CN103949646A - Preparation method for Nb-Si base ultra-temperature alloy turbine vane - Google Patents
Preparation method for Nb-Si base ultra-temperature alloy turbine vane Download PDFInfo
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Abstract
The invention belongs to the technical field of the turbine blade manufacturing, and particularly relates to a method for preparing an Nb-Si base ultra-temperature alloy turbine vane by the electron beam melting (EBM). Electron beam selection area high-speed forming equipment is utilized, and the preparation of the complex Nb-Si alloy turbine vane is directly finished in one step by a CAD (computer-aided design) model by setting a reasonable technological parameter; the obtained turbine vane has the advantages of high consistency, good forming precision and few defects; the alloy vane mainly consists of Nbss sosoloid and Nb5Si3 phase, so that the alloy vane has a small phase size and even distribution, and the combination property of the turbine vane can be improved. According to the method, no dies are required in the turbine vane forming process, alloy pollution and oxidation can be reduced, inclusion content is lowered, the alloy material use ratio is high, and the combination property of the vane can be improved.
Description
Technical field
The invention belongs to turbo blade manufacturing technology field, be specifically related to a kind of preparation method of Nb-Si based ultra-high temperature alloy turbine blade.
Background technology
The development of high performance airplane depends on the lasting progress of aero engine technology.Along with the raising of gas-turbine unit thrust-weight ratio and efficiency, turbine inlet temperature (TIT) constantly increases.In combustion turbine engine components, the condition of work of turbo blade is the harshest, not only to bear extreme high temperature, heavily stressed and severe corrosive environment, and requiring the long life, this just requires turbo blade material to have high creep-resistant property, good corrosion resistance, high creep rupture strength and fracture toughness etc.
The third generation nickel-base high-temperature single crystal alloy that aero engine turbine blades uses at present, its serviceability temperature limit is 1150 DEG C, approaches 85% of this alloy melting point, it is very difficult wanting further to improve its serviceability temperature.Therefore exploitation has the more blade material of bearing high temperature ability, to the manufacture important in inhibiting of aero-engine.In in the past more than 20 year, refractory silicide is subject to extensive concern because of features such as its high-melting-point, low-density and good high-temperature behaviors.Wherein Nb-Si base alloy (density 6.6～7.2g/cm
3, fracture toughness can exceed 20MPam
1/2), the most potential as engine turbine blade material.
Nb-Si based ultra-high temperature alloy basic composition is toughness solid solution Nb mutually
sswith hard intermetallic compound Nb
5si
3.This tough/hard two-phase structure, in performance excellent high intensity, has certain Toughness.Due to Nb-Si base alloy melting point high (exceeding 1800 DEG C), contain the contour active element of a large amount of Ti and Hf simultaneously, cause alloy material preparation difficulty.The preparation of Nb-Si base alloy mainly contains the methods such as non-consumable vacuum arc melting, induction melting, model casting and directional solidification.Nb-Si base alloy is prepared in vacuum arc melting, and structural homogenity is uncontrollable, has a large amount of shrinkage cavity shrinkage porosities, affects alloy property.Vacuum induction melting is prepared Nb-Si base alloy, can keep alloying component even, but preparation process melt temperature is inhomogeneous, and the degree of superheat is low, easily forms the defects such as poured short.Directional solidification can obtain the tissue of good combination property, have near-net forming and efficiency high etc. feature, become the prefered method of preparation Nb-Si base alloy, but at high temperature, melt is very easy to and crucible generation interfacial reaction, and oxygen content and be mingled with increase reduces alloy property.Model casting is prepared Nb-Si alloy technology and is not also attained full development, and the Nb-Si base alloy activity of melting has limited the application of ceramic base formwork system.
Moreover, turbo blade structure is complicated (accompanying drawing 1) extremely, adopts said method to prepare blade and need to prepare complicated mould or formwork, and technique is loaded down with trivial details, needs many postprocessing working procedures simultaneously, and production efficiency is low.Therefore, the Problems in forming of solution Nb-Si based ultra-high temperature alloy turbine blade is most important.
Summary of the invention
The present invention, just for the problems referred to above, provides a kind of employing electron beam selective melting RP technique (electron beam melting, EBM) to prepare fast the method for NbSi based ultra-high temperature alloy turbine blade.
EBM can realize 3 D complex structure parts without mould, high performance quick preparation.Its principle is: based on discrete/stack shaping principle, utilize computer to obtain the three-dimensional CAD physical model of parts, then utilize delamination software to carry out hierarchy slicing in component height direction, and the three-D profile information of parts is converted into two-dimensional silhouette information, and generate scanning pattern.The high-power electron beam of electron gun transmitting is according to the scanning pattern of specifying, and the successively preset metal or alloy powder of melt deposition, piles up layer by layer and form 3 d part.EBM method economy, quick, is specially adapted to the preparation of difficult processing, high-performance refractory metal or alloy part.
The present invention utilizes electron beam selective melting RP technique to prepare NbSi based ultra-high temperature alloy turbine blade, and accompanying drawing 2 is the structural principle schematic diagram of electron beam quickly shaping device.
The technical scheme that the present invention prepares turbo blade is:
A fast preparation method for NbSi based ultra-high temperature alloy turbine blade, is characterized in that comprising the following steps:
1. first utilize three-dimensional graphics software (Magics) to set up the three-dimensional CAD model of the turbo blade (7) needing, and save as stl file; Then utilize delamination software (EBM assembler) stl file to be carried out in short transverse to hierarchy slicing processing, be divided into the section of even thickness (0.05～0.1mm), cross-sectional profiles information and scanning machining path that section comprises blade (7); Utilize delamination software that section is saved as to ABF file, and import in electron beam constituency quickly shaping device (9);
2. NbSi alloy powder is encased in the Pu Fen mechanism (5) in equipment (9).When equipment (9) is evacuated to 10
-3pa～10
-2after Pa, electron gun (1) is launched electronic beam current (2), and under the effect of focus coil (3) and deflection coil (4), according to the pre-hot path (13) of design in advance, forming board (8) is carried out to preheating;
3. preheating forming board (8) is to assigned temperature, and Pu Fen mechanism (5) is at the NbSi alloy powder (6) of forming board (8) layer overlay specific thicknesses (identical with slice thickness); Then electron gun (1) is launched electronic beam current (2), and under the effect of focus coil (3) and deflection coil (4), according to the pre-hot path (13) of design in advance, all powder (6) is carried out to preheating;
4. preheating powder (6) is to assigned temperature, electronic beam current (2) stream is according to metal (alloy) powder (6) of the fusing appointed area, fusing path (14) of designing in advance, and local metal dust (6) fusing that electronic beam current (2) scans forms molten bath (11) and deposits and obtain sedimentary deposit (10) rapidly along with leaving of electronic beam current (2);
5. after completing an aspect processing, forming board (8) moves down the distance of a powder (6) bed thickness, Pu Fen mechanism (5) is at the upper new metal dust (6) of layer overlay of sedimentary deposit (10), repeating step 3,4, pile up so layer by layer, until complete the processing of whole turbo blade (7);
Pre-alloyed NbSi base alloy powder prepared by Powder In Argon Atomization that the present invention adopts, is characterized in that NbSi powder is spherical in shape or subsphaeroidal, and diameter should be between 50～150 μ m.
In the present invention, in NbSi supertherm turbo blade preparation process, paving powder thickness is 0.05mm～0.1mm.
In the present invention, NbSi supertherm turbo blade preparation process adopts Ti6Al4V forming board, and thickness is 10mm.
In the present invention, NbSi supertherm turbo blade preparation process comprises basal plate preheating, powder preheating and fusion process, and warm is to prevent that powder from splashing, and promotes powder presintering, make to be shaped maintains a higher temperature simultaneously, reduces shaping blade internal stress.
In the present invention, in preparation NbSi superhigh temperature turbo blade process, beam voltage maintains 60kV.
In the present invention, the pre-thermal parameter of forming board that preparation NbSi superhigh temperature turbo blade adopts is: beam scan velocity is 12000mm/s, and electronic beam current is 40mA, sweep span 0.05～0.2mm.
In the present invention, the pre-thermal parameter of powder that preparation NbSi superhigh temperature turbo blade adopts is: preheating 6～10 times, and beam scan velocity is 6000mm/s～8000mm/s, electronic beam current is 30～40mA, sweep span 0.05～0.2mm;
In the present invention, the powder smelting parameter that preparation NbSi superhigh temperature turbo blade adopts is: melt 1 time, beam scan velocity is 400～600mm/s, and fusion current is 8～12mA, sweep span 0.05～0.2mm.
In the present invention, the vacuum of preparation NbSi superhigh temperature turbo blade equipment maintains 10
-3pa～10
-2pa;
In the present invention, the preheat temperature of forming board and powder is identical, is controlled between 900～1100 DEG C;
In the present invention, after preparation NbSi superhigh temperature turbo blade process completes, pour argon gas quickening to blade shaping district cooling, while being down to 100 DEG C to leaf temperature, taking out blade and be cooled to room temperature.
Compared with the method for preparing aero engine turbine blades with conventional method, the advantage of technical solution of the present invention is:
(1) electron beam constituency RP technique is subject to the restriction of blade shape hardly, the directly turbo blade of machining shape complexity, near-net-shape, shaping blade without or little post processing; In forming process, without forging, casting and mould, avoid alloy to pollute, significantly shorten the manufacturing cycle of blade, reduce manufacturing cost; Undressed, unnecessary NbSi powder can recycle and reuse simultaneously, and stock utilization is high;
(2) in NbSi alloy, low-alloyed performance can fall in the increase of oxygen content; and the high vacuum environment that electron beam shaping adopts; the NbSi alloy of the condition of high temperature is had to better protection effect; can effectively avoid the oxidation of alloy; under vacuum, there is refining effect simultaneously, can improve the performance of NbSi alloy vane.
(3) capacity usage ratio high (electron beam absorptivity >75%), line can be easy to realize high-power, thereby the fusing stackeding speed of material is very fast, and turbo blade manufacture is rapid.
(4) due to powder is carried out to preheating, when shaping, leaf temperature maintains between 900～1100 DEG C all the time, is equivalent to thermal processes act on the one hand, and the built-in thermal stress of shaping blade is reduced, and prevents distortion, is conducive to the matched well of blade strength and plasticity; Contribute on the other hand the homogenization of leaf tissue performance.
(5) electron beam Quick-forming NbSi turbo blade, when powder smelting, pool size is very little, setting time is extremely short, therefore cooling velocity is very large, is height nonequilibrium freezing, and setting time is extremely short, can effectively reduce the microsegregation of NbSi alloy, and alloy density is high, there is tiny, even, stable rapid solidification tissue, thereby obtain the NbSi supertherm turbo blade of mechanical property excellence.
(6) EBM technology can directly be prepared complex-shaped turbo blade, and blade density (>99%) and forming accuracy are higher, and blade surface roughness is about Ra25; Powder smelting sintering is abundant, and interlayer is in conjunction with good, and blade surface is without obvious pore and not molten powder.Leaf tissue is by Nb
sssolid solution and Nb
5si
3two phase compositions, two phase sizes are very tiny, reach nanoscale, and two-phase is evenly distributed, and these tissue signatures are conducive to improve the combination property of blade.
Below by the drawings and specific embodiments in detail the present invention is described in detail.
Brief description of the drawings:
Accompanying drawing 1 is turbo blade structural representation;
Accompanying drawing 2 is EBM equipment and forming process schematic diagram thereof;
Accompanying drawing 3 is EBM process microcosmic schematic diagram;
Accompanying drawing 4 is basal plate preheating in EBM process, powder preheating and powder smelting schematic diagram;
The Nb-18Si-24Ti-2Cr-2Al-2Hf turbo blade pictorial diagram that accompanying drawing 5 is prepared for EBM technology;
The Nb-18Si-24Ti-2Cr-2Al-2Hf turbo blade XRD spectra that accompanying drawing 6 is prepared for EBM technology;
Accompanying drawing 7 is prepared Nb-18Si-24Ti-2Cr-2Al-2Hf turbo blade cross section micro-organization chart for EBM technology;
Each digital implication in accompanying drawing:
1-electron gun; 2-electronic beam current; 3-focus coil; 4-deflection coil; 5-Pu Fen mechanism; 6-alloy powder; 7-turbo blade;
8-forming board; 9-former; 10-sedimentary deposit; 11-molten bath; The pre-hot path of 12-; 13-melts path.
Detailed description of the invention
Embodiment 1:Nb-18Si-24Ti-2Cr-2Al-2Hf (at.%, atomic percent) supertherm turbo blade is prepared fast.
1. first utilize CAD 3D graphics software (as Magics etc.) to set up the D S TL file of Nb-18Si-24Ti-2Cr-2Al-2Hf alloy turbine blade (7); Then utilize delamination software (as EBM assembler etc.) stl file to be carried out in short transverse to hierarchy slicing processing, be evenly divided into the section that thickness is 0.05mm, cross section information and scanning machining path that section comprises blade (7); Utilize delamination software that section is saved as to ABF file, and import in electron beam constituency quickly shaping device (9);
2. by argon gas atomization size, the Nb-18Si-24Ti-2Cr-2Al-2Hf powder (6) between 50～150 μ m packs in Pu Fen mechanism (5).Equipment (9) is evacuated to 10
-3～10
-2after Pa, electron gun (1) is launched electronic beam current (2), and under the effect of focus coil (3) and deflection coil (4), according to the pre-hot path of Z-shaped (13), Ti6Al4V forming board (8) is carried out to preheating, pre-thermal parameter is: sweep speed 12000mm/s, line is 40mA, and sweep span is 0.2mm.
3. preheating forming board (8) is after 1000 DEG C, the Nb-18Si-24Ti-2Cr-2Al-2Hf powder (6) that Pu Fen mechanism (5) is 0.05mm at forming board (8) layer overlay thickness;
4. after one deck paving powder completes, electron gun (1) is launched electronic beam current (2), and under the effect of focus coil (3) and deflection coil (4), according to the pre-hot path of Z-shaped (13), all powder (6) is carried out to preheating; Pre-thermal parameter is: preheating 6 times, and sweep speed 6000mm/s, line 30mA, sweep span is 0.2mm;
5. preheating powder (6) is after 1000 DEG C, and Nb-18Si-24Ti-2Cr-2Al-2Hf alloy powder (6) is melted in the fusing path (14) that electronic beam current (2) stream is specified according to current layer.Melting characteristic parameter is: melts 1 time, and sweep speed 500mm/s, fusion current is 10mA, sweep span 0.1mm.Local alloy powder (6) fusing that electronic beam current (2) scans forms molten bath (11) and solidifies rapidly deposition along with leaving of electronic beam current (2) and obtains sedimentary deposit (10); After completing an aspect processing, forming board (8) is mobile 0.05mm (thickness of a powder bed) vertically downward;
6. Pu Fen mechanism (5) is the NbSi base alloy powder (6) that 0.05mm is new at the upper layer overlay thickness of sedimentary deposit (10), repeating step 4-5.Pile up so layer by layer, until complete the processing of turbo blade (7);
7. after turbo blade (7) has been manufactured, pour argon gas quickening cooling to shaped region, while being down to 100 DEG C to turbo blade (7) temperature, taking-up air cooling are to room temperature.
Can be found out by accompanying drawing 5, utilize electron beam constituency RP technique (EBM) can prepare the turbo blade with labyrinth, blade shaping density (>99%) and precision are higher, and surface roughness is about Ra25; Powder smelting sintering is abundant, and interlayer is in conjunction with good, and blade surface does not have pore and not molten powder to occur.
Can be drawn by accompanying drawing 6, the tissue of electron beam selective melting Quick-forming Nb-18Si-24Ti-2Cr-2Al-2Hf turbo blade is mainly Nb
sSsolid solution and Nb
5si
3two-phase.
Accompanying drawing 7 is the micro-organization chart of electron beam constituency Quick-forming Nb-18Si-24Ti-2Cr-2Al-2Hf blade, and wherein light color is Nb mutually
sS, dark color is Nb mutually
5si
3.Draw shaping blade dense structure by figure, (m), interlayer, in conjunction with good, does not have not molten alloy powder to size <1 μ the circular pore of the minimum rule of a small amount of size; Nb in blade
sSsolid solution and Nb
5si
3two-phase is very tiny, reaches nanoscale, and two-phase is evenly distributed, and these tissue signatures are conducive to improve the combination property of blade.
In the present invention, in the process of electron beam selective melting turbine blades, blade matrix remains higher temperature, contributes to the homogenization of structure property, and in the different position of blade, tissue signature is basically identical.
The above, be only preferred embodiment of the present invention, not limits the invention, and the NbSi alloying component that technical spirit according to the present invention is done above-mentioned example, the simple modification of preparation parameter, within still belonging to technical scheme protection domain of the present invention.
Claims (17)
1. a fast preparation method for NbSi based ultra-high temperature alloy turbine blade, is characterized in that, utilizes electron beam selective melting RP technique to prepare turbo blade, and preparation process comprises the following steps:
(1). set up the three-dimensional CAD model of turbo blade to be processed, then in short transverse, it is carried out to hierarchy slicing processing to be divided into the section of even thickness, cross-sectional profiles information and machining path that section comprises turbo blade, and the file of cutting into slices imports in the quickly shaping device of electron beam constituency;
(2). in the quickly shaping device of electron beam constituency, pack NbSi alloy powder into, and forming board is positioned in the forming cavity of electron beam constituency quickly shaping device on liftable platform, and forming cavity is vacuumized;
(3). utilize electron beam, according to the pre-hot path of design in advance, forming board is carried out to preheating, after preheating completes, powder-scraping device is evenly laid one deck NbSi alloy powder on substrate, and powder thickness equates with slice thickness in step (1);
(4). utilize electron beam, according to the pre-hot path of design in advance, all powder on substrate is carried out to preheating;
(5). powder is preheated to after assigned temperature, electronic beam current stream is according to the alloy powder of the fusing appointed area, fusing path of designing in advance, and the local alloy powder fusing that electronic beam current scans forms molten bath and rapid deposition obtains sedimentary deposit along with leaving of electronic beam current;
(6). in completing steps (5), to after the processing of an aspect, the distance of a bed thickness of forming board decline, evenly lays one deck NbSi alloy powder on the sedimentary deposit that powder-scraping device forms in step (5) again;
(7). repeat above-mentioned steps (4)-(6), until NbSi supertherm blade processing completes; After machining, pour refrigerating gas to forming cavity, accelerate the cooling of turbo blade, while being down to below 100 DEG C to the temperature of turbo blade, take out and be cooled to room temperature.
2. the fast preparation method of a kind of NbSi based ultra-high temperature alloy turbine blade according to claim 1, is characterized in that, the slice thickness described in step (1) is 0.05～0.1mm.
3. the fast preparation method of a kind of NbSi based ultra-high temperature alloy turbine blade according to claim 1, it is characterized in that, NbSi alloy powder selected in step (2) is prepared by Powder In Argon Atomization and obtains, spherical in shape or subsphaeroidal, and diameter is 50～150 μ m.
4. the fast preparation method of a kind of NbSi based ultra-high temperature alloy turbine blade according to claim 1, is characterized in that, described NbSi alloy powder composition is counted Nb-18Si-24Ti-2Cr-2Al-2Hf with atomic percent.
5. according to the fast preparation method of a kind of NbSi based ultra-high temperature alloy turbine blade described in claim 1 or 4, it is characterized in that, can directly prepare complex-shaped turbo blade, the turbo blade density >99% that cool to room temperature obtains, surface accuracy is higher, forming defects is few, and Main Tissues is by Nb
sssolid solution and Nb
5si
3hardening constituent composition, phase size <1 μ m and being evenly distributed.
6. the fast preparation method of a kind of NbSi based ultra-high temperature alloy turbine blade according to claim 1, is characterized in that, described forming board adopts Ti6Al4V forming board.
7. the fast preparation method of a kind of NbSi based ultra-high temperature alloy turbine blade according to claim 6, is characterized in that, described Ti6Al4V forming board thickness is 10mm.
8. the fast preparation method of a kind of NbSi based ultra-high temperature alloy turbine blade according to claim 1, is characterized in that, the beam voltage of described electron beam constituency quickly shaping device maintains 60kV.
9. the fast preparation method of a kind of NbSi based ultra-high temperature alloy turbine blade according to claim 1, is characterized in that, the vacuum vacuumizing in step (2) in postforming chamber is 10
-3pa～10
-2pa.
10. the fast preparation method of a kind of NbSi based ultra-high temperature alloy turbine blade according to claim 1, is characterized in that, in step (3), the preheat temperature of substrate is 900～1100 DEG C.
11. according to the fast preparation method of a kind of NbSi based ultra-high temperature alloy turbine blade described in claim 1 or 10, it is characterized in that, in step (3), the pre-thermal parameter of substrate is: beam scan velocity is 12000mm/s, electronic beam current is 40mA, sweep span 0.05～0.2mm.
The fast preparation method of 12. a kind of NbSi based ultra-high temperature alloy turbine blades according to claim 1, is characterized in that, in step (4), the preheat temperature of powder is identical with substrate, is 900～1100 DEG C.
13. according to the fast preparation method of a kind of NbSi based ultra-high temperature alloy turbine blade described in claim 1 or 12, it is characterized in that, in step (4), the pre-thermal parameter of powder is: preheating 6～10 times, beam scan velocity is 6000mm/s～8000mm/s, electronic beam current is 30～40mA, sweep span 0.05～0.2mm.
The fast preparation method of 14. a kind of NbSi based ultra-high temperature alloy turbine blades according to claim 1, is characterized in that, in step (3), the NbSi alloy powder thickness of evenly laying on substrate is 0.05～0.1mm.
The fast preparation method of 15. a kind of NbSi based ultra-high temperature alloy turbine blades according to claim 1, it is characterized in that, in step (5), powder smelting parameter: melt 1 time, beam scan velocity is 400～600mm/s, fusion current is 8～12mA, sweep span 0.05～0.2mm.
The fast preparation method of 16. a kind of NbSi based ultra-high temperature alloy turbine blades according to claim 1, is characterized in that, in step (6), then the NbSi alloy powder thickness of evenly laying is 0.05～0.1mm.
The fast preparation method of 17. a kind of NbSi based ultra-high temperature alloy turbine blades according to claim 1, is characterized in that, in step (7), described refrigerating gas is argon gas.
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