraffin under fine melt state after pre-filled hydrocarbon compound solidification
As packing material, cavity gap in double wall is filled up completely, due to aforementioned pre-filled hydrocarbon compound inhibition,
The paraffin filled at this time is flowed to empty band, and solidification filling can be completed after region to be filled is sufficiently spread.
In this step, paraffin has corrosion-resistant, easy filling, the easily good feature of removal and insulation effect as filler,
Process can be eliminated wounds influence.
Step S140 is setting machined parameters, based in the actually detected wall thickness value and double wall at each section of blade
Cavity gap value, in cooling hole machined, the machined parameters that setting matches with detection data process the gas for meeting design requirement
Film cooling hole.
For details, reference can be made to following embodiments:
In step s 110, shown in Figure 3 is typical double layer wall construction turbo blade schematic cross-section.It is shown in figure
Position from K1 to K16 on blade.Using CT scan measurement double-wall structure blade cooling hole machined part thickness direction
The wall thickness value of different cross section.
In the step s 120, by practice, select certain hydrocarbon compound as pre-filled inner cavity protection materials.It is led
Wanting ingredient is solid alkane, is faint yellow translucent solid, density 0.9g/cm3, in the filling process, the compound is in half
Melting, semi-solid state carry out selective filling to blade inner cavity, after it is fully cured, " enclose in empty band formation
The effect of wall " lays the foundation for secondary filling.
In step s 130, after completion is pre-filled, start to carry out secondary filling.Select paraffin as secondary filler.It should
Material is about melted at 60 DEG C, and mobility is preferable.Blade to be filled is placed in paraffin in the molten state, the paraffin of liquid
Blade inner cavity will be completely filled with.At this moment " enclosure wall " of pre-filled formation begins to play a role, it closes the paraffin under liquid
Without overflowing in cavity gap in double wall.As temperature is gradually reduced, paraffin solidifies and is full of cavity gap in entire, will not
There is " hole " phenomenon.
Cured paraffin will not only carry out negative effect to electrode band in process, but also can be effectively to inner cavity to wall shape
It is a kind of good protection materials at good protective effect.
It is (as follows based on the wall thickness value for using CT scan to measure certain blade different cross section in step S110 in step S140
Shown in table 1), in the specific exhaust fenestra of processing, according to wall thickness measured value, double wall inner cavity gap width is obtained, by differentiation
Feed distance parameter setting is into processing program.In process, it is exhausted to be aided with inner cavity for the setting of differentiation feed distance parameter
The filling of edge material realizes small―gap suture inner cavity to the effective protection of wall, completes the electro-hydraulic beam system of this kind of labyrinth blade
Hole.Using method of the invention, double-wall structure processing is realized on blade, as shown in Figure 3.
Each point wall thickness value at 1 different cross section of table and position
The above description is only an example of the present application, and the invention is not limited to described above and be shown in figure
Particular step and structure.Also, the detailed description to known method technology for brevity, is omitted here.It is not departing from
In the case where the scope of the present invention to those skilled in the art, various changes and changes are possible in this application.It is all this
Any modification, equivalent replacement, improvement and so within the spirit and principle of application, should be included in claims hereof
In range.
Claims (5)
1. a kind of inner cavity means of defence of blade gaseous film control hole machined characterized by comprising
Blade wall thickness is detected, the structure design based on double-wall structure blade measures each Section Point of blade using ultrasound detection
Wall thickness value, obtain the double wall inner cavity gap width at each section of blade；
Pre-filled hydrocarbon compound selects the higher hydrocarbon compound of relative melting points under semi-molten state as packing material,
The protective action for being similar to enclosure wall is formed to being filled at the both ends open region of blade inner cavity according to double-wall structure feature；
Secondary filling paraffin selects paraffin under fine melt state as packing material after pre-filled hydrocarbon compound solidification,
Cavity gap in double wall is filled up completely, due to aforementioned pre-filled hydrocarbon compound inhibition, the stone filled at this time
Wax is flowed to empty band, and solidification filling can be completed after region to be filled is sufficiently spread；
Machined parameters are set, based on the actually detected wall thickness value and double wall inner cavity gap width at each section of blade, cold
But when hole machined, the machined parameters that setting matches with detection data process the film cooling holes for meeting design requirement.
2. the inner cavity means of defence of blade gaseous film control hole machined according to claim 1, which is characterized in that the detection
In blade wall thickness method, blade cooling hole machined part thickness direction is chosen in the structure design based on double-wall structure blade
Section Point is as each measurement point.
3. the inner cavity means of defence of blade gaseous film control hole machined according to claim 1, which is characterized in that the pre-fill
It fills in the method for hydrocarbon compound, in the filling process, which is in semi-molten, semi-solid state, to blade inner cavity
Selective filling is carried out, after it is fully cured, forms the protective action for being similar to enclosure wall in empty band, it is secondary to stop
Fill the flow direction of paraffin.
4. the inner cavity means of defence of blade gaseous film control hole machined according to claim 1, which is characterized in that described secondary
In the method for filling paraffin, blade to be filled is placed in paraffin in the molten state, be completely filled with the paraffin of liquid
Blade inner cavity, under the barrier effect of hydrocarbon compound, the paraffin of liquid is enclosed in double wall in cavity gap without overflowing,
Then cool down, paraffin is made to solidify and be full of cavity gap in entire.
5. the inner cavity means of defence of blade gaseous film control hole machined according to claim 1, which is characterized in that the setting
It, need to be according to actually detected wall thickness value and double wall inner cavity gap width, by cooling hole corresponding at different wall thickness in machined parameters
Feed distance parameter setting is processed into processing program.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811539312.4A CN109693006B (en) | 2018-12-17 | 2018-12-17 | Inner cavity protection method for blade air film cooling hole machining |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811539312.4A CN109693006B (en) | 2018-12-17 | 2018-12-17 | Inner cavity protection method for blade air film cooling hole machining |
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| CN109693006A true CN109693006A (en) | 2019-04-30 |
| CN109693006B CN109693006B (en) | 2020-06-05 |
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| CN201811539312.4A Active CN109693006B (en) | 2018-12-17 | 2018-12-17 | Inner cavity protection method for blade air film cooling hole machining |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110524072A (en) * | 2019-08-30 | 2019-12-03 | 中国航发动力股份有限公司 | A kind of guide vane air film hole combined machining method |
| CN111763809A (en) * | 2020-06-10 | 2020-10-13 | 中国航发北京航空材料研究院 | Protection device for spray-forbidden region in inner cavity of hollow blade and assembly method |
| CN112475490A (en) * | 2020-11-12 | 2021-03-12 | 中国航发沈阳黎明航空发动机有限责任公司 | Wall-to-wall protection method for gas film hole at seam groove part of flame tube in electric spark machining |
| CN113461412A (en) * | 2021-06-25 | 2021-10-01 | 西安交通大学 | Core-shell integrated casting mold with controllable gap and preparation method and application thereof |
| CN114083146A (en) * | 2021-10-27 | 2022-02-25 | 中国航发北京航空材料研究院 | Ultrafast laser processing method for double-wall ultra-air cooling turbine blade air film cooling tank |
| CN114406380A (en) * | 2022-01-24 | 2022-04-29 | 中国航空制造技术研究院 | Method and equipment for quickly determining electrochemical hole-making machining stroke on line |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0267718A2 (en) * | 1986-11-13 | 1988-05-18 | Chromalloy Gas Turbine Corporation | Airfoil with diffused cooling holes and method and apparatus for making the same |
| US20040109765A1 (en) * | 2002-12-02 | 2004-06-10 | Alstom Technology Ltd. | Turbine blade |
| CN102335789A (en) * | 2011-11-11 | 2012-02-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Device and method for removing re-melting layers on inner walls of air film holes of blades |
| CN104801800A (en) * | 2015-04-14 | 2015-07-29 | 南京航空航天大学 | Small-pore electromechanical and combined processed insulation material coating contrast method and application |
| CN104907492A (en) * | 2015-05-07 | 2015-09-16 | 西安交通大学 | Making method of surface double-walled hollow turbine blade |
| US20160221124A1 (en) * | 2015-01-30 | 2016-08-04 | United Technologies Corporation | Method For Disposing A Blocking Material |
| CN106239031A (en) * | 2016-08-29 | 2016-12-21 | 中航动力股份有限公司 | A kind of method preventing film cooling holes welding blocking |
| CN106624232A (en) * | 2016-11-29 | 2017-05-10 | 贵阳中航动力精密铸造有限公司 | Precise machining method for conical film holes of turbine guide blade |
| CN106735657A (en) * | 2016-12-27 | 2017-05-31 | 成都鑫胜太数控设备有限公司 | A kind of processing method of aero-engine bilayer turbine blade film cooling holes |
| CN207735791U (en) * | 2017-12-27 | 2018-08-17 | 中国科学院西安光学精密机械研究所 | Femtosecond laser processing device with thermal barrier coating blade air film hole |
-
2018
- 2018-12-17 CN CN201811539312.4A patent/CN109693006B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0267718A2 (en) * | 1986-11-13 | 1988-05-18 | Chromalloy Gas Turbine Corporation | Airfoil with diffused cooling holes and method and apparatus for making the same |
| US20040109765A1 (en) * | 2002-12-02 | 2004-06-10 | Alstom Technology Ltd. | Turbine blade |
| CN102335789A (en) * | 2011-11-11 | 2012-02-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Device and method for removing re-melting layers on inner walls of air film holes of blades |
| US20160221124A1 (en) * | 2015-01-30 | 2016-08-04 | United Technologies Corporation | Method For Disposing A Blocking Material |
| CN104801800A (en) * | 2015-04-14 | 2015-07-29 | 南京航空航天大学 | Small-pore electromechanical and combined processed insulation material coating contrast method and application |
| CN104907492A (en) * | 2015-05-07 | 2015-09-16 | 西安交通大学 | Making method of surface double-walled hollow turbine blade |
| CN106239031A (en) * | 2016-08-29 | 2016-12-21 | 中航动力股份有限公司 | A kind of method preventing film cooling holes welding blocking |
| CN106624232A (en) * | 2016-11-29 | 2017-05-10 | 贵阳中航动力精密铸造有限公司 | Precise machining method for conical film holes of turbine guide blade |
| CN106735657A (en) * | 2016-12-27 | 2017-05-31 | 成都鑫胜太数控设备有限公司 | A kind of processing method of aero-engine bilayer turbine blade film cooling holes |
| CN207735791U (en) * | 2017-12-27 | 2018-08-17 | 中国科学院西安光学精密机械研究所 | Femtosecond laser processing device with thermal barrier coating blade air film hole |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110524072A (en) * | 2019-08-30 | 2019-12-03 | 中国航发动力股份有限公司 | A kind of guide vane air film hole combined machining method |
| CN111763809A (en) * | 2020-06-10 | 2020-10-13 | 中国航发北京航空材料研究院 | Protection device for spray-forbidden region in inner cavity of hollow blade and assembly method |
| CN111763809B (en) * | 2020-06-10 | 2021-10-15 | 中国航发北京航空材料研究院 | Protection device for spray-forbidden region in inner cavity of hollow blade and assembly method |
| CN112475490A (en) * | 2020-11-12 | 2021-03-12 | 中国航发沈阳黎明航空发动机有限责任公司 | Wall-to-wall protection method for gas film hole at seam groove part of flame tube in electric spark machining |
| CN112475490B (en) * | 2020-11-12 | 2022-08-19 | 中国航发沈阳黎明航空发动机有限责任公司 | Wall-to-wall protection method for air film hole at seam groove part of flame tube in electric spark machining |
| CN113461412A (en) * | 2021-06-25 | 2021-10-01 | 西安交通大学 | Core-shell integrated casting mold with controllable gap and preparation method and application thereof |
| CN113461412B (en) * | 2021-06-25 | 2022-08-16 | 西安交通大学 | Core-shell integrated casting mold with controllable gap and preparation method and application thereof |
| CN114083146A (en) * | 2021-10-27 | 2022-02-25 | 中国航发北京航空材料研究院 | Ultrafast laser processing method for double-wall ultra-air cooling turbine blade air film cooling tank |
| CN114083146B (en) * | 2021-10-27 | 2024-04-09 | 中国航发北京航空材料研究院 | Ultra-fast laser processing method for double-wall ultra-air cooling turbine blade air film cooling groove |
| CN114406380A (en) * | 2022-01-24 | 2022-04-29 | 中国航空制造技术研究院 | Method and equipment for quickly determining electrochemical hole-making machining stroke on line |
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