CN101037754A - High-temperature alloy part and welding material - Google Patents
High-temperature alloy part and welding material Download PDFInfo
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- CN101037754A CN101037754A CN 200610024844 CN200610024844A CN101037754A CN 101037754 A CN101037754 A CN 101037754A CN 200610024844 CN200610024844 CN 200610024844 CN 200610024844 A CN200610024844 A CN 200610024844A CN 101037754 A CN101037754 A CN 101037754A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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Abstract
The running temperature of the metal parts in the high-temperature structurre of combustion turbine can reach 1100-1400 DEG C, accordingly the parts are made of costly high-temperature alloy, and there are welding materials with special chemical component for connecting the parts, in order that the formed metal connecting body has good gross mechanical property. In addition, all kinds of high-temperature alloy parts can be damaged in the running environment of high temperature, the welding repair is an important part of repairing for replacing damaged high-temperature alloy parts, while the choice of welding materials is extremely important except reasonable welding process, false or unqualified welding materials will directly result in the discard of the parts.
Description
Affiliated technical field
The present invention relates to a kind of high temperature alloy, its main application is to make to be used for gas turbine component and other high-temperature alloy parts, and makes the welding material that welding nickel base superalloy parts are used.
Background technology
The operating temperature of the metal parts in the gas turbine high temperature structure reaches as high as 1100 to 1400 degrees centigrade, these parts all are to be made by the superalloy of costliness, connect the welding material that these parts need special Chemical Composition, good overall mechanical property is arranged to guarantee the metal disjunctor that forms.In addition, under pyritous running environment, various high-temperature alloy parts can produce certain damage, weld repairs is for a very important part in the high-temperature alloy part place under repair that damage is arranged that changes, and weld repairs is except having the rational welding, it is highly important that the selection of welding material, welding material mistake or underproof will directly cause scrapping of parts.
Being used to make the metal parts that moves under the hot conditions and the superalloy of welding material is still to have excellent mechanical intensity under high temperature and harsh running environment, a class alloy of anti-oxidant, corrosion resistance.Along with the development of scientific and technological cause, superalloy forms six comparatively complete parts gradually.
One, wrought superalloy
Wrought superalloy is meant and can carries out heat, cold deformation processing, and operating temperature range-253～1320 ℃ has good mechanical performance and comprehensive strong, toughness index, has a class alloy of higher anti-oxidant, corrosion resistance.Can be divided into solution strengthening type alloy and ageing strengthening type alloy by its thermal treatment process.
1, solution strengthening type alloy
The use temperature scope is 900～1300 ℃, and high anti-oxidation temperature reaches 1320 ℃.GH128 alloy for example, room temperature tensile intensity is that 850MPa, yield strength are 350MPa; 1000 ℃ of tensile strengths are that 140MPa, unit elongation are that 85%, 1000 ℃, creep rupture life of 30MPa stress are 200 hours, unit elongation 40%.Solid solution alloy generally is used to make parts such as Aeronautics and Astronautics engine chamber, casing.
2, ageing strengthening type alloy
Use temperature is-253～950 ℃, generally is used to make structural parts such as the turbine disk of Aeronautics and Astronautics engine and blade.The alloy working temperature of making the turbine disk is-253～700 ℃, requires to have good high low temperature intensity and anti-fatigue performance.
For example: the GH4169 alloy reaches 1000MPa 650 ℃ high-yield strengths; The alloy temperature of making blade can reach 950 ℃, and for example: GH220 alloy, 950 ℃ tensile strength are 490MPa, and 940 ℃, creep rupture life of 200MPa were greater than 40 hours.
Wrought superalloy is mainly space flight, aviation, nuclear energy, oil civilian industry structural forging, cake material, ring, bar, sheet material, tubing, band and silk material is provided.
Two, cast superalloy
Cast superalloy is meant the type high temp alloy that can maybe can only use the castmethod forming part.Its principal feature is:
1. has wideer composition range
Owing to can take into account its deformation processing performance, the design of alloy can be concentrated and be considered to optimize its use properties.As for nickel base superalloy, can make γ ' content reach 60% or higher by adjusting composition, thereby under the temperature up to alloy melting point 85%, alloy still can keep premium properties.
2. has more wide Application Areas
Because the special benefits that has of castmethod, can be according to the use needs of part, design, produce nearly end form or do not have the superalloy foundry goods of any complex construction of having of surplus and shape.
According to the use temperature of casting alloy, can be divided into following three classes:
The first kind: at the equiax crystal cast superalloy of-253～650 ℃ of uses
This class alloy has good comprehensive performances in very big range temperature, particularly can keep intensity and plasticity all not to descend at low temperatures.As the K4169 alloy of large usage quantity on the Aeronautics and Astronautics engine, its 650 ℃ of tensile strengths are 1000MPa, yield strength 850MPa, stretching plastic 15%; 650 ℃, be 200 hours the creep rupture life under the 620MPa stress.Various pumps have been used for making in the diffuser-casing of aircraft engine and the airspace engine with complex structural member etc.
Second class: at the equiax crystal cast superalloy of 650～950 ℃ of uses
This class alloy at high temperature has higher mechanical property and hot corrosion resistance.K419 alloy for example, in the time of 950 ℃, tensile strength greater than 700MPa, stretching plastic greater than 6%; 950 ℃, 200 hours stress-rupture strength limit is greater than 230MPa.This class alloy is suitable for being used as aero engine turbine blades, turning vane and block cast turbine.
The 3rd class: at the directional freeze cylindrulite and the single crystal super alloy of 950～1100 ℃ of uses
This class alloy has excellent comprehensive performances and anti-oxidant, hot corrosion resistance in this temperature range.DD402 single crystal alloy for example, 1100 ℃, stress following creep rupture life of 130MPa were greater than 100 hours.This is the highest turbine blade material of domestic use temperature, is applicable to the Turbine Blade of making the novel high-performance engine.
Along with improving constantly of precision casting process technology, new special process also constantly occurs.The CA technology of thin brilliant foundry engieering, directional solidification technique, complex thin-wall structural part etc. all makes the cast superalloy level improve greatly, and range of application improves constantly.
Three, powder metallurgy high-temperature alloy
Adopt the atomizing superalloy powder, behind hip moulding or hot isostatic pressing, produce the product of superalloy powder again through the production technique of forging molding.Adopt powder metallurgical technique, because powder particle is tiny, speed of cooling is fast, thereby composition is even, no macrosegregation, and also crystal grain is tiny, and hot workability is good, the using rate of metal height, cost is low, and especially the yield strength of alloy and fatigue property are greatly improved.
The FGH95 powder metallurgy high-temperature alloy, 650 ℃ of tensile strength 1500MPa; 1034MPa stress following creep rupture life is greater than 50 hours, be current under 650 ℃ of working conditions the highest a kind of diskware powder metallurgy high-temperature alloy of strength level.Powder metallurgy high-temperature alloy can satisfy the service requirements of the higher engine of stress level, is the selection material of high temperature parts such as high thrust-weight ratio engine turbine disk, compressor disc and turbine baffle plate.
Four, oxide dispersion intensifying (ODS) alloy
Be to adopt unique mechanical alloying (MA) technology, superfine (less than 50nm) at high temperature has overstable oxide dispersion intensifying and is scattered in the alloy substrate equably mutually, and a kind of special superalloy that forms.Its alloy strength still can be kept under near the condition of the fusing point of alloy own, has excellent high-temperature creep property, superior high-temperature oxidation resistance, anti-carbon, sulfur corrosion performance.
Realized at present the three kinds of ODS alloys that mainly contain commercially produced:
MA956 alloy use temperature under oxidizing atmosphere can reach 1350 ℃, occupies position first of anti-oxidant, the anti-carbon of superalloy, the sulfur corrosion.Can be used for the aeroengine combustor buring chamber liner.
MA754 alloy use temperature under oxidizing atmosphere can reach 1250 ℃ and keep quite high hot strength, anti-in alkali glass corrode.Aircraft engine guider castor ring gear and turning vane now have been used to make.
The MA6000 alloy is that 222MPa, yield strength are 192MPa 1100 ℃ of tensile strengths; 1100 ℃, creep rupture strength was 127MPa in 1000 hours, occupied position first of the superalloy, can be used for blade of aviation engine.
Five, intermetallic compound high-temperature material
The intermetallic compound high-temperature material is that a class of recent research exploitation has the proportion high-temperature material important application prospect, light.For over ten years, exploitation and applied research to the basic research of intermetallic compound, alloy designs, technical process are ripe, are especially obtaining the achievement that attracts people's attention aspect processing technology of preparing, malleableize and reinforcement, mechanical property and the applied research of Ti-Al, Ni-Al and Fe-Al based material.
Ti
3Al base alloy (TAC-1), TiAl base alloy (TAC-2) and Ti
2AlNb base alloy has low density (3.8～5.8g/cm
3), advantages such as high-temp and high-strength, high stiffness and excellent anti-oxidant, creep resistance, can make structural part loss of weight 35～50%.
Ni
3Al base alloy, MX-246 have well corrosion-resistant, wear-resistant and gasproof erosion performance, show fabulous application prospect.Fe
3Al base alloy has good anti-oxidant wear-corrosion resistance, in middle temperature (less than 600 ℃) higher-strength is arranged, and cost is low, is a kind ofly can partly replace stainless novel material.
Six, high ambient temperature alloy
In a lot of fields of civilian industry, the construction material of military service all is in the pyritous corrosive environment.For satisfying market demand,, sort out serial superalloy according to the environment for use of material.
Summary of the invention
High temperature alloy of the present invention contains multiple alloying elements such as nickel chromium triangle molybdenum ferro-cobalt tungsten manganese silicon-carbon.The present invention is by testing the best proportion relation that has obtained various elements repeatedly, prove that superalloy of the present invention has effective especially hot metal and merges concatenation ability and make tie point keep the characteristic of good mechanical properties, special needs to be pointed out is that the present invention has possessed the ability of persistent resistance to high temperature oxidation and high temperature corrosion.
The technical solution adopted for the present invention to solve the technical problems is: multiple alloying elements such as nickel chromium triangle molybdenum ferro-cobalt tungsten manganese silicon-carbon fully melt, merge evenly the back by suitable cooling step moulding in strict accordance with the composition proportion of the best in the ultrahigh-temperature vacuum oven, thereby make alloy material composition of the present invention even and contain few oxide compound of trying one's best.Be furnished with the metal ingredient that anti-oxidant resistance to corrosion is very strong under hot conditions (chromium and silicon etc.) in the material prescription of the present invention, under hot conditions, have anti-oxidant erosion-resisting performance to guarantee material monolithic.Elements such as nickel chromium triangle molybdenum cobalt tungsten have the solution strengthening effect, and 0.1% carbon mainly forms granular carbide and is distributed in crystal boundary, stop intercrystalline slip.When high temperature alloy of the present invention is used as welding material when being used for the welding of high-temperature alloy part, the microalloy composition of the interpolation in the alloy makes to form between scolder and the alloy component body has the metal disjunctor of good overall mechanical property, thereby has guaranteed the normal operation of parts.
The invention has the beneficial effects as follows: novel high-temperature alloy material of the present invention has the ability of persistent resistance to high temperature oxidation and high temperature corrosion and is very easy to and the effective characteristic that merges and keep excellent mechanical performances of other superalloys, can be used for making the employed welding material of gas turbine hot parts welding maintenance.
Embodiment
Multiple alloying element is fully melted, merges evenly the back after in strict accordance with composition proportion of the present invention by suitable cooling step moulding in the ultrahigh-temperature vacuum oven, make superalloy ingot or sheet material, adopt the method moulding high-temperature alloy part of forging or precision casting, half precision casting then.As required can be on the high-temperature alloy part surface made from method coated with high temperature alloy protecting coatings such as thermospray, physics coating, chemical coatings with the present invention.
Utilize advanced preparation technology of welding wire,, produce the welding wire that is used for the high-temperature alloy part welding avoiding high temperature alloy oxidation of the present invention, being mingled with under the situation with element loss.(noting: during production, the oxidation of metal, be mingled with the quality that all can influence welding wire with the loss of element, pay special attention to)
For the convenience that the welder uses, the welding wire length of all manual weldings is decided to be 91 centimetres (about 36 inches) without exception, and simultaneously, the code name title that must suppress the welding wire material therefor at the head of every root bead silk is in order to avoid mistake occurs when welding.The diameter of welding wire is selected or manufacturing by actual needs.Wherein, gage of wire comparatively commonly used has in the welding maintenance of gas turbine hot parts: 0.9 millimeter (about 0.035 inch), 1.6 millimeters (about 1/16 inch) and 2.4 millimeters (about 3/32 inches) etc.
Claims (3)
1. high temperature alloy, concrete composition is as follows: nickel: surplus; Chromium: 21.0%～23.0%; Molybdenum: 8.5%～9.5%; Cobalt: 1.2%～1.8%; Iron: 18.0%～19.0%; Tungsten: 0.5%～0.7%; Manganese: 0.4%～0.6%; Silicon: 0.4%～0.6%; Carbon: 0.05%～0.15%; Other all dirts＜0.30%.
2. high temperature alloy according to claim 1 can be used for making gas turbine hot passage parts and other high-temperature alloy parts, and is used for making the employed welding material of welding nickel base superalloy parts.
3. superalloy welding material according to claim 2 is characterized in that having excellent high-temperature intensity with the high-temperature alloy part of this superalloy scolder REPAIR WELDING, high temperature anti-fatigue performance and other high-temperature mechanical properties.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200610024844 CN101037754A (en) | 2006-03-17 | 2006-03-17 | High-temperature alloy part and welding material |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200610024844 CN101037754A (en) | 2006-03-17 | 2006-03-17 | High-temperature alloy part and welding material |
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| CN101037754A true CN101037754A (en) | 2007-09-19 |
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| CN 200610024844 Pending CN101037754A (en) | 2006-03-17 | 2006-03-17 | High-temperature alloy part and welding material |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107760960A (en) * | 2017-10-11 | 2018-03-06 | 桂林市晟博科技服务有限公司 | A kind of high-temperature alloy material and preparation method thereof |
| CN113732562A (en) * | 2021-08-19 | 2021-12-03 | 江苏新航合金科技有限公司 | High-temperature-resistant corrosion-resistant nickel-based alloy welding material for pressure container |
-
2006
- 2006-03-17 CN CN 200610024844 patent/CN101037754A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107760960A (en) * | 2017-10-11 | 2018-03-06 | 桂林市晟博科技服务有限公司 | A kind of high-temperature alloy material and preparation method thereof |
| CN113732562A (en) * | 2021-08-19 | 2021-12-03 | 江苏新航合金科技有限公司 | High-temperature-resistant corrosion-resistant nickel-based alloy welding material for pressure container |
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