CN104001857A - Guide blade of gas turbine and precise casting technique of guide blade - Google Patents
Guide blade of gas turbine and precise casting technique of guide blade Download PDFInfo
- Publication number
- CN104001857A CN104001857A CN201410249952.7A CN201410249952A CN104001857A CN 104001857 A CN104001857 A CN 104001857A CN 201410249952 A CN201410249952 A CN 201410249952A CN 104001857 A CN104001857 A CN 104001857A
- Authority
- CN
- China
- Prior art keywords
- gas turbine
- wax
- temperature
- guide vane
- vacuum
- 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.)
- Granted
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a guide blade of a gas turbine and a precise casting technique of the guide blade, aiming at solving the problem of low machining efficiency and high rejection rate in the prior art. The guide blade of the gas turbine comprises at least two blade main bodies, an upper edge plate, a lower edge plate and a throat channel, wherein the upper and lower edge plates are arranged at two ends of the blade main bodies; the throat channel is formed between each two adjacent blade main bodies. A manufacturing method comprises the following steps: (1) preparing a mold, namely, pressing selected medium-temperature wax material on a wax pressing machine according to the shape of the guide blade of the gas turbine, maintaining the pressure of the prepared wax mold for 20-30 seconds; taking the wax mold out and amending so as to enable the wax mold to be flawless; and assembling a casting head of the wax mold. The precise casting technique is suitable for manufacturing the guide blade of the gas turbine.
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 that quality is light, volume is little, water, electricity and oil consumption few, starting is fast, control the advantages such as convenient, vulnerable part is few, reliable and easy to maintenance, has been widely used at present big-and-middle-sized surface ship.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 Luo Si of the United States, Russia, Japan and other countries always, and China is domestic to be limited always, slower development, and gas turbine can not get tremendous development.
Summary of the invention
The object of the invention is in order to solve existing Gas Turbine guide vane slower development, every physical and chemical index is difficult to reach typical problem, and then a kind of Gas Turbine guide vane and precision casting technology thereof are provided.
Technical scheme of the present invention is: a kind of Gas Turbine guide vane and precision casting technology thereof, and concrete steps are:
Step 1: molding: on wax injector, select middle temperature wax material, suppress by the die mould of required Gas Turbine guide vane, take out after the wax-pattern pressurize 20-30s making, then revise wax-pattern and make its zero defect, then wax-pattern is carried out to the assembling of dead head;
Step 2: shell processed: the wax-pattern outer surface obtaining in step 1, select total silicon sol adhesive to make shell, the ground floor of shell and the powder of the second layer are fining agent, the 3rd layer adopts mullite sand powder to be made into high-strength fireproof coating, then to shell, carry out air-dry, until shell reaches after the intensity of regulation, adopt steam to dewax, dewaxing temperature is that 140-160 ℃, pressure are that 0.4-0.6MPa, dwell time are 10-15 minute;
Step 3: vacuum smelting smelting and pouring: at the shell outer wrapping insulation quilt described in step 2, then carry out roasting, sintering temperature is 850-950 ℃, adopt afterwards vacuum induction casting stove to carry out respectively vacuum metling and vacuum pouring, obtain required foundry goods, after casting complete, the foundry goods obtaining is kept under vacuum state after 10-15 minute taking out, be put in incubator, carry out cooling;
Step 4: vacuum heat: the foundry goods obtaining in step 3 is carried out to austenitizing processing, and austenitizing temperature is 1160-1180 ℃, is then incubated 3-5 hour, and blowing argon gas carries out cooling afterwards; Then carry out Ageing Treatment for the first time, the temperature of Ageing Treatment is 1000-1100 ℃ for the first time, and temperature retention time 3-5 hour carries out blowing argon gas cooling afterwards; Then carry out Ageing Treatment for the second time, the temperature of Ageing Treatment is 800-950 ℃ for the second time, and temperature retention time is 15-17 hour, then carries out blowing argon gas and obtain described Gas Turbine guide vane after cooling.
The present invention also provides a kind of Gas Turbine guide vane that adopts above-mentioned precision casting technology to prepare, and comprises 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.
The present invention also provides a kind of nozzle ring, and it has above-mentioned Gas Turbine guide vane.
The present invention also provides a kind of gas turbine, and 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 machine turbine guide vane sheet, by rational technological parameter is set, coordinate advanced equipment, make the every physical and chemical index of blade of producing, reach the highest level of external production product of the same race, it is domestically leading that technology belongs to.The turbine guide vane chip architecture of this invention is that two guide vane duplexs form, and length of blade reaches 400mm most, and blade path is that the venturi of blade is comprised of two blade three-dimensional torsionals 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.
The specific embodiment
The specific embodiment one: in conjunction with Fig. 1 and Fig. 2, present embodiment is described, present embodiment comprises a kind of precision casting technology of Gas Turbine guide vane, and concrete steps are:
Step 1: molding: on wax injector, select middle temperature wax material, suppress by the die mould of required Gas Turbine guide vane, take out after the wax-pattern pressurize 20-30s making, then revise wax-pattern and make its zero defect, then wax-pattern is carried out to the assembling of dead head;
Step 2: shell processed: the wax-pattern outer surface obtaining in step 1, select total silicon sol adhesive to make shell, the ground floor of shell and the powder of the second layer are fining agent, the 3rd layer adopts mullite sand powder to be made into high-strength fireproof coating, then to shell, carry out air-dry, until shell reaches after the intensity of regulation, adopt steam to dewax, dewaxing temperature is that 140-160 ℃, pressure are that 0.4-0.6MPa, dwell time are 10-15 minute;
Step 3: vacuum smelting smelting and pouring: at the shell outer wrapping insulation quilt described in step 2, then carry out roasting, sintering temperature is 850-950 ℃, adopt afterwards vacuum induction casting stove to carry out respectively vacuum metling and vacuum pouring, obtain required foundry goods, after casting complete, the foundry goods obtaining is kept under vacuum state after 10-15 minute taking out, be put in incubator, carry out cooling;
Step 4: vacuum heat: the foundry goods obtaining in step 3 is carried out to austenitizing processing, and austenitizing temperature is 1160-1180 ℃, is then incubated 3-5 hour, and blowing argon gas carries out cooling afterwards; Then carry out Ageing Treatment for the first time, the temperature of Ageing Treatment is 1000-1100 ℃ for the first time, and temperature retention time 3-5 hour carries out blowing argon gas cooling afterwards; Then carry out Ageing Treatment for the second time, the temperature of Ageing Treatment is 800-950 ℃ for the second time, and temperature retention time is 15-17 hour, then carries out blowing argon gas and obtain described Gas Turbine guide vane after cooling.
The inventive method is warm wax material compacting wax-pattern in pattern making procedure adopts, designer completes the three-dimensional entity model of foundry goods and running gate system by Three-dimensional Design Software, by the cooled and solidified of computer simulation casting process, sequentially come to determine that position may appear in the heat energy-saving position of foundry goods and casting flaw afterwards, realize optimizing pouring system function.Coating adopts domestic advanced person's total silicon colloidal sol as binding agent, coordinates advanced fining agent to use, and can obtain good hot strength of investment shell and high temperature stability like this, and make foundry goods obtain surface grain refinement.
New type high temperature foundry alloy is adopted to advanced vacuum metling and vacuum casting method, coordinate its rational parameter to complete the strict control to it.Adopt advanced vacuum heat treatment furnace to carry out vacuum heat to blade, by solution treated and secondary ageing, process to realize the good interior tissue of foundry goods and performance, to meet every physics and chemistry of foundry goods, require:
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 ℃ of situations, tensile strength is not less than 460MPa; Percentage elongation: be not less than 7%; Creep rupture strength: in 900 ℃ of situations, tension is not less than 210MPa, and the time is not less than 100h;
Low power grain size: the place, exhaust limit 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, pack shell into, vacuumize in vacuum and be not more than under 1Pa state and pour into a mould, then shell is parked vacuum breaker after 4-7 minute, takes out.
The specific embodiment two: in conjunction with Fig. 2, present embodiment is described, in step 3, the temperature of vacuum pouring is 1470-1520 ℃, the speed of vacuum pouring is 3-8 rod second one.Other is identical with the specific embodiment one.
The specific embodiment three: in conjunction with Fig. 2, present embodiment is described, a kind of Gas Turbine guide vane that adopts 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.
The specific embodiment four: in conjunction with Fig. 2, present embodiment is described, a kind of nozzle ring of present embodiment, it has above-mentioned Gas Turbine guide vane.
The specific embodiment five: in conjunction with Fig. 2, present embodiment is described, 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 skills are according to main design of the present invention and spirit; can carry out very easily corresponding flexible or modification, therefore protection scope of the present invention should be as the criterion with the desired protection domain of claims.
Claims (5)
1. a precision casting technology for Gas Turbine guide vane, is characterized in that, concrete steps are:
Step 1: molding: on wax injector, select middle temperature wax material, suppress by the die mould of required Gas Turbine guide vane, take out after the wax-pattern pressurize 20-30s making, then revise wax-pattern and make its zero defect, then wax-pattern is carried out to the assembling of dead head;
Step 2: shell processed: the wax-pattern outer surface obtaining in step 1, select total silicon sol adhesive to make shell, the ground floor of shell and the powder of the second layer are fining agent, the 3rd layer adopts mullite sand powder to be made into high-strength fireproof coating, then to shell, carry out air-dry, until shell reaches after the intensity of regulation, adopt steam to dewax, dewaxing temperature is that 140-160 ℃, pressure are that 0.4-0.6MPa, dwell time are 10-15 minute;
Step 3: vacuum smelting smelting and pouring: at the shell outer wrapping insulation quilt described in step 2, then carry out roasting, sintering temperature is 850-950 ℃, adopt afterwards vacuum induction casting stove to carry out respectively vacuum metling and vacuum pouring, obtain required foundry goods, after casting complete, the foundry goods obtaining is kept under vacuum state after 10-15 minute taking out, be put in incubator, carry out cooling;
Step 4: vacuum heat: the foundry goods obtaining in step 3 is carried out to austenitizing processing, and austenitizing temperature is 1160-1180 ℃, is then incubated 3-5 hour, and blowing argon gas carries out cooling afterwards; Then carry out Ageing Treatment for the first time, the temperature of Ageing Treatment is 1000-1100 ℃ for the first time, and temperature retention time 3-5 hour carries out blowing argon gas cooling afterwards; Then carry out Ageing Treatment for the second time, the temperature of Ageing Treatment is 800-950 ℃ for the second time, and temperature retention time is 15-17 hour, then carries out blowing argon gas and obtain described Gas Turbine guide vane after cooling.
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 ℃, and the speed of vacuum pouring is one group of 5-8 second.
3. adopt the Gas Turbine guide vane that 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), and 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410249952.7A CN104001857B (en) | 2014-06-06 | 2014-06-06 | A kind of Gas Turbine guide vane and precision casting technology thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410249952.7A CN104001857B (en) | 2014-06-06 | 2014-06-06 | A kind of Gas Turbine guide vane and precision casting technology thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104001857A true CN104001857A (en) | 2014-08-27 |
| CN104001857B CN104001857B (en) | 2016-02-10 |
Family
ID=51362925
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410249952.7A Active CN104001857B (en) | 2014-06-06 | 2014-06-06 | A kind of Gas Turbine guide vane and precision casting technology thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104001857B (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN105290330A (en) * | 2015-12-04 | 2016-02-03 | 霍山县忠福铸造有限责任公司 | Manufacturing method for cable protective casting of offshore petroleum drilling platform |
| WO2017114070A1 (en) * | 2015-12-29 | 2017-07-06 | 张建勋 | Environmentally friendly preparation method for automobile booster turbine |
| WO2017114079A1 (en) * | 2015-12-30 | 2017-07-06 | 张建勋 | Method for preparing automobile supercharging turbine |
| WO2017114078A1 (en) * | 2015-12-30 | 2017-07-06 | 张建勋 | Method for preparing engine component |
| WO2017114066A1 (en) * | 2015-12-29 | 2017-07-06 | 张建勋 | Environmentally friendly method for preparing automobile engine shell |
| WO2017114068A1 (en) * | 2015-12-29 | 2017-07-06 | 张建勋 | Environmentally friendly method for preparing automobile engine blade |
| 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 |
| CN107457358A (en) * | 2017-08-24 | 2017-12-12 | 西安中工动力能源有限公司 | Miniature gas turbine turbine rotor and its casting method |
| 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 |
| CN108941455A (en) * | 2018-07-27 | 2018-12-07 | 沈阳中科三耐新材料股份有限公司 | A kind of casting method of gas turbine duplex turborotor |
| CN109093072A (en) * | 2018-07-27 | 2018-12-28 | 沈阳中科三耐新材料股份有限公司 | A kind of casting technique of gas turbine turbo blade |
| CN109622888A (en) * | 2018-12-20 | 2019-04-16 | 航天海鹰(哈尔滨)钛业有限公司 | A kind of cast shaping process of the multi-joint guide vane casting of complexity high temperature alloy |
| 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 |
| CN113857430A (en) * | 2021-08-23 | 2021-12-31 | 中国科学院金属研究所 | Blade deformation control method and application |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5299909A (en) * | 1993-03-25 | 1994-04-05 | Praxair Technology, Inc. | Radial turbine nozzle vane |
| CN1683099A (en) * | 2005-02-02 | 2005-10-19 | 哈尔滨鑫润精铸工业有限公司 | Fine casting method for super long lower pressure partition guide blade of turbine in stainless steel investment mold |
| CN101992268A (en) * | 2010-11-20 | 2011-03-30 | 沈阳工业大学 | Preparation process of high-temperature alloy multigang hollow turbine blade |
| CN103509973A (en) * | 2013-09-22 | 2014-01-15 | 苏州华宇精密铸造有限公司 | Precisely cast blade and manufacturing method thereof |
-
2014
- 2014-06-06 CN CN201410249952.7A patent/CN104001857B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5299909A (en) * | 1993-03-25 | 1994-04-05 | Praxair Technology, Inc. | Radial turbine nozzle vane |
| CN1683099A (en) * | 2005-02-02 | 2005-10-19 | 哈尔滨鑫润精铸工业有限公司 | Fine casting method for super long lower pressure partition guide blade of turbine in stainless steel investment mold |
| CN101992268A (en) * | 2010-11-20 | 2011-03-30 | 沈阳工业大学 | Preparation process of high-temperature alloy multigang hollow turbine blade |
| CN103509973A (en) * | 2013-09-22 | 2014-01-15 | 苏州华宇精密铸造有限公司 | Precisely cast blade and manufacturing method thereof |
Non-Patent Citations (2)
| Title |
|---|
| 王延辉: "DZ-4合金发动机低压涡轮叶片定向凝固实验研究", 《万方数据库》 * |
| 高亚龙等: "燃机叶片精密铸造技术研究", 《汽轮机技术》 * |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN105290330A (en) * | 2015-12-04 | 2016-02-03 | 霍山县忠福铸造有限责任公司 | Manufacturing method for cable protective casting of offshore petroleum drilling platform |
| WO2017114070A1 (en) * | 2015-12-29 | 2017-07-06 | 张建勋 | Environmentally friendly preparation method for automobile booster turbine |
| WO2017114066A1 (en) * | 2015-12-29 | 2017-07-06 | 张建勋 | Environmentally friendly method for preparing automobile engine shell |
| WO2017114068A1 (en) * | 2015-12-29 | 2017-07-06 | 张建勋 | Environmentally friendly method for preparing automobile engine blade |
| WO2017114079A1 (en) * | 2015-12-30 | 2017-07-06 | 张建勋 | Method for preparing automobile supercharging turbine |
| WO2017114078A1 (en) * | 2015-12-30 | 2017-07-06 | 张建勋 | Method for preparing 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 |
| CN107457358A (en) * | 2017-08-24 | 2017-12-12 | 西安中工动力能源有限公司 | Miniature gas turbine turbine rotor and its casting method |
| 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 |
| CN108941455A (en) * | 2018-07-27 | 2018-12-07 | 沈阳中科三耐新材料股份有限公司 | A kind of casting method of gas turbine duplex turborotor |
| CN109093072A (en) * | 2018-07-27 | 2018-12-28 | 沈阳中科三耐新材料股份有限公司 | A kind of casting technique of gas turbine turbo blade |
| 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 |
| CN109622888A (en) * | 2018-12-20 | 2019-04-16 | 航天海鹰(哈尔滨)钛业有限公司 | A kind of cast shaping process of the multi-joint guide vane casting of complexity high temperature alloy |
| CN113857430A (en) * | 2021-08-23 | 2021-12-31 | 中国科学院金属研究所 | Blade deformation control method and application |
| CN113857430B (en) * | 2021-08-23 | 2023-10-13 | 中国科学院金属研究所 | Blade deformation control method and application |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104001857B (en) | 2016-02-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104001857B (en) | A kind of Gas Turbine guide vane and precision casting technology thereof | |
| CN100534670C (en) | Fine casting method for super long lower pressure partition guide blade of turbine in stainless steel investment mold | |
| CN107598097A (en) | A kind of wax-pattern combination of turborotor and its fine casting method | |
| CN109648065B (en) | Method for evaluating recrystallization forming tendency of single crystal superalloy | |
| CN106001513B (en) | A kind of preparation method of precision-investment casting single crystal super alloy thin-walled sample | |
| CN102019353A (en) | Precision casting molding method for complex thin-walled member | |
| CN104384452A (en) | Preparation technique for thin-walled silica-based ceramic mold core | |
| CN103302242A (en) | Precise casing method of tiles of floating wall of combustion chamber of aeroengine | |
| CN106270392A (en) | A kind of manufacture method of single crystal super alloy working-blade | |
| CN105543749A (en) | High-entropy alloy gradient stress modification technology | |
| CN109622888A (en) | A kind of cast shaping process of the multi-joint guide vane casting of complexity high temperature alloy | |
| CN104972063B (en) | Method for manufacturing wax mould for precision investment casting | |
| CN108941455B (en) | Casting method of duplex turbine guide vane for gas turbine | |
| CN101476085A (en) | Method for foundry production of ultra-supercritical main steam control valve for nuclear power unit | |
| CN109093072B (en) | Casting process of turbine blade for gas turbine | |
| CN103509973A (en) | Precisely cast blade and manufacturing method thereof | |
| CN103320709B (en) | Cold working die steel material and alloy inoculant | |
| CN104999034B (en) | Casting method of large allowance-free pressure expander precise casting piece | |
| CN106046807A (en) | High heat stability precision casting wax and preparation method thereof | |
| CN104972062A (en) | Manufacturing process of high-temperature alloy turbine | |
| CN103147019A (en) | Casting method of cold working die module | |
| CN101760698A (en) | Cement kiln roller steel casting and casting method thereof | |
| CN104550735A (en) | Precision casting method of last stage extra-long guide blade for million-kilowatt nuclear power unit | |
| CN100493778C (en) | Sand mould casting method for large-scale high-temperature alloy cast | |
| CN100577323C (en) | A kind of manufacture method of commutating support plate shaped shell of accurate casting heavy type combustion turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |