CN105603260A - High-temperature-resistant turbocharger turbine wheel - Google Patents
High-temperature-resistant turbocharger turbine wheel Download PDFInfo
- Publication number
- CN105603260A CN105603260A CN201510990541.8A CN201510990541A CN105603260A CN 105603260 A CN105603260 A CN 105603260A CN 201510990541 A CN201510990541 A CN 201510990541A CN 105603260 A CN105603260 A CN 105603260A
- Authority
- CN
- China
- Prior art keywords
- resistant
- turbocharger turbine
- elevated temperatures
- turbine
- spylevy
- 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
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/07—Alloys based on nickel or cobalt based on cobalt
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
-
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Supercharger (AREA)
Abstract
The invention relates to a high-temperature-resistant turbocharger turbine wheel. The turbocharger turbine wheel comprises a turbine body, wherein the turbine body comprises a ceramic filling part and a metal layer arranged on an outer layer of the ceramic filling part; the metal layer is made of cobalt-based high-temperature alloy; and the cobalt-based high-temperature alloy consists of the following components (in percentage by mass): 0.15-0.3% of C, 8-15% of Ni, 15-25% of Cr, 10-15% of W, 0.3-1% of Mo, 0.5-3% of Nb, 0.3-1% of Ta, 0.1-0.8% of Ti, 0.003-0.008% of B, 0.1-0.8% of Zr, 0.05-0.5% of rare earth elements, not more than 3% of Fe and the balance of Co and inevitable impurity elements. According to the turbocharger turbine wheel, the high-temperature usage performance of the turbine wheel is improved to a certain extent and the effects of absorbing sound, reducing noise and reducing turbine wheel mass can be achieved.
Description
Technical field
The present invention relates to a kind of turbocharger turbine, relate in particular to a kind of resistant to elevated temperatures whirlpoolWheel booster turbine.
Background technology
Turbocharger is actually a kind of air compressor, and it is that one is utilized engineThe particular component of the waste gas acting of discharging. Turbocharger not only can energy-saving and emission-reduction, andAnd can also effectively improve engine power, become high-new that auto manufacturing competitively developsOne of technology.
The operating ambient temperature of turbocharger is higher, the operating temperature of diesel pressure boosterGenerally 600 DEG C of left and right, the operating temperature of petrol engine supercharge device will be up to800-900 DEG C, special vehicle engine booster operating temperature will be up to 900-950 DEG C.Along with the raising that engine performance is required, the operating temperature of turbocharger also will enter oneStep improves. And turbocharger is mainly made up of turbine part and volute part. Turbine existsHigh Rotation Speed under high temperature, requires to have particularly preferred high-temperature behavior, therefore all adopt high temperature to closeGold is manufactured. Turbocharger volute shape complexity, requires material to have good castabilityCan, need to there is good elevated temperature strength, creep resistance, non-oxidizability, anti-corruption simultaneouslyErosion property and dimensional stability etc.
In addition, turbocharger work in, certain noise that also can produce.And along with the prolongation of service time, noise effect meeting is more and more serious. Therefore, turbine increasesDepressor also needs to carry out sound-deadening and noise-reducing processing.
Summary of the invention
The object of the invention is, for the above-mentioned problems in the prior art, to have proposed oneGood and the resistant to elevated temperatures turbocharger turbine that can sound-deadening and noise-reducing of kind of high-temperature behavior.
Object of the present invention can realize by following technical proposal: a kind of resistant to elevated temperatures turbineBooster turbine, comprises turbine body, and turbine body comprises ceramic filling part and is arranged onThe outer field metal level of pottery filling part, metal level is made up of cobalt base superalloy, cobalt-based high-temperatureAlloy is made up of following composition (by percentage to the quality): C:0.15-0.3%, and Ni:8-15%,Cr：15-25％，W：10-15％，Mo：0.3-1％，Nb：0.5-3％，Ta：0.3-1％，Ti:0.1-0.8%, B:0.003-0.008%, Zr:0.1-0.8%, rare earth element: 0.05-0.5%,Fe≤3%, surplus is Co and inevitable impurity element.
Turbocharger turbine body of the present invention comprises ceramic filling part and is arranged on potteryThe outer field metal level of filling part. Because pottery not only has higher hardness, and at high temperatureUnder environment, still there is good mechanical strength. Therefore, the present invention is by metal structureCeramic structures improves metal structure in addition, can increase to a certain extent whirlpoolThe applied at elevated temperature performance of wheel reduces the quality of turbine simultaneously.
In addition, metal level of the present invention is made up of cobalt base superalloy, and it is at 700-1100 barUnder part, still there is certain elevated temperature strength and good corrosion and heat resistant, oxidation resistance, anti-The combination property such as fatigue behaviour, fracture toughness is to manufacture turbocharger turbine of the present inventionPreferred material.
In cobalt base superalloy of the present invention, C not only can stable austenite tissue, alsoCan form with the alloying element such as Cr, Zr, Ta, W, Ti the hardening constituent of strong carbide. SeparatelyOutward, alloying element Ti, Nb, Cr and N have very strong affinity, and are castingCheng Zhong, unavoidably can bring N into, therefore, needs rationally to control N and Ti, NbDeng alloying element, make N and Ti and Nb form TiN and NNb particle, disperse distributesIn alloy, play the effect of dispersion-strengtherning, improve cobalt base superalloy at high temperatureThe performances such as stress breaking life. But, the particle utmost points such as the TiN that N and alloying element formDifficult decomposition, can cluster be present in alloy melt, in process of setting, promotes as coreThe separating out and grow up fast of the carbide such as TiC, massive carbide blocks interdendritic passage,Reduce mobility and the feeding of aluminium alloy, thereby can cause micro-the dredging in alloy structureThe reduction of the aobvious increase of pine torches and alloy mechanical property. Therefore, the content of alloying element andThe content of the N element of bringing in casting process all needs strict control.
In cobalt base superalloy of the present invention, the content of Ni, Cr, tri-kinds of elements of WHigh. Wherein, Ni be ensure form austenitic important element, and can also with Cr elementCoordinate to keep the high antioxidant anticorrosive performance of alloy. And Cr element is to improve alloy antioxygenChange the essential element of corrosive nature, be also to form strong carbide to play with C element simultaneouslyThe essential element of strengthening effect. And W is the main solid solution element of alloy, its mass fractionMust control in above-mentioned scope, could effectively play solution strengthening effect.
In addition, the present invention has also controlled the content of Fe element, because Fe content increases,Not only can make the hardness of cobalt base superalloy decline, also can reduce cobalt base superalloyStructure stability under corrosion and heat resistant, oxidation resistance, anti-fatigue performance and high temperature.
In the resistant to elevated temperatures turbocharger turbine of above-mentioned one, ceramic filling part is nitrogenizeSilicon pottery. The performance such as intensity and hardness of silicon nitride ceramics is better than general ceramic material, andAnd be to have extraordinary temperature tolerance and corrosion resistance, intensity can be maintained to 1200 alwaysDEG C high temperature and do not decline, after being heated, can not be melt into and melt body.
In the resistant to elevated temperatures turbocharger turbine of above-mentioned one, silicon nitride ceramics is porousSilicon nitride ceramics.
In the resistant to elevated temperatures turbocharger turbine of above-mentioned one, porous silicon nitride ceramicAperture is 50-100 μ m, and the porosity is 60-70%.
The present invention has also controlled aperture and the porosity of porous silicon-nitride ceramic material, makes thisThe silicon nitride ceramics of invention can also become a kind of well absorbing sound and lowering noise material, reduces turbineThe noise pollution that booster produces in work.
In the resistant to elevated temperatures turbocharger turbine of above-mentioned one, cobalt base superalloy by withLower composition (by percentage to the quality) composition: C:0.2-0.25%, Ni:10-12%,Cr：18-22％，W：12-13％，Mo：0.5-0.8％，Nb：0.8-1.5％，Ta：0.5-0.8%, Ti:0.3-0.5%, B:0.005-0.006%, Zr:0.3-0.5%, rare earthElement: 0.1-0.3%, Fe≤3%, surplus is Co and inevitable impurity element.
In the resistant to elevated temperatures turbocharger turbine of above-mentioned one, La in rare earth elementContent >=65%. The rare earth element adding in cobalt base superalloy of the present invention be mainly La orThe mixture of La and other rare earth element, thus play the effect of microalloying, with hydrogen etc.Gas and many nonmetallic inclusions generate the high compound of fusing point, reach dehydrogenation, refining, cleanTurn use into. , can also on the crystal grain boundary of growing up, optionally adsorb meanwhile, hinder brilliantThe growth of grain, makes grain refinement, has rotten effect. Thereby raising cobalt base superalloyCombination property.
In the resistant to elevated temperatures turbocharger turbine of above-mentioned one, also shape of turbine body surfaceBecome matcoveredn. Turbine is broken by high-temperature oxydation and heat erosion easily in long-term work processBad, therefore in order to improve the service life of turbine, except preparing material of improvement turbine,Can also use protective protective layer to protect on turbine body surface.
In the resistant to elevated temperatures turbocharger turbine of above-mentioned one, protective layer is NiCrAlYLayer.
In the resistant to elevated temperatures turbocharger turbine of above-mentioned one, in NiCrAlY layer (withMass percent meter) Cr accounts for 25-30%, and Al accounts for 10-15%, and Y accounts for 0.1-1%, and surplus isNi。
NiCrAlY protective layer of the present invention has good resistance to high temperature oxidation, corrosion and heat resistantThe performances such as energy, plasticity, and composition can be controlled on request.
Compared with prior art, the present invention has following advantage:
1. turbocharger turbine body of the present invention comprises ceramic filling part and is arranged on potteryThe outer field metal level of porcelain filling part, can increase the applied at elevated temperature of turbine to a certain extentCan, reduce the quality of turbine simultaneously.
2. the metal level of turbocharger turbine body of the present invention is by cobalt base superalloy systemBecome, there is certain elevated temperature strength and good corrosion and heat resistant, oxidation resistance, anti-tiredThe combination properties such as labor performance, fracture toughness.
3. the pottery filling part of turbocharger turbine body of the present invention is porous silicon nitride potteryPorcelain, the better performances such as its intensity and hardness, and can also play the effect of absorbing sound and lowering noise.
The present invention turbocharger turbine body surface be also formed with resistance to high temperature oxidation,The well behaved NiCrAlY protective layer such as hot corrosion resistance, plasticity.
Detailed description of the invention
Be below specific embodiments of the invention, technical scheme of the present invention is done furtherDescribe, but the present invention is not limited to these embodiment.
Embodiment 1:
Turbocharger turbine body in the present embodiment comprises ceramic filling part and settingAt the outer field metal level of ceramic filling part, layer on surface of metal is also formed with NiCrAlY protectionLayer, wherein in NiCrAlY layer, (by percentage to the quality) Cr accounts for 28%, Al and accounts for 13%, YAccount for 0.5%, surplus is Ni.
Wherein, ceramic filling part is that aperture is 50-100 μ m, and what the porosity was 60-70% is manyHole silicon nitride ceramics.
Metal level is made up of cobalt base superalloy, cobalt base superalloy by following composition (with matterAmount percentage meter) composition: C:0.15%, Ni:8%, Cr:15%, W:10%,Mo：0.3％，Nb：0.5％，Ta：0.3％，Ti：0.1％，B：0.003％，Zr：0.1%, rare earth element: 0.05%, Fe:2%, surplus is Co and inevitably assortedPrime element. Wherein, the La that rare earth element is 65% and 35%Y composition.
Embodiment 2:
Turbocharger turbine body in the present embodiment comprises ceramic filling part and settingAt the outer field metal level of ceramic filling part, layer on surface of metal is also formed with NiCrAlY protectionLayer, wherein in NiCrAlY layer, (by percentage to the quality) Cr accounts for 28%, Al and accounts for 13%, YAccount for 0.5%, surplus is Ni.
Wherein, ceramic filling part is that aperture is 50-100 μ m, and what the porosity was 60-70% is manyHole silicon nitride ceramics.
Metal level is made up of cobalt base superalloy, cobalt base superalloy by following composition (with matterAmount percentage meter) composition: C:0.2%, Ni:10%, Cr:18%, W:12%,Mo：0.5％，Nb：0.8％，Ta：0.5％，Ti：0.3％，B：0.005％，Zr：0.3%, rare earth element: 0.1%, Fe:2%, surplus is Co and inevitable impurityElement. Wherein, the La that rare earth element is 65% and 35%Y composition.
Embodiment 3:
Turbocharger turbine body in the present embodiment comprises ceramic filling part and settingAt the outer field metal level of ceramic filling part, layer on surface of metal is also formed with NiCrAlY protectionLayer, wherein in NiCrAlY layer, (by percentage to the quality) Cr accounts for 28%, Al and accounts for 13%, YAccount for 0.5%, surplus is Ni.
Wherein, ceramic filling part is that aperture is 50-100 μ m, and what the porosity was 60-70% is manyHole silicon nitride ceramics.
Metal level is made up of cobalt base superalloy, cobalt base superalloy by following composition (with matterAmount percentage meter) composition: C:0.23%, Ni:11%, Cr:20%, W:12.5%,Mo：0.6％，Nb：1％，Ta：0.6％，Ti：0.4％，B：0.0055％，Zr：0.4%, rare earth element: 0.2%, Fe:1%, surplus is Co and inevitable impurityElement. Wherein, the La that rare earth element is 65% and 35%Y composition.
Embodiment 4:
Turbocharger turbine body in the present embodiment comprises ceramic filling part and settingAt the outer field metal level of ceramic filling part, layer on surface of metal is also formed with NiCrAlY protectionLayer, wherein in NiCrAlY layer, (by percentage to the quality) Cr accounts for 28%, Al and accounts for 13%, YAccount for 0.5%, surplus is Ni.
Wherein, ceramic filling part is that aperture is 50-100 μ m, and what the porosity was 60-70% is manyHole silicon nitride ceramics.
Metal level is made up of cobalt base superalloy, cobalt base superalloy by following composition (with matterAmount percentage meter) composition: C:0.25%, Ni:12%, Cr:22%, W:13%,Mo：0.8％，Nb：1.5％，Ta：0.8％，Ti：0.5％，B：0.006％，Zr：0.5%, rare earth element: 0.3%, Fe:1%, surplus is Co and inevitable impurityElement. Wherein, the La that rare earth element is 65% and 35%Y composition.
Embodiment 5:
Turbocharger turbine body in the present embodiment comprises ceramic filling part and settingAt the outer field metal level of ceramic filling part, layer on surface of metal is also formed with NiCrAlY protectionLayer, wherein in NiCrAlY layer, (by percentage to the quality) Cr accounts for 28%, Al and accounts for 13%, YAccount for 0.5%, surplus is Ni.
Wherein, ceramic filling part is that aperture is 50-100 μ m, and what the porosity was 60-70% is manyHole silicon nitride ceramics.
Metal level is made up of cobalt base superalloy, cobalt base superalloy by following composition (with matterAmount percentage meter) composition: C:0.3%, Ni:15%, Cr:25%, W:15%,Mo：1％，Nb：3％，Ta：1％，Ti：0.8％，B：0.008％，Zr：0.8％，Rare earth element: 0.5%, Fe:3%, surplus is Co and inevitable impurity element.Wherein, the La that rare earth element is 65% and 35%Y composition.
Comparative example 1 is only with the difference of embodiment 3, and comparative example 1 does not contain ceramic filling part.
Comparative example 2 is only with the difference of embodiment 3, and the ceramic filling part of comparative example 2 isCommon silicon nitride ceramics.
Comparative example 3 is only with the difference of embodiment 3, the metal level of comparative example 3 byDZ40M cobalt base superalloy is made.
Comparative example 4 is only with the difference of embodiment 3, the cobalt base superalloy of comparative example 4In do not add rare earth element.
Comparative example 5 is only with the difference of embodiment 3, the cobalt base superalloy of comparative example 5The rare earth element of middle interpolation is not containing La.
Comparative example 6 is only with the difference of embodiment 3, the turbine body surface of comparative example 6There is no protective layer.
The turbocharger turbine of the embodiment of the present invention and comparative example is carried out to performance test, surveyTest result is as shown in table 1.
Table 1
As known from Table 1, turbocharger turbine of the present invention has excellent intensity and Nai GaoWarm nature energy, and also there is good absorbing sound and lowering noise effect.
In above-described embodiment and alternative thereof, in rare earth element, the addition of La is all rightBe 70%, 75%, 80%, 85%, 90%, 95%, 100%.
In above-described embodiment and alternative thereof, rare earth element can also be for being La and otherAny mixing of rare earth element, wherein content >=65% of La.
In above-described embodiment and alternative thereof, in NiCrAlY protective layer (with quality hundredProportion by subtraction meter) Cr can also account for 25%, 26%, 27%, 29%, 30%.
In above-described embodiment and alternative thereof, in NiCrAlY protective layer (with quality hundredProportion by subtraction meter) Al can also account for 10%, 11%, 12%, 14%, 15%.
In above-described embodiment and alternative thereof, in NiCrAlY protective layer (with quality hundredProportion by subtraction meter) Y can also account for 0.1%, 0.2%, 0.3%, 0.4%, 0.6%, 0.7%, 0.8%,0.9％、1％。
Specific embodiment described herein is only to the explanation for example of the present invention's spirit.Those skilled in the art can do respectively described specific embodimentPlant amendment or supplement or adopt similar mode to substitute, but can't depart from spirit of the present inventionOr surmount the defined scope of appended claims.
Although the present invention has been made a detailed description and has quoted as proof some specific embodiments,But to those skilled in the art, only otherwise leave the spirit and scope of the present inventionIt is obvious can making various changes or revise.
Claims (9)
1. a resistant to elevated temperatures turbocharger turbine, comprises turbine body, it is characterized in that,Described turbine body comprises ceramic filling part and is arranged on the outer field metal of ceramic filling partLayer, described metal level is made up of cobalt base superalloy, and described cobalt base superalloy is by becoming belowDivide (by percentage to the quality) composition: C:0.15-0.3%, Ni:8-15%, Cr:15-25%,W：10-15％，Mo：0.3-1％，Nb：0.5-3％，Ta：0.3-1％，Ti：0.1-0.8％，B:0.003-0.008%, Zr:0.1-0.8%, rare earth element: 0.05-0.5%, Fe≤3%,Surplus is Co and inevitable impurity element.
2. the resistant to elevated temperatures turbocharger turbine of one according to claim 1, its spyLevy and be, described ceramic filling part is silicon nitride ceramics.
3. the resistant to elevated temperatures turbocharger turbine of one according to claim 2, its spyLevy and be, described silicon nitride ceramics is porous silicon nitride ceramic.
4. the resistant to elevated temperatures turbocharger turbine of one according to claim 3, its spyLevy and be, the aperture of described porous silicon nitride ceramic is 50-100 μ m, and the porosity is60-70％。
5. the resistant to elevated temperatures turbocharger turbine of one according to claim 1, its spyLevy and be, described cobalt base superalloy is made up of following composition (by percentage to the quality):C：0.2-0.25％，Ni：10-12％，Cr：18-22％，W：12-13％，Mo：0.5-0.8％，Nb：0.8-1.5％，Ta：0.5-0.8％，Ti：0.3-0.5％，B：0.005-0.006％，Zr:0.3-0.5%, rare earth element: 0.1-0.3%, Fe≤3%, surplus is Co and can notThe impurity element of avoiding.
6. a kind of resistant to elevated temperatures turbocharger turbine according to claim 1 or 5, itsBe characterised in that content >=65% of La in described rare earth element.
7. the resistant to elevated temperatures turbocharger turbine of one according to claim 1, its spyLevy and be, described turbine body surface is also formed with protective layer.
8. the resistant to elevated temperatures turbocharger turbine of one according to claim 7, its spyLevy and be, described protective layer is NiCrAlY layer.
9. the resistant to elevated temperatures turbocharger turbine of one according to claim 8, its spyLevy and be, in described NiCrAlY layer, (by percentage to the quality) Cr accounts for 25-30%, AlAccount for 10-15%, Y accounts for 0.1-1%, and surplus is Ni.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510990541.8A CN105603260A (en) | 2015-12-24 | 2015-12-24 | High-temperature-resistant turbocharger turbine wheel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510990541.8A CN105603260A (en) | 2015-12-24 | 2015-12-24 | High-temperature-resistant turbocharger turbine wheel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105603260A true CN105603260A (en) | 2016-05-25 |
Family
ID=55983595
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510990541.8A Pending CN105603260A (en) | 2015-12-24 | 2015-12-24 | High-temperature-resistant turbocharger turbine wheel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105603260A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106180738A (en) * | 2016-08-16 | 2016-12-07 | 兰州工业学院 | A kind of valve high temperature resistant nickel cobalt tungsten rare earth alloy powder material and preparation method thereof |
| CN109338163A (en) * | 2018-12-24 | 2019-02-15 | 南通金源智能技术有限公司 | Cobalt base superalloy powder |
| CN110923512A (en) * | 2019-12-04 | 2020-03-27 | 上海旷彩环保科技发展有限公司 | High-temperature corrosion resistant alloy core, production process and electromagnetic heating rotary kiln |
| CN111918975A (en) * | 2019-03-07 | 2020-11-10 | 三菱动力株式会社 | Heat exchanger |
| US11155904B2 (en) | 2019-07-11 | 2021-10-26 | L.E. Jones Company | Cobalt-rich wear resistant alloy and method of making and use thereof |
| EP3936632A4 (en) * | 2019-03-07 | 2022-11-02 | Mitsubishi Heavy Industries, Ltd. | Cobalt-based alloy product and cobalt-based alloy article |
| CN115478273A (en) * | 2022-09-30 | 2022-12-16 | 沈阳大陆激光工程技术有限公司 | A laser-manufactured high wear-resistant cobalt-based alloy material applied to the finish rolling side guide plate |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101205573A (en) * | 2007-12-17 | 2008-06-25 | 北京航空航天大学 | Method for preparing Co-based single crystal superalloy by combination of seed crystal method and spiral crystal selection method |
| CN101484597A (en) * | 2006-07-07 | 2009-07-15 | 伊顿公司 | Wear resistant high temperature alloy |
| CN101654754A (en) * | 2009-08-27 | 2010-02-24 | 北京航空航天大学 | Co-M-C alloy and method for manufacturing same with liquid metal cooling method |
| CN102115866A (en) * | 2009-12-30 | 2011-07-06 | 中国科学院金属研究所 | NiCrAIY coating for nickel base high temperature alloy and preparation method thereof |
| CN105177392A (en) * | 2014-06-02 | 2015-12-23 | 通用电气公司 | Gas turbine component and process for producing gas turbine component |
-
2015
- 2015-12-24 CN CN201510990541.8A patent/CN105603260A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101484597A (en) * | 2006-07-07 | 2009-07-15 | 伊顿公司 | Wear resistant high temperature alloy |
| CN101205573A (en) * | 2007-12-17 | 2008-06-25 | 北京航空航天大学 | Method for preparing Co-based single crystal superalloy by combination of seed crystal method and spiral crystal selection method |
| CN101654754A (en) * | 2009-08-27 | 2010-02-24 | 北京航空航天大学 | Co-M-C alloy and method for manufacturing same with liquid metal cooling method |
| CN102115866A (en) * | 2009-12-30 | 2011-07-06 | 中国科学院金属研究所 | NiCrAIY coating for nickel base high temperature alloy and preparation method thereof |
| CN105177392A (en) * | 2014-06-02 | 2015-12-23 | 通用电气公司 | Gas turbine component and process for producing gas turbine component |
Non-Patent Citations (1)
| Title |
|---|
| 刘国玺: ""氮化硅基多孔陶瓷材料的制备"", 《中国优秀硕士学位论文全文数据库工程科技I辑》 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106180738A (en) * | 2016-08-16 | 2016-12-07 | 兰州工业学院 | A kind of valve high temperature resistant nickel cobalt tungsten rare earth alloy powder material and preparation method thereof |
| CN109338163A (en) * | 2018-12-24 | 2019-02-15 | 南通金源智能技术有限公司 | Cobalt base superalloy powder |
| CN111918975A (en) * | 2019-03-07 | 2020-11-10 | 三菱动力株式会社 | Heat exchanger |
| CN111918975B (en) * | 2019-03-07 | 2022-05-17 | 三菱重工业株式会社 | heat exchanger |
| EP3936632A4 (en) * | 2019-03-07 | 2022-11-02 | Mitsubishi Heavy Industries, Ltd. | Cobalt-based alloy product and cobalt-based alloy article |
| US11155904B2 (en) | 2019-07-11 | 2021-10-26 | L.E. Jones Company | Cobalt-rich wear resistant alloy and method of making and use thereof |
| CN110923512A (en) * | 2019-12-04 | 2020-03-27 | 上海旷彩环保科技发展有限公司 | High-temperature corrosion resistant alloy core, production process and electromagnetic heating rotary kiln |
| CN110923512B (en) * | 2019-12-04 | 2020-12-04 | 上海江竑环保科技有限公司 | High-temperature corrosion resistant alloy core, production process and electromagnetic heating rotary kiln |
| CN115478273A (en) * | 2022-09-30 | 2022-12-16 | 沈阳大陆激光工程技术有限公司 | A laser-manufactured high wear-resistant cobalt-based alloy material applied to the finish rolling side guide plate |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105603260A (en) | High-temperature-resistant turbocharger turbine wheel | |
| RU2760223C1 (en) | Oxidation-resistant heat-resistant alloy and method for its production | |
| CN104611622B (en) | Austenite ductile cast iron alloy composite and product prepared therefrom | |
| US4789412A (en) | Cobalt-base alloy having high strength and high toughness, production process of the same, and gas turbine nozzle | |
| CN104593692B (en) | A kind of heat-resistant cast austenitic stainless steel with excellent high temperature combination property | |
| CN108842082B (en) | A kind of Fe-Ni base casting superalloy and preparation method thereof | |
| JP6768929B2 (en) | Ferritic stainless steel with excellent high-temperature wear resistance, manufacturing method of ferritic stainless steel sheet, exhaust parts, high-temperature sliding parts, and turbocharger parts | |
| JP2009540115A (en) | Cast iron alloy with excellent high-temperature oxidation resistance | |
| JP2000291430A (en) | Exhaust system part, internal combustion engine using the same and manufacture of the exhaust system part | |
| CN107075633A (en) | The austenite heat-resistant cast steel of excellent in thermal fatigue characteristics and the exhaust system component comprising it | |
| CN104694783A (en) | Nickel-based air valve alloy and preparation method thereof | |
| KR101845761B1 (en) | Ferritic spheroidal cast iron for exhaust system | |
| JP6160625B2 (en) | Ferritic heat-resistant cast steel with excellent machinability and exhaust system parts composed thereof | |
| WO2011125901A1 (en) | Ferrite heat-resistant cast steel having excellent normal-temperature toughness and exhaust system component formed from the same | |
| JP6098637B2 (en) | Austenitic heat-resistant cast steel with excellent machinability and exhaust system parts composed thereof | |
| CN113862562A (en) | Antioxidant high-creep cast austenitic heat-resistant stainless steel and preparation method thereof | |
| JP4504736B2 (en) | Austenitic cast steel product and manufacturing method thereof | |
| CN117363955A (en) | Multi-type precipitated phase cooperative strengthening heat-resistant alloy and preparation method thereof | |
| CN107267778B (en) | Magnesium smelting reduction tank and preparation method thereof | |
| CN114752817B (en) | A kind of superalloy mold material and its preparation method and application | |
| CN110938781B (en) | Low-cost high-aluminum heat-resistant steel and preparation method thereof | |
| JPH07197209A (en) | Ferritic heat resistant cast steel excellent in castability and exhaust system parts made thereof | |
| JP2012122085A (en) | Ferritic spheroidal graphite cast iron and exhaust system part of automobile using the same | |
| JPH07118790A (en) | Spheroidal graphite cast iron with excellent high temperature strength | |
| CN106755723B (en) | A kind of corrosion-and high-temp-resistant alloy steel material and preparation method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160525 |