CN107035412A - A kind of ceramic-metal composite turbine shaft of low inertia, quick response - Google Patents
A kind of ceramic-metal composite turbine shaft of low inertia, quick response Download PDFInfo
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- CN107035412A CN107035412A CN201710192376.0A CN201710192376A CN107035412A CN 107035412 A CN107035412 A CN 107035412A CN 201710192376 A CN201710192376 A CN 201710192376A CN 107035412 A CN107035412 A CN 107035412A
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- ceramic
- powder
- quick response
- metal composite
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Classifications
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- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/02—Sand moulds or like moulds for shaped castings
- B22C9/04—Use of lost patterns
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/22—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip
- B22F3/225—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip by injection molding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
- B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
- B22F7/08—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Materials Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
- Powder Metallurgy (AREA)
- Ceramic Products (AREA)
Abstract
The present invention discloses a kind of low inertia, the ceramic-metal composite turbine shaft of quick response, including turbine and rotating shaft.Turbine is divided into three-decker, respectively inside subject, transition zone and blade layer from the inside to the outside.Wherein inside subject is using traditional Nickel-Based Steel, for the uniform revolving body manufactured by casting and molding method.Transition zone uses superalloy powder, is sintered in inside subject.Blade layer uses silicon nitride and zirconium oxide hybrid ceramic material；Blade layer has the turbo blade of wheel hub top layer and wheel shaft outer wall circumferential array.The rotating shaft uses high-temperature steel, and one end is coaxially connected using hollow friction welding mode with composite wood material wheel.The present invention is composited using the ceramic multiple material of Nickel-Based Steel superalloy powder, mitigate turbine type mass, reach turbine and bear 1050 DEG C of high-temperature work environments, rotating shaft with same material high-temperature steel uses conventional friction welding procedure, connection is reliable, manufacturing cost is low, and realizing improves the purpose of engine response.
Description
Technical field
The present invention relates to turbocharging technology field, and in particular to a kind of low inertia of turbocharger, quick response
Ceramic-metal composite turbine shaft.
Background technology
Turbocharger is arranged on waste pipe, and turbine case is directly connected with blast pipe, is in high temperature, height
Under the working condition of pressure, especially on aviation piston engine and SI Engine engine, up to 950 DEG C of waste gas row temperature~
1050 DEG C, more high than 850 DEG C of Diesel engine highest row temperature, traditional nickel-base alloy turbine can not meet its performance
It is required that.And nickel-base alloy density is big, turbine type mass weight causes the response of turbocharger sluggish substantially.Therefore, around resistance to
High temperature and low quality two large problems, work out the booster turbine of a variety of solution materials, mainly there is two kinds：One is titanium-aluminium alloy whirlpool
Wheel；Two be ceramics turbo.
Titanium-aluminium alloy has superior mechanical performance, and density is low, only the 1/2 of nickel-base alloy, when temperature is more than 600 DEG C
The inoxidizability and corrosion resistance still having had.Turbocharger replaces nickel-base alloy turbine with titanium aluminium turbine, can effectively mitigate
Turbine type mass, reduces the inertia of turbine rotor, slackens the response lag of turbine wheel shaft, improves engine power response.But it is same
Nickel-base alloy is the same, and titanium aluminium turbine is only applicable to less than 850 DEG C of engine exhaust temperature, and the application on gasoline engine is limited.
Ceramics due to having the advantages that high temperature resistant, it is corrosion-resistant, wear-resistant, can fully adapt to turbine high-temperature work environment, can
Conventional turbine material nickel-base alloy is substituted, as the ideal material for making booster turbine rotor.Particularly silicon nitride ceramics phase
There is the small advantage of density for nickel-base alloy, ceramics turbo density is only 0.4 times of nickel-base alloy, can effectively mitigate turbine
Quality, reduces the inertia of turbine rotor, slackens the response lag of turbine wheel shaft, improves engine power response.Patent
CN201480023248 also provides a kind of " ceramics turbo part bonded by using the partial transient liquid phase of metal binding agent
Increasing material manufacturing " process.But the application of ceramics turbo is largely determined by two aspects：One is due to that its fragility is big, ductility is low,
Under exceedingly odious use condition, face thermal shock damage problem, and the Thermal Shock Damage formed in long term high temperature and
The structure evolution damage being responsible under load and performance sharp-decay problem, silicon nitride turbine rotor reliability is by severe challenge.
On the other hand it is due to that its fusing point is high, the connection of silicon nitride ceramics turbine and high-temperature steel 42CrMo rotating shafts, which turns into, restricts its application
A great problem.
The content of the invention
The technical problems to be solved by the invention are to overcome the shortcomings of that above-mentioned prior art is present there is provided low inertia, quickly
The ceramic-metal composite turbine shaft of response, turbine is multiple using Nickel-Based Steel-superalloy powder-ceramics multiple material
Conjunction is formed, and is mitigated turbine type mass, is reached turbine and bear 1050 DEG C of high-temperature work environments, the rotating shaft with same material high-temperature steel
Using conventional friction welding procedure, connection is reliable, and manufacturing cost is low, and realizing improves the purpose of engine response.
A kind of ceramic-metal composite turbine shaft of low inertia, quick response, it is characterised in that：Including turbine and turn
Axle two parts are welded；
The turbine is divided into three-decker, respectively inside subject, transition zone and blade layer from the inside to the outside；Wherein, it is internal
Main body is using traditional Nickel-Based Steel, for the uniform revolving body manufactured by casting and molding method；Nickel-Based Steel is from Ni-based
Steel alloy K418；Transition zone uses superalloy powder, is sintered in inside subject；Blade layer is mixed using silicon nitride and zirconium oxide
Close ceramic material；Blade layer has the turbo blade of wheel hub top layer and wheel shaft outer wall circumferential array；The rotating shaft uses resistance to height
Wen Gang, material is 42CrMo, and one end is coaxially connected using hollow friction welding mode with composite wood material wheel.
The advantage of the invention is that：
(1) low inertia of the present invention, the ceramic-metal composite turbine shaft of quick response, using Nickel-Based Steel-height
Temperature alloy powder-ceramic composite is made, low with lightweight, inertia, improves the advantage of efficiency of vent oxidation catalyst.
(2) low inertia of the present invention, the ceramic-metal composite turbine shaft of quick response, using Nickel-Based Steel-height
Temperature alloy powder-ceramic composite turbine, with high temperature resistant, corrosion resistant advantage；
(3) low inertia of the present invention, the ceramic-metal composite turbine shaft of quick response, using Nickel-Based Steel-height
Temperature alloy powder-ceramic composite turbine, turbine intermediate body member Nickel-Based Steel K418 and the hollow friction welding (FW)s of rotating shaft 42CrMo
Connect technical maturity reliable, solve the problem of pure ceramics turbo is connected difficulty with rotating shaft.
Brief description of the drawings
Fig. 1 is turbine shaft structural representation of the present invention.
Fig. 2 is turbine portion structure sectional view of the present invention.
In figure：
1- turbine 2- rotating shaft 101- inside subject 102- transition zones
103- blades layer 102a- annular groove 102b- ring-shaped step 103a- wheel hubs top layer
103b- turbo blades
Embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
A kind of described low inertia, the ceramic-metal composite turbine shaft of quick response, including composite turbine 1
It is welded with the two parts of high-temperature steel rotating shaft 2, as shown in Figure 1.
Described composite turbine 1 is divided into three-decker from the inside to the outside, respectively inside subject 101, transition zone 102 with
Blade layer 103, as shown in Figure 2.Wherein, inside subject 101 is using traditional Nickel-Based Steel, to be manufactured by casting and molding method
Uniform revolving body.Specifically：Nickel-Based Steel selects Nickel-Based Steel K418, density 8.0kg/cm^3, linear expansion coefficient
12.6e-6/ DEG C, 10.15W/m. DEG C of thermal conductivity, 800 DEG C of heat resistance.
Transition zone 102 uses superalloy powder, is sintered in inside subject.Before sintering, transition zone 102 is main by inside
The ring-shaped step 101b structures designed on the annular groove 101a and forward end circumference designed in the circumference of body 101 are realized fixed
Position, and thus the end of inside subject 101, transition zone is prevented by annular groove 101a with the part of transition zone 102 is not covered
102 deformations, ensure that transition zone 101a thickness is uniform by ring-shaped step 101b structures, prevent transition zone 102 from ftractureing.Specifically：
The material of transition zone 102 is DOS superalloy powders, is that a kind of of formation has based on the basis of martensite steel and ferritic steel
There is the preferable core cladding materials for bearing highneutronflux, due to the crystal structure of itself, the steel matrix at body cube center can be with shape
Into the Ke Shi gases group with disperse, overstable reinforcing state, the characteristic with high temperature creep-resisting are formed.The material of transition zone 102
Characteristic circle plays good transitional function between K418 and ceramics, is prevented effectively from the ceramics caused by difference of linear expansion
The Problem of Failure such as face checking.
Blade layer 103 uses silicon nitride and zirconium oxide hybrid ceramic material.Specifically：Silicon nitride and zirconium oxide hybrid ceramic
Density of material 3.2kg/cm^3,3.2e-6/ DEG C of linear expansion coefficient, 29.3W/m. DEG C of thermal conductivity, 1000 DEG C of heat resistance；And exceed
900 DEG C of high-temperature fuel gas pass through composite turbine surface of the present invention, and the inoxidizability and corrosion resistance of ceramic plated layer remain unchanged well,
It is delivered to the temperature of inside subject and drops to less than 700 DEG C, K418 resistance to thermal boundary is met, equally with good mechanical property.
Blade layer 103 has the wheel hub top layer 103a and turbo blade 103b of wheel shaft outer wall circumferential array, wheel hub top layer 103a thickness 1
The all silicon nitrides of~3mm, turbo blade 103b and zirconium oxide hybrid ceramic material, are made of transient liquid phase adhesive technology,
Its density is only 0.4 times of nickel-base alloy, turbine gross mass can be made to mitigate about 40%, and make the rotary inertia mass radius of turbine
Greatly reduce, advantageously reduce turbine shaft rotary inertia, improve its transient response.
The described material of high-temperature steel rotating shaft 2 is adopted as 42CrMo, and one end uses hollow friction welding (FW) with composite turbine 1
Connect mode 3 coaxially connected, welding is reliable, solve simple ceramics turbo fragility greatly, the problem of difficulty is connected with rotating shaft.
The ceramic-metal composite turbine shaft of low inertia of the present invention, quick response, is molded by subordinate's step：
Step 1：Cast inside subject 101；
A, using solvent casting technique, from low-temperature wax CP200 as expendable pattern material, stand and remove water process, shaped inner
Main body wax-pattern.
B, inside subject wax-pattern poured into a mould using Ludox bonding agent system, technical process is coats, stucco and drying；Its
In, coating is mixed by a certain percentage by powder and Ludox, including investment precoat, transition coating and backing layer coating.Face
Coating and molten metal contacts, do not react with molten metal, it is ensured that shell inner surface quality, and use 70 mesh zircon sand conducts
Surface layer stucco；Transition coating uses 30~60 mesh gangue stuccos；The powder of backing layer coating uses the bastard coal of 270~320 mesh
Stone flour, refractoriness is more than 1450 DEG C, it is ensured that the high and low temperature intensity of shell, it is ensured that casting is indeformable and dimensional accuracy, and stucco is
16~24 mesh gangues；Finally complete slurry seal.
The powder and Ludox mixed proportion of above-mentioned investment precoat are 3.7:1.The powder and Ludox of transition coating are mixed
Composition and division in a proportion example is 2.0:1.The powder and Ludox mixed proportion of backing layer coating are 1.4:1.The Ludox component content is mainly
SiO2：30~31% (weight/mass percentage compositions), Na2O≤0.3% (weight/mass percentage composition)；Density (25 DEG C)：1.195~
1.215g/cm3；Viscosity (20 DEG C)≤7.0Pa.S × 10-1；PH value 8.5~10.0；10~20nm of average grain diameter；Outward appearance：It is milky white
Color is translucent；Stationary phase：1 year.
The powder of above-mentioned investment precoat and transition coating is to contain following quality hundred in 325 mesh zirconium English powder, zirconium English powder
Divide the component of content：ZrO2Content >=65%, Fe2O3Content≤0.1%, TiO2Content≤0.5%, P2O5Content≤0.1%,
Al2O3Content≤0.3%, SiO2Content<33%；Density is 4.6~4.78g/cm3；Refractoriness>1500℃；The Mohs of hardness 7.5
Hardness；The coefficient of expansion：4.6×10-3(l/℃)。
C, in step b pour into a mould after inside subject wax-pattern fusible pattern dewax, obtain inside subject formwork；
D, the internal theme formwork of roasting；
E, alloy melting and cast；
By intermediate frequency vacuum induction melting austenitic heat resistant cast steel, and using vacuum casting process to internal main body mould shell
Poured into a mould.
F, shake shell and the clear shell of ball blast；
Step 2：Pass through superalloy powder injection moulding transition zone 102.
By DOS superalloy powders and bonding agent Ludox by weight 1:1.5 ratio is matched, stir about
Paste is made after 40min；Then add in injector holding vessel, stand after 30min, paste injection is carried into inside subject
In 101 transition zone mould, mould need to be preheated to 300 DEG C, extrusion forming；The inside subject and transition zone of forming are put into baking
Sizing drying, 120 DEG C~200 DEG C of temperature, 24~30h of time in dry stove.
Step 3：Transient liquid phase bonding forming blade layer 103.
1) by ceramic powders and inorganic binder powder by weight 1:1.5 mix to prepare initial powder；The ceramics
Powder is silicon nitride and zirconium oxide hybrid ceramic powder；Inorganic adhesive powder is metal dust.
2) using increasing material manufacturing technique by initial powder on transition zone 102 formed blades layer 103.Described increasing material manufacturing
Technique can be molten using Direct Laser sintering, Direct Laser fusing, selective laser sintering, selective laser melting or electron beam
One kind in change.
3) sinter to be densified the blade layer of shaping using partial transient liquid phase.
Step 4：Turbine 1 and the welding of the friction welding (FW) of rotating shaft 2.
It is slightly different for the different diameter welding parameters of rotating shaft 2,19mm turbine shaft is approximately equal to for diameter, is welded
Rotating speed 850rpm, 2.2~2.4MPa of upsetting force, need pressurize 10s, need to then carry out temper, 200 DEG C of temperature, when
Between 30s.
Claims (9)
1. the ceramic-metal composite turbine shaft of a kind of low inertia, quick response, it is characterised in that：Including turbine and rotating shaft
Two parts are welded；
The turbine is divided into three-decker, respectively inside subject, transition zone and blade layer from the inside to the outside；Wherein, inside subject
Using traditional Nickel-Based Steel, for the uniform revolving body manufactured by casting and molding method；Transition zone uses superalloy powder,
It is sintered in inside subject；Blade layer uses silicon nitride and zirconium oxide hybrid ceramic material；Blade layer have wheel hub top layer and
The turbo blade of wheel shaft outer wall circumferential array；Described high-temperature steel, one end is coaxial using hollow friction welding mode with turbine
Connection.
2. a kind of low inertia, the ceramic-metal composite turbine shaft of quick response as claimed in claim 1, its feature exist
In：Nickel-Based Steel selects Nickel-Based Steel K418, density 8.0kg/cm^3,12.6e-6/ DEG C of linear expansion coefficient, thermal conductivity
10.15W/m. DEG C, 800 DEG C of heat resistance.
3. a kind of low inertia, the ceramic-metal composite turbine shaft of quick response as claimed in claim 1, its feature exist
In：Buffer layer material is DOS superalloy powders, and buffer layer material characteristic circle is between K418 and ceramics.
4. a kind of low inertia, the ceramic-metal composite turbine shaft of quick response as claimed in claim 1, its feature exist
In：Silicon nitride and zirconium oxide hybrid ceramic density of material 3.2kg/cm^3,3.2e-6/ DEG C of linear expansion coefficient, thermal conductivity 29.3W/
M. DEG C, 1000 DEG C of heat resistance.
5. a kind of low inertia, the ceramic-metal composite turbine shaft of quick response as claimed in claim 1, its feature exist
In：Rotating shaft material is 42CrMo.
6. a kind of low inertia, the ceramic-metal composite turbine shaft of quick response as claimed in claim 1, its feature exist
In：The forging type of inside subject is：
A, using solvent casting technique, from low-temperature wax CP200 as expendable pattern material, stand and remove water process, shaped inner main body
Wax-pattern；
B, inside subject wax-pattern poured into a mould using Ludox bonding agent system, technical process is coats, stucco and drying；
C, in step b pour into a mould after inside subject wax-pattern fusible pattern dewax, obtain inside subject formwork；
D, roasting inside subject formwork；
E, alloy melting, and pour into a mould main body formwork；
F, shake shell and the clear shell of ball blast.
7. a kind of low inertia, the ceramic-metal composite turbine shaft of quick response as claimed in claim 6, its feature exist
In：In step b：Coating is mixed by powder and Ludox, including investment precoat, transition coating and backing layer coating；Surface layer
Coating is used as surface layer stucco using 70 mesh zircon sands；Transition coating uses 30~60 mesh gangue stuccos；Backing layer coating is used
16~24 mesh gangue stuccos；The powder and Ludox mixed proportion of investment precoat are 3.7:1；The powder and silicon of transition coating
Colloidal sol mixed proportion is 2.0:1；The powder and Ludox mixed proportion of backing layer coating are 1.4:1；Investment precoat and transition zone are applied
The powder of material is 325 mesh zirconium English powder；The powder of backing layer coating uses the colliery powder of 270~320 mesh, and refractoriness is more than 1450
℃。
8. a kind of low inertia, the ceramic-metal composite turbine shaft of quick response as claimed in claim 1, its feature exist
In：Transition zone passes through superalloy powder injection moulding；
By DOS superalloy powders and bonding agent Ludox by weight 1:1.5 ratio is matched, after stir about 40min
Paste is made；Then add in injector holding vessel, stand after 30min, paste is injected into the transition with inside subject
In layer mould, mould need to be preheated to 300 DEG C, extrusion forming；The inside subject and transition zone of forming are put into drying oven default
Type is dried, 120 DEG C~200 DEG C of temperature, 24~30h of time.
9. a kind of low inertia, the ceramic-metal composite turbine shaft of quick response as claimed in claim 1, its feature exist
In：Blade layer uses transient liquid phase bonding forming, comprises the following steps that：
1) by ceramic powders and inorganic binder powder by weight 1:1.5 mix to prepare initial powder；
2) using increasing material manufacturing technique by initial powder on transition zone formed blades layer；
3) sinter to be densified the blade layer of shaping using partial transient liquid phase.
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| CN201710192376.0A CN107035412B (en) | 2017-03-28 | 2017-03-28 | A kind of ceramic-metal composite turbine shaft of low inertia, quick response |
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| CN201710192376.0A CN107035412B (en) | 2017-03-28 | 2017-03-28 | A kind of ceramic-metal composite turbine shaft of low inertia, quick response |
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| CN107035412B CN107035412B (en) | 2019-11-15 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114214554A (en) * | 2021-11-17 | 2022-03-22 | 哈尔滨工业大学（威海） | Nickel-based high-temperature alloy powder and preparation method applied to hollow turbine blade |
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| CN104475682A (en) * | 2014-12-17 | 2015-04-01 | 北京航空航天大学 | Combined wax pattern-based method of achieving precision investment casting for heat-resistant cast steel thin-wall turbine shell |
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| US20050036898A1 (en) * | 2003-08-12 | 2005-02-17 | Patrick Sweetland | Metal injection molded turbine rotor and metal injection molded shaft connection attachment thereto |
| CN101077644A (en) * | 2006-05-26 | 2007-11-28 | 南京盛润科技有限公司 | Gradient compound material and preparation method |
| CN101612824A (en) * | 2009-08-05 | 2009-12-30 | 李新桥 | A kind of metal/ceramic 3-layer composite material and preparation technology and application |
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| CN108580907A (en) * | 2018-06-05 | 2018-09-28 | 广东省材料与加工研究所 | A kind of preparation method and parallel double-screw extruder screwing element of the surface peening layer of screwing element |
| CN114214554A (en) * | 2021-11-17 | 2022-03-22 | 哈尔滨工业大学（威海） | Nickel-based high-temperature alloy powder and preparation method applied to hollow turbine blade |
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| CN107035412B (en) | 2019-11-15 |
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