CN101037739A - High-temperature alloy material - Google Patents
High-temperature alloy material Download PDFInfo
- Publication number
- CN101037739A CN101037739A CN 200610024848 CN200610024848A CN101037739A CN 101037739 A CN101037739 A CN 101037739A CN 200610024848 CN200610024848 CN 200610024848 CN 200610024848 A CN200610024848 A CN 200610024848A CN 101037739 A CN101037739 A CN 101037739A
- Authority
- CN
- China
- Prior art keywords
- temperature
- alloy
- high temperature
- superalloy
- temperature alloy
- 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
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a novel high-temperature alloy material, charactrized in that it has excellent mechanical performance under high temperature, in particular has lasting creep resistance under high temperature, while the high-temperature alloy material of the invention has oxidation resistance under high temperature and corrosion resistance under high temperature. The high-temperature alloy material of the invention is usable for producing combustion engine heat channel parts with high creep resistance under high temperature, while can greatly improve the service life of the heat channel parts. The surface of the heat channel parts produced by the high-temperature alloy material of the invention is coated high-temperature alloy protecting layer, accordingly it can further improve the service life of the heat channel parts.
Description
Affiliated technical field
The present invention relates to a kind of high temperature alloy, its main application is to make for high temperature oxidation corrosion resistance, metal parts that the high temperature creep-resisting Capability Requirement is very high.One of main application of high temperature alloy of the present invention is manufacturing and the maintenance that is used for gas turbine hot passage parts.
Background technology
The operating temperature of gas turbine hot passage parts is up to 1100 to 1400 degrees centigrade, under such ultra high temp, general Metal and Alloy can not satisfy hot passage parts necessary mechanical strength and anti-oxidant corrosion resistance, must design the superalloy with various High-Temperature Strengthening mechanism and could satisfy the requirement of making gas turbine hot passage parts.Superalloy is a class alloy of using under the harsh mechanical stress of high temperature and oxidation, corrosive environment.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
Superalloy of the present invention contains multiple alloying elements such as nickel chromium cobalt molybdenum aluminium titanium manganese zirconium borosilicate 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 strong especially high temperature creep-resisting ability, 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, be fit to make the extra high combustion machine of high temperature creep-resisting Capability Requirement thermal part.
The technical solution adopted for the present invention to solve the technical problems is: multiple alloying elements such as nickel chromium cobalt molybdenum aluminium titanium manganese zirconium borosilicate carbon fully melt, merge even back by suitable cooling step moulding in strict accordance with composition proportion of the present invention in the ultrahigh-temperature vacuum oven, in fertile material, form tiny precipitated phase (second phase that disperse distributes), these precipitated phases can hinder the development of dislocation motion, lattice slippage and creep effectively under hot conditions, significantly improve the hot strength of alloy.The zirconium of trace and boron etc. have the active element of some special surface and are added into alloy, owing to its internal adsorption phenomenon is enriched in crystal boundary, fill up the crystal boundary room, reduce defective, reduce the crystal boundary diffusion in the creep process, assemble and grow up at crystal boundary thereby suppressed strengthening phase, simultaneously can also remove obnoxious flavour and impurity element, make grain-boundary strengthening, improve the hot strength of alloy effectively, thereby make alloy material of the present invention have good creep-resistant property.Also be furnished with anti-oxidant erosion-resisting metal ingredient under hot conditions in the material prescription of the present invention, under hot conditions, have anti-oxidant erosion-resisting performance to guarantee material.
In the hot passage parts surface-coated superalloy supercoat made from superalloy of the present invention, the work-ing life that can further improve hot passage parts.
The invention has the beneficial effects as follows: novel high-temperature alloy material of the present invention has the ability of strong especially high temperature creep-resisting ability, persistent resistance to high temperature oxidation and high temperature corrosion, can be used for the manufacturing of gas turbine hot passage parts.
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.
Claims (5)
1. high temperature alloy, concrete composition is as follows: nickel: surplus; Cobalt: 19.0%-21.0%; Chromium: 19.0%-21.0%; Molybdenum: 5.4%-6.4%; Aluminium: 0.4%-0.6%; Titanium: 1.8%-2.4%; Manganese: 0.3%-0.5%; Silicon: 0.2%-0.4%; Carbon: 0.04%-0.08%; Zirconium: 0.015%-0.025%; Boron: 0.0005%-0.0015%; Other all dirts＜0.30%
2. high temperature alloy according to claim 1 is characterized in that this material can be used for the manufacturing of the superalloy hot passage parts of internal combustion turbine, especially to the extra high hot passage parts of high temperature creep-resisting Capability Requirement.
3. high temperature alloy according to claim 1 is characterized in that having outstanding hot strength and other high-temperature mechanical properties with the superalloy thermal part of the internal combustion turbine of this material manufacturing.
4. high temperature alloy according to claim 1 is characterized in that having outstanding high-temperature oxidation resistant and high-temperature corrosion-resistance performance with the superalloy hot passage parts of the internal combustion turbine of this material manufacturing.
5. the superalloy hot passage parts surface-coated superalloy supercoat of the internal combustion turbine of making at high temperature alloy according to claim 1, the work-ing life that can further improve hot passage parts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200610024848 CN101037739A (en) | 2006-03-17 | 2006-03-17 | High-temperature alloy material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200610024848 CN101037739A (en) | 2006-03-17 | 2006-03-17 | High-temperature alloy material |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101037739A true CN101037739A (en) | 2007-09-19 |
Family
ID=38888911
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200610024848 Pending CN101037739A (en) | 2006-03-17 | 2006-03-17 | High-temperature alloy material |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101037739A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101899593A (en) * | 2010-04-06 | 2010-12-01 | 江苏立新合金实业总公司 | Nickel-chromium high-resistance electrothermal alloy |
| CN106756248A (en) * | 2016-12-02 | 2017-05-31 | 四川六合锻造股份有限公司 | Ni Cr Co bases age-hardening type high temperature alloys and its smelting process |
| 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 |
| CN107829055A (en) * | 2017-10-11 | 2018-03-23 | 桂林市晟博科技服务有限公司 | A kind of refractory alloy material and preparation method thereof |
| CN109822192A (en) * | 2019-03-06 | 2019-05-31 | 南昌航空大学 | A kind of preparation method of single crystal super alloy monocrystalline middle layer |
| CN110814577A (en) * | 2019-11-16 | 2020-02-21 | 国网河南省电力公司电力科学研究院 | Exothermic fusion brazing welding powder suitable for copper-clad steel grounding grid in dry-wet alternating environment |
-
2006
- 2006-03-17 CN CN 200610024848 patent/CN101037739A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101899593A (en) * | 2010-04-06 | 2010-12-01 | 江苏立新合金实业总公司 | Nickel-chromium high-resistance electrothermal alloy |
| CN106756248A (en) * | 2016-12-02 | 2017-05-31 | 四川六合锻造股份有限公司 | Ni Cr Co bases age-hardening type high temperature alloys and its smelting process |
| 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 |
| CN107829055A (en) * | 2017-10-11 | 2018-03-23 | 桂林市晟博科技服务有限公司 | A kind of refractory alloy material and preparation method thereof |
| CN109822192A (en) * | 2019-03-06 | 2019-05-31 | 南昌航空大学 | A kind of preparation method of single crystal super alloy monocrystalline middle layer |
| CN109822192B (en) * | 2019-03-06 | 2023-10-03 | 南昌航空大学 | Preparation method of single crystal intermediate layer of single crystal superalloy |
| CN110814577A (en) * | 2019-11-16 | 2020-02-21 | 国网河南省电力公司电力科学研究院 | Exothermic fusion brazing welding powder suitable for copper-clad steel grounding grid in dry-wet alternating environment |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Jiang et al. | Review of porous intermetallic compounds by reactive synthesis of elemental powders | |
| US6221181B1 (en) | Coating composition for high temperature protection | |
| RU2433197C2 (en) | Heat-resistant nickel-based alloy, part manufacturing method, and turbomachine part | |
| EP2532761B1 (en) | Cobalt-nickel base alloy and method of making an article therefrom | |
| CN102808113B (en) | Process for preparing nickel-base superalloy | |
| EP1586669B1 (en) | Oxidation resistant superalloy and article | |
| CN104120325A (en) | Low thermal expansion coefficient NaMxAlySiz high entropy alloy and preparation method thereof | |
| CN101037739A (en) | High-temperature alloy material | |
| CN101372730A (en) | Gamma''strengthened high performance casting nickel-based high-temperature alloy | |
| CN100588730C (en) | Rich chromium evolution phase reinforcing high chromated nickel base high-temperature alloy and preparation thereof | |
| CN101037738A (en) | High-temperature alloy part and welding material | |
| CN114351027A (en) | High entropy alloy with low specific gravity | |
| Kumar et al. | A critical review on mechanically alloyed high entropy alloys: processing challenges and properties | |
| CN104404321A (en) | Super-strength aluminum alloy drill rod pipe body for super-deep well and manufacturing method for super-strength aluminum alloy drill rod pipe body | |
| CN105543568A (en) | Platinum-contained and rhenium-free nickel base single crystal superalloy and preparation method and application thereof | |
| CN102808111A (en) | Preparation method for nickel-based superalloy for exhaust valve | |
| CN114214532B (en) | Method for realizing gamma-TiAl alloy refinement by accurately controlling metastable structure stabilization | |
| CN1540015A (en) | Precipitation reinforced Ni-Fe-Cr alloy and its prodn. method | |
| KR100725624B1 (en) | Ni-based single crystal superalloys | |
| CA1198612A (en) | Nickel base superalloy | |
| CN101037740A (en) | High-temperature alloy part and welding material | |
| CN109536781B (en) | High-purity low-inclusion nickel-based powder high-temperature alloy and preparation method and application thereof | |
| CN101037754A (en) | High-temperature alloy part and welding material | |
| CN101429609B (en) | Novel high-temperature alloy and method for producing the same | |
| Kablov et al. | Strategic trends of development of structural materials and technologies of their processing for modern and future aircraft engines |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |