CN104001857B - A kind of Gas Turbine guide vane and precision casting technology thereof - Google Patents
A kind of Gas Turbine guide vane and precision casting technology thereof Download PDFInfo
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- CN104001857B CN104001857B CN201410249952.7A CN201410249952A CN104001857B CN 104001857 B CN104001857 B CN 104001857B CN 201410249952 A CN201410249952 A CN 201410249952A CN 104001857 B CN104001857 B CN 104001857B
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Abstract
A kind of Gas Turbine guide vane and precision casting technology thereof, it relates to a kind of guide vane and process thereof.The present invention's problem that the working (machining) efficiency existed in existing process technology is low in order to solve, percent defective is high.A kind of Gas Turbine guide vane of the present invention, it comprises at least two blade bodies, supramarginal plate, inframarginal and venturi; Supramarginal plate and inframarginal lay respectively at the two ends of blade body, and adjacent two blade bodies are provided with venturi; Its preparation method is: step one: molding: on wax injector, select mid temperature wax, suppress by the shape of required Gas Turbine guide vane, take out after obtained wax-pattern pressurize 20-30s, then revise wax-pattern and make its zero defect, then the assembling of dead head is carried out to wax-pattern.The present invention is used for the manufacture of Gas Turbine guide vane.
Description
Technical field
The present invention relates to a kind of guide vane and process thereof, be specifically related to a kind of Gas Turbine guide vane and precision casting technology thereof.
Background technology
Gas-turbine power plant has the advantages such as quality is light, volume is little, water, electricity and oil consumption are few, and starting is fast, control is convenient, vulnerable part is few, reliable and easy to maintenance, has been widely used in big-and-middle-sized surface ship at present.Guide vane is the critical component of Gas Turbine, and the core technology of gas turbine high temperature alloy vane manufacture is monopolized by English, the United States, Russia Luo Si, Japan and other countries always, and China is domestic to be limited always, and slower development, gas turbine can not get tremendous development.
Summary of the invention
The object of the invention is to solve existing Gas Turbine guide vane slower development, every physical and chemical index is difficult to reach typical problem, and then provides a kind of Gas Turbine guide vane and precision casting technology thereof.
Technical scheme of the present invention is: a kind of Gas Turbine guide vane and precision casting technology thereof, and concrete steps are:
Step one: molding: on wax injector, selects mid temperature wax, suppresses by the die mould of required Gas Turbine guide vane, takes out after obtained wax-pattern pressurize 20-30s, then revises wax-pattern and makes its zero defect, then carry out the assembling of dead head to wax-pattern;
Step 2: shell processed: the wax-pattern outer surface obtained in step one, total silicon sol adhesive is selected to make shell, the ground floor of shell and the powder of the second layer are fining agent, third layer adopts mullite sand powder to be made into high-strength fireproof coating, then carry out air-dry to shell, until after shell reaches the intensity of regulation, adopt steam to dewax, dewaxing temperature is 140-160 DEG C, pressure is 0.4-0.6MPa, the dwell time is 10-15 minute;
Step 3: vacuum smelting smelting and pouring: the shell outer wrapping insulation quilt described in step 2, then roasting is carried out, sintering temperature is 850-950 DEG C, vacuum induction casting stove is adopted to carry out vacuum metling and vacuum pouring respectively afterwards, obtain required foundry goods, after casting complete, the foundry goods obtained is kept under vacuum conditions take out after 10-15 minute, be put in incubator and cool;
Step 4: vacuum heat: austenitizing process is carried out to the foundry goods obtained in step 3, austenitizing temperature is 1160-1180 DEG C, and be then incubated 3-5 hour, blowing argon gas cools afterwards; Then carry out first time Ageing Treatment, the temperature of Ageing Treatment is 1000-1100 DEG C, temperature retention time 3-5 hour for the first time, carries out blowing argon gas cooling afterwards; Then carry out second time Ageing Treatment, the temperature of second time Ageing Treatment is 800-950 DEG C, and temperature retention time is 15-17 hour, then obtains described Gas Turbine guide vane after carrying out blowing argon gas cooling.
Present invention also offers a kind of Gas Turbine guide vane adopting above-mentioned precision casting technology to prepare, comprise at least two blade bodies, supramarginal plate and inframarginal; Supramarginal plate and inframarginal lay respectively at the two ends of blade body, and adjacent two blade bodies are provided with venturi, and blade body, supramarginal plate and inframarginal are integrally formed.
Present invention also offers a kind of nozzle ring, it has above-mentioned Gas Turbine guide vane.
Present invention also offers a kind of gas turbine, it has above-mentioned nozzle ring.
The present invention compared with prior art has following effect:
The present invention adopts the process of new type high temperature foundry alloy production combustion engine turbine guide vane, by arranging rational technological parameter, coordinating advanced equipment, making the every physical and chemical index of blade produced, reach external highest level of producing identical product, technology belongs to domestically leading.The turbine guide vane chip architecture of this invention is two panels guide vane duplex composition, and length of blade reaches 400mm most, and blade path is that the venturi of blade is made up of two panels blade three-dimensional torsional without surplus casting, and bulk is shunk large.
Accompanying drawing explanation
Fig. 1 is the front view of Gas Turbine guide vane of the present invention.
Fig. 2 is the side view of Gas Turbine guide vane of the present invention.
Detailed description of the invention
Detailed description of the invention one: composition graphs 1 and Fig. 2 illustrate present embodiment, present embodiment comprises a kind of precision casting technology of Gas Turbine guide vane, and concrete steps are:
Step one: molding: on wax injector, selects mid temperature wax, suppresses by the die mould of required Gas Turbine guide vane, takes out after obtained wax-pattern pressurize 20-30s, then revises wax-pattern and makes its zero defect, then carry out the assembling of dead head to wax-pattern;
Step 2: shell processed: the wax-pattern outer surface obtained in step one, total silicon sol adhesive is selected to make shell, the ground floor of shell and the powder of the second layer are fining agent, third layer adopts mullite sand powder to be made into high-strength fireproof coating, then carry out air-dry to shell, until after shell reaches the intensity of regulation, adopt steam to dewax, dewaxing temperature is 140-160 DEG C, pressure is 0.4-0.6MPa, the dwell time is 10-15 minute;
Step 3: vacuum smelting smelting and pouring: the shell outer wrapping insulation quilt described in step 2, then roasting is carried out, sintering temperature is 850-950 DEG C, vacuum induction casting stove is adopted to carry out vacuum metling and vacuum pouring respectively afterwards, obtain required foundry goods, after casting complete, the foundry goods obtained is kept under vacuum conditions take out after 10-15 minute, be put in incubator and cool;
Step 4: vacuum heat: austenitizing process is carried out to the foundry goods obtained in step 3, austenitizing temperature is 1160-1180 DEG C, and be then incubated 3-5 hour, blowing argon gas cools afterwards; Then carry out first time Ageing Treatment, the temperature of Ageing Treatment is 1000-1100 DEG C, temperature retention time 3-5 hour for the first time, carries out blowing argon gas cooling afterwards; Then carry out second time Ageing Treatment, the temperature of second time Ageing Treatment is 800-950 DEG C, and temperature retention time is 15-17 hour, then obtains described Gas Turbine guide vane after carrying out blowing argon gas cooling.
The inventive method adopts mid temperature wax compacting wax-pattern at pattern making procedure, designer completes the three-dimensional entity model of foundry goods and running gate system by Three-dimensional Design Software, determine that the heat energy-saving position of foundry goods and casting flaw may occur position by the cooled and solidified order of computer simulation casting process afterwards, realize optimizing pouring system function.Coating adopts the total silicon colloidal sol of domestic advanced person as binding agent, coordinates advanced fining agent to use, can obtain good hot strength of investment shell and high temperature stability like this, and make foundry goods obtain surface grain refinement.
Advanced vacuum metling and vacuum casting method are adopted to new type high temperature foundry alloy, coordinates the strict control that its rational parameter has been come it.Adopt advanced vacuum heat treatment furnace to carry out vacuum heat to blade, realize the excellent interior tissue of foundry goods and performance by a solution treated and secondary ageing process, to meet every physicochemical requirements of foundry goods:
Be specially: chemical composition: C:0.07-0.15; Cr19.0-22; Co:9.3-12.1; Ti2.9-3.9; Fe :≤0.5; Mn :≤0.4; Si :≤0.3;
Mechanical behavior under high temperature: tensile strength: in 900 DEG C of situations, tensile strength is not less than 460MPa; Percentage elongation: be not less than 7%; Creep rupture strength: in 900 DEG C of situations, tension is not less than 210MPa, and the time is not less than 100h;
Low power grain size: the exhaust limit place of blade body 1 is not more than 5 grades (2.82mm), and other positions are not more than 7 grades (5.64mm).
Wherein, concrete fusion process is: by vacuum drying oven charging and power transmission, after melting stage, refining period, load shell, vacuumize and pour into a mould under vacuum is not more than 1Pa state, then shell parks vacuum breaker after 4-7 minute, takes out.
Detailed description of the invention two: composition graphs 2 illustrates present embodiment, in step 3, the temperature of vacuum pouring is 1470-1520 DEG C, and the speed of vacuum pouring is 3-8 rod second one.Other is identical with detailed description of the invention one.
Detailed description of the invention three: composition graphs 2 illustrates present embodiment, a kind of Gas Turbine guide vane adopting above-mentioned precision casting technology to prepare of present embodiment, comprises at least two blade bodies 1, supramarginal plate 2 and inframarginal 3; Supramarginal plate 2 and inframarginal 3 lay respectively at the two ends of blade body 1, and adjacent two blade bodies 1 are provided with venturi 4, and blade body 1, supramarginal plate 2 and inframarginal 3 are integrally formed.
Detailed description of the invention four: composition graphs 2 illustrates present embodiment, a kind of nozzle ring of present embodiment, it has above-mentioned Gas Turbine guide vane.
Detailed description of the invention five: composition graphs 2 illustrates present embodiment, a kind of gas turbine of present embodiment, it has above-mentioned nozzle ring.
Foregoing is only preferred embodiment of the present invention; not for limiting embodiment of the present invention; those of ordinary skill in the art are according to central scope of the present invention and spirit; can carry out corresponding flexible or amendment very easily, therefore protection scope of the present invention should be as the criterion with the protection domain required by claims.
Claims (5)
1. a precision casting technology for Gas Turbine guide vane, is characterized in that, concrete steps are:
Step one: molding: on wax injector, selects mid temperature wax, suppresses by the die mould of required Gas Turbine guide vane, takes out after obtained wax-pattern pressurize 20-30s, then revises wax-pattern and makes its zero defect, then carry out the assembling of dead head to wax-pattern;
Step 2: shell processed: the wax-pattern outer surface obtained in step one, silica sol binder makes shell, the ground floor of shell and the powder of the second layer are fining agent, third layer adopts mullite sand powder to be made into high-strength fireproof coating, then carry out air-dry to shell, until after shell reaches the intensity of regulation, adopt steam to dewax, dewaxing temperature is 140-160 DEG C, pressure is 0.4-0.6MPa, the dwell time is 10-15 minute;
Step 3: vacuum smelting smelting and pouring: the shell outer wrapping insulation quilt described in step 2, then roasting is carried out, sintering temperature is 850-950 DEG C, vacuum induction casting stove is adopted to carry out vacuum metling and vacuum pouring respectively afterwards, obtain required foundry goods, after casting complete, the foundry goods obtained is kept under vacuum conditions take out after 10-15 minute, be put in incubator and cool;
Step 4: vacuum heat: austenitizing process is carried out to the foundry goods obtained in step 3, austenitizing temperature is 1160-1180 DEG C, and be then incubated 3-5 hour, blowing argon gas cools afterwards; Then carry out first time Ageing Treatment, the temperature of Ageing Treatment is 1000-1100 DEG C, temperature retention time 3-5 hour for the first time, carries out blowing argon gas cooling afterwards; Then carry out second time Ageing Treatment, the temperature of second time Ageing Treatment is 800-950 DEG C, and temperature retention time is 15-17 hour, then obtains described Gas Turbine guide vane after carrying out blowing argon gas cooling;
The mechanical behavior under high temperature of obtained Gas Turbine guide vane: tensile strength: in 900 DEG C of situations, tensile strength is not less than 460MPa; Percentage elongation: be not less than 7%; Creep rupture strength: in 900 DEG C of situations, tension is not less than 210MPa, and the time is not less than 100h; Low power grain size: the exhaust limit place of blade body 1 is not more than 2.82mm, and other positions are not more than 5.64mm.
2. a precision casting technology for Gas Turbine guide vane as claimed in claim 1, is characterized in that, in described step 3, the temperature of vacuum pouring is 1470-1520 DEG C, and the speed of vacuum pouring is 5-8 second one group.
3. adopt a Gas Turbine guide vane prepared by precision casting technology described in claim 1, it is characterized in that, comprise at least two blade bodies (1), supramarginal plate (2) and inframarginal (3); Supramarginal plate (2) and inframarginal (3) lay respectively at the two ends of blade body (1), adjacent two blade bodies (1) are provided with venturi (4), and blade body (1), supramarginal plate (2) and inframarginal (3) are integrally formed.
4. a nozzle ring, it has Gas Turbine guide vane as claimed in claim 3.
5. a gas turbine, it has nozzle ring as claimed in claim 4.
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| CN104550735A (en) * | 2015-02-08 | 2015-04-29 | 哈尔滨鑫润工业有限公司 | Precision casting method of last stage extra-long guide blade for million-kilowatt nuclear power unit |
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| CN105618676A (en) * | 2015-12-29 | 2016-06-01 | 青岛博泰美联化工技术有限公司 | Environment-friendly preparation method for automobile engine shell |
| CN105618679A (en) * | 2015-12-30 | 2016-06-01 | 青岛博泰美联化工技术有限公司 | Preparation method for automobile charging turbine |
| CN105537518A (en) * | 2015-12-30 | 2016-05-04 | 青岛博泰美联化工技术有限公司 | Preparation method of engine component |
| CN107138679A (en) * | 2017-05-05 | 2017-09-08 | 山东齐林电力设备股份有限公司 | Micro-vacuum precision casting process |
| CN107457358B (en) * | 2017-08-24 | 2018-12-14 | 西安中工动力能源有限公司 | The casting method of miniature gas turbine turbine rotor |
| CN108672657A (en) * | 2018-05-24 | 2018-10-19 | 哈尔滨鑫润工业有限公司 | Improve the process of the hot investment casting of extraordinary combustion engine rectification pillar high temperature resistance |
| CN108941455B (en) * | 2018-07-27 | 2020-08-14 | 沈阳中科三耐新材料股份有限公司 | Casting method of duplex turbine guide vane for gas turbine |
| CN109093072B (en) * | 2018-07-27 | 2020-11-17 | 沈阳中科三耐新材料股份有限公司 | Casting process of turbine blade for gas turbine |
| CN111206964A (en) * | 2018-11-22 | 2020-05-29 | 中发天信(北京)航空发动机科技股份有限公司 | Integrally cast aeroengine turbine guider and preparation method thereof |
| CN109622888B (en) * | 2018-12-20 | 2021-04-06 | 航天海鹰(哈尔滨)钛业有限公司 | Casting forming process of complex high-temperature alloy multi-connection guide blade casting |
| CN113857430B (en) * | 2021-08-23 | 2023-10-13 | 中国科学院金属研究所 | Blade deformation control method and application |
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