CN107287480B - Blade of aviation engine aluminum matrix composite - Google Patents

Blade of aviation engine aluminum matrix composite Download PDF

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Publication number
CN107287480B
CN107287480B CN201610199991.XA CN201610199991A CN107287480B CN 107287480 B CN107287480 B CN 107287480B CN 201610199991 A CN201610199991 A CN 201610199991A CN 107287480 B CN107287480 B CN 107287480B
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blade
tenon
aviation engine
aluminum matrix
matrix composite
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CN107287480A (en
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杨超
周超羡
童辉
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AECC Commercial Aircraft Engine Co Ltd
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AECC Commercial Aircraft Engine Co Ltd
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/10—Alloys based on aluminium with zinc as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/02—Making non-ferrous alloys by melting
    • C22C1/026—Alloys based on aluminium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/02—Making non-ferrous alloys by melting
    • C22C1/03—Making non-ferrous alloys by melting using master alloys
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/06—Making non-ferrous alloys with the use of special agents for refining or deoxidising
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/10—Alloys containing non-metals
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
    • C22C32/0047—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with carbides, nitrides, borides or silicides as the main non-metallic constituents
    • C22C32/0073—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with carbides, nitrides, borides or silicides as the main non-metallic constituents only borides
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluid Mechanics (AREA)
  • Composite Materials (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Powder Metallurgy (AREA)

Abstract

The present invention relates to blade of aviation engine aluminum matrix composites.Specifically, the present invention provides a kind of aluminum matrix composite, by percentage to the quality, the aluminum matrix composite includes Zn:4.0~10.0%, Mg:0.8~3.0%, Cu:1.0~3.0%, Zr:0.05~0.5% and TiB2Ceramic particle: 1.0~10.0%, surplus Al.The clean interfaces of aluminum matrix composite matrix and ceramic particle of the invention, are well combined, and ceramic particle is evenly distributed, and there is excellent mechanical property, especially plastic elongation rate and the relatively existing in-situ authigenic aluminum matrix composite of elasticity modulus to improve a lot.

Description

Blade of aviation engine aluminum matrix composite
Technical field
The present invention relates to blade of aviation engine aluminum matrix composites.
Background technique
Aero-engine, especially big bypass ratio commercial aviation engine, in addition to high-performance, high reliability and long-life It is required that the requirement to low emission, low noise and low cost is higher and higher, and reduce by one of discharge and cost and reduction noise Important channel is exactly the weight for mitigating engine.
The operating temperature of fan blade is environment temperature in engine, hollow design using titanium alloy main at present or Polymer matrix composites preparation.But either hollow titanium alloy fan blade or the fan blade of polymer matrix composites are all There is a problem of that preparation difficulty is big, the period is long and at high cost.Booster stage first order stator blade and first order rotor in engine The operating temperature of blade is all at 150 DEG C hereinafter, be presently mainly to be manufactured using stainless steel and titanium alloy.
For three of the above engine blade, if manufacturing cycle is prepared or can reduced using aluminum matrix composite With cost (such as fan blade) or weight (such as booster stage first order stator blade and the rotor of components can be reduced Blade).But to realize that aluminum matrix composite replaces fan blade, booster stage first order stator blade and rotor leaf in engine Piece at present material, it is necessary to meet the performance requirement used first.
Traditional ceramic particle reinforced aluminium base composite material generallys use the outer plus ceramic particle in aluminum substrate and is prepared, That there is ceramic particles is poor with matrix infiltration for this aluminum matrix composite, and interfacial reaction is difficult to control, and ceramic particle is distributed not The defects of uniform, the severe weakness strengthening effect of ceramic particle affect the performance of aluminum matrix composite.Simultaneously using additional The problems such as ceramic particle prepares aluminum matrix composite there is complex technical process, higher cost, is unfavorable for promoting and applying.Separately Outside, the plasticity of the comprehensive mechanical property of the ceramic particle reinforced aluminium base composite material of existing in-situ authigenic, especially material is prolonged Rate is stretched, the requirement of engine associated vanes can't be fully met.
For example, CN 103725911A is related to a kind of preparation method of alumina particle reinforced aluminum matrix composites, this is compound Material is to be uniformly mixed using additional alumina ceramic grain into aluminium powder, then carries out hot pressing and hot-working is prepared. The problems such as poor in conjunction with basal body interface, mechanical property that there is ceramic particles in the composite material of this method preparation is not prominent, together When step of preparation process it is more, be unfavorable for promoting and applying.
CN 1718805A is related to aluminum based composite material enhanced by granules in situ.The reinforced phase particle of the composite material is six sides The size of shape or rectangle, reinforced phase particle is 20~300nm, and the mass fraction of reinforced phase is 0.1~40%.But this application institute It is difficult that the aluminum matrix composite enumerated has that plasticity deficiency, machine add.
There is still a need for the aluminum matrix composites of performance requirement needed for meeting for this field, can be used to prepare aero-engine leaf Piece.
Summary of the invention
First aspect present invention provides a kind of aluminum matrix composite, by percentage to the quality, the aluminum matrix composite packet Contain:
Zn:4.0~10.0%,
Mg:0.8~3.0%,
Cu:1.0~3.0%,
Zr:0.05~0.5%, and
TiB2Ceramic particle: 1.0~10.0%,
Surplus is Al.
In one or more embodiments, in the aluminum matrix composite, the content of Zn is 4.0~5.0%, 4.0~ 4.0~7.0%, 4.0~8.0%, 4.0~9.0%, 5.0~7.0%, 5.0~8.0%, 5.0~9.0%, 6.0 6.0% ,~ 7.0%, 6.0~8.0%, 6.0~10.0%, 5.0~6.5%, 5.5~7.0%, 5.8~6.3%, 6.5~7.5% or 6.8 ~7.3% etc..
In one or more embodiments, in the aluminum matrix composite, the content of Mg is 0.8~1.5%, 0.8~ 0.8~2.5%, 1.0~2.5%, 1.5~2.5%, 1.8~2.5%, 2.2~3.0%, 2.0~2.5%, 2.0 2.2% ,~ 2.3%, 2.2~2.5% or 2.2~2.8% etc..
In one or more embodiments, in the aluminum matrix composite, the content of Cu is 1.0~2.0%, 1.0~ 1.2~2.1%, 1.2~2.6%, 1.5~2.5%, 1.5~2.8%, 1.8~2.5%, 1.8~2.3%, 2.0 2.5% ,~ 3.0%, 2.0~2.5%, 2.0~2.6%, 2.1~2.6% or 1.9~2.3% etc..
In one or more embodiments, in the aluminum matrix composite, the content of Zr is 0.05~0.12%, 0.12~ 0.50%, 0.05~0.30%, 0.05~0.20%, 0.10~0.30%, 0.10~0.20%, 0.10~0.15%, 0.12 ~0.18%, 0.12~0.30%, 0.15~0.30%, 0.15~0.25% or 0.30~0.50% etc..
In one or more embodiments, in the aluminum matrix composite, TiB2Content be 1.0~2.0%, 1.0~ 5.0%, 1.0~7.0%, 2.0~5.0%, 2.0~7.0%, 2.0~10.0%, 5.0~7.0%, 5.0~10.0%, 7.0 ~10.0%, 3.0~7.0%, 3.0~5.5%, 4.0~6.0%, 4.5~5.5%, 6.5~7.5%, 1.8~2.3%, 4.8~5.3% or 6.8~7.3% etc..
In one or more embodiments, the aluminum matrix composite contains:
Zn:4.0~6.0%,
Mg:0.8~2.2%,
Cu:1.2~2.1%,
Zr:0.05~0.12%, and
TiB2Ceramic particle: 2.0~5.0%,
Surplus is Al.
In one or more embodiments, the aluminum matrix composite contains:
Zn:4.0~7.0%,
Mg:0.8~2.5%,
Cu:1.2~2.6%,
Zr:0.05~0.5%, and
TiB2Ceramic particle: 2.0~7.0%,
Surplus is Al.
In one or more embodiments, the aluminum matrix composite contains:
Zn:6.0~7.0%,
Mg:2.2~2.5%,
Cu:2.1~2.6%,
Zr:0.12~0.3%, and
TiB2Ceramic particle: 5.0~7.0%,
Surplus is Al.
In one or more embodiments, the aluminum matrix composite contains:
Zn:5.5~6.0%,
Mg:1.5~2.2%,
Cu:1.8~2.1%,
Zr:0.10~0.15%, and
TiB2Ceramic particle: 4.5~5.5%,
Surplus is Al.
In one or more embodiments, the aluminum matrix composite contains:
Zn:4.0~4.5%,
Mg:0.8~1.2%,
Cu:1.2~1.5%,
Zr:0.05~0.10%, and
TiB2Ceramic particle: 2.0~3.0%,
Surplus is Al.
In one or more embodiments, the aluminum matrix composite contains:
Zn:5.8~6.3%,
Mg:2.0~2.5%,
Cu:1.9~2.3%,
Zr:0.10~0.15%, and
TiB2Ceramic particle: 4.8~5.3%,
Surplus is Al.
In one or more embodiments, the aluminum matrix composite contains:
Zn:6.8~7.3%,
Mg:2.2~2.7%,
Cu:2.4~2.8%,
Zr:0.45~0.50%, and
TiB2Ceramic particle: 6.5~7.5%,
Surplus is Al.
In one or more embodiments, the aluminum matrix composite contains:
Zn:4.0~7.0%,
Mg:0.8~2.2%,
Cu:1.2~2.1%,
Zr:0.05~0.12%, and
TiB2Ceramic particle: 2.0~5.0%,
Surplus is Al.
In one or more embodiments, the TiB2The size of ceramic particle is in 300nm~1000nm, grain shape It is nearly ball-type or hexagon, rectangle and subsphaeroidal mixing.
Second aspect of the present invention provides a kind of method for preparing aluminum matrix composite as described herein, which comprises
(1) make KBF4And K2TiF6Mixture and the blend melt of Mg and Al following chemical reaction occurs:
3K2TiF6+6KBF4+10Al→3TiB2+K3AlF6+9KAlF4；
(2) after reaction, the byproduct of reaction K for swimming in bath surface is removed3AlF6And KAlF4, obtain reaction and produce Object；With
(3) Zn, made of Al-Cu alloy and Al-Zr alloy are added in the reaction product of step (2) acquisition, after abundant melting, Logical high-purity argon gas and carbon trichloride powder carry out refinery by de-gassing, and pour into slab, then carry out solid solution and aging strengthening model, thus Obtain the aluminum matrix composite.
In one or more embodiments, by the way that Mg to be added in the Al of fusing, the mixing for obtaining the Mg and Al is molten Body.
In one or more embodiments, by KBF4And K2TiF6Mixture be added in the blend melt, make described The chemical reaction occurs for salt mixture and the blend melt.
In one or more embodiments, solid solubility temperature is 466 DEG C~480 DEG C, and soaking time is 1h~4h.
It in one or more embodiments, is quenched after solution treatment, hardening media is water, and casting is made after quenching certainly So it is cooled to room temperature.
In one or more embodiments, artificial aging temperature is 117~123 DEG C, and soaking time is 15~20h, empty It is cold.
In one or more embodiments, the solid solution meets the requirement of AMS2772 with aging strengthening model.
Third aspect present invention provides a kind of blade of aviation engine, and the blade uses aluminum-base composite of the present invention Material is prepared.
In one or more embodiments, it is quiet that the blade of aviation engine is selected from fan blade, the booster stage first order Blades and rotor blade.
In one or more embodiments, the fan blade has tenon position, as tenon position and blade portion The joining section of position stretches root segment and blade.
In one or more embodiments, tenon position uses arc-shaped or linear, and wherein the axial direction of tenon is long Degree L be 50~500mm, tenon apex angle Rs be 30~120 °, tenon base angle Rd be 30~120 °, tenon T wire length Lt be 20~ 60mm, tenon width Lc are 20~70mm, and tenon T line height Hd is 5~40mm, and tenon contact surface height Hg is 5~40mm.
In one or more embodiments, stretch root segment using smooth surface connect, the radius of corner that smoothly transits be 0.5~ 10mm。
In one or more embodiments, blade has the section of high aspect ratio air foil shape, including front and rear edge, wherein Front and rear edge radius is between 0.1~3mm, and for the torsional angle of blade bottom aerofoil profile and blade tip aerofoil profile between 5 °~90 °, blade tip is axially long L1 is spent between 50~300mm.
In one or more embodiments, the booster stage first order stator blade has listrium and blade.
In one or more embodiments, L2 and L3 are between 10~500mm for listrium length, and form pipes' analysis.
In one or more embodiments, blade has the section of air foil shape, including front and rear edge, wherein front and rear edge half Diameter is between 0.1~3mm, and the torsional angle of blade bottom aerofoil profile and blade tip aerofoil profile is between 1 °~90 °, and blade tip axial length L 1 is 10 Between~300mm, blade height H1 is between 10~500mm.
In one or more embodiments, the booster stage first order rotor blade has tenon position, as tenon The listrium and blade of the joining section at position and blade position.
In one or more embodiments, tenon position uses circumferential or axial linear, wherein the axial direction of tenon For length L3 between 10~200mm, tenon angle R1 is between 30~150 °.
In one or more embodiments, joining section of the listrium as tenon position and blade position, and form runner Face.
In one or more embodiments, blade has the section of air foil shape, including front and rear edge, wherein front and rear edge half Diameter is between 0.1~3mm, and the torsional angle of blade bottom aerofoil profile and blade tip aerofoil profile is between 1 °~90 °, and blade tip axial length L 1 is 10 Between~300mm, blade height H1 is between 10~500mm, and listrium axial length L 2 is between 10~400mm.
Fourth aspect present invention also provides aluminum matrix composite of the present invention in preparing blade of aviation engine Purposes.
In one or more embodiments, it is quiet that the blade of aviation engine is selected from fan blade, the booster stage first order Blades and rotor blade.
Detailed description of the invention
Fig. 1: TiB2The high resolution transmission electron microscopy photo at interface between ceramic particle and 7050 matrixes.
Fig. 2: aluminum matrix composite fan blade.
Fig. 3: aerofoil profile schematic diagram.
Fig. 4: tenon schematic diagram.
Fig. 5: aluminum matrix composite booster stage stator blade.
Fig. 6: aerofoil profile schematic diagram.
Fig. 7: listrium schematic diagram.
Fig. 8: aluminum matrix composite booster stage rotor blade.
Fig. 9: aerofoil profile schematic diagram.
Figure 10: tenon schematic diagram.
Specific embodiment
The present invention provides a kind of aluminum matrix composite, and by percentage to the quality, the aluminum matrix composite includes:
Zn:4.0~10.0%,
Mg:0.8~3.0%,
Cu:1.0~3.0%,
Zr:0.05~0.5%, and
TiB2Ceramic particle: 1.0~10.0%,
Surplus is Al.
In aluminum matrix composite of the invention, the content of Zn can for 4.0~5.0%, 4.0~6.0%, 4.0~ 4.0~8.0%, 4.0~9.0%, 5.0~7.0%, 5.0~8.0%, 5.0~9.0%, 6.0~7.0%, 6.0 7.0% ,~ 8.0%, 6.0~10.0%, 5.0~6.5%, 5.5~7.0%, 5.8~6.3%, 6.5~7.5% or 6.8~7.3% etc..
The content of Mg can for 0.8~1.5%, 0.8~2.2%, 0.8~2.5%, 1.0~2.5%, 1.5~2.5%, 1.8~2.5%, 2.2~3.0%, 2.0~2.5%, 2.0~2.3%, 2.2~2.5% or 2.2~2.8% etc..
The content of Cu can for 1.0~2.0%, 1.0~2.5%, 1.2~2.1%, 1.2~2.6%, 1.5~2.5%, 1.5~2.8%, 1.8~2.5%, 1.8~2.3%, 2.0~3.0%, 2.0~2.5%, 2.0~2.6%, 2.1~2.6% Or 1.9~2.3% etc..
The content of Zr can for 0.05~0.12%, 0.12~0.50%, 0.05~0.30%, 0.05~0.20%, 0.10~0.30%, 0.10~0.20%, 0.10~0.15%, 0.12~0.18%, 0.12~0.30%, 0.15~ 0.30%, 0.15~0.25% or 0.30~0.50% etc..
TiB2Content can for 1.0~2.0%, 1.0~5.0%, 1.0~7.0%, 2.0~5.0%, 2.0~ 7.0%, 2.0~10.0%, 5.0~7.0%, 5.0~10.0%, 7.0~10.0%, 3.0~7.0%, 3.0~5.5%, 4.0~6.0%, 4.5~5.5%, 6.5~7.5%, 1.8~2.3%, 4.8~5.3% or 6.8~7.3% etc..
It should be understood that each mass percent range of above-mentioned each ingredient can be freely combined.Thus, for example, in one or more In embodiment, aluminum matrix composite of the present invention contains:
Zn:4.0~6.0%,
Mg:0.8~2.2%,
Cu:1.2~2.1%,
Zr:0.05~0.12%, and
TiB2Ceramic particle: 2.0~5.0%,
Surplus is Al.
In other embodiments, aluminum matrix composite of the present invention contains:
Zn:4.0~7.0%,
Mg:0.8~2.5%,
Cu:1.2~2.6%,
Zr:0.05~0.5%, and
TiB2Ceramic particle: 2.0~7.0%,
Surplus is Al.
In other embodiments, aluminum matrix composite of the present invention contains:
Zn:6.0~7.0%,
Mg:2.2~2.5%,
Cu:2.1~2.6%,
Zr:0.12~0.3%, and
TiB2Ceramic particle: 5.0~7.0%,
Surplus is Al.
In one or more embodiments, aluminum matrix composite of the present invention contains:
Zn:5.5~6.0%,
Mg:1.5~2.2%,
Cu:1.8~2.1%,
Zr:0.10~0.15%, and
TiB2Ceramic particle: 4.5~5.5%,
Surplus is Al.
In other embodiments, aluminum matrix composite of the present invention contains:
Zn:4.0~4.5%,
Mg:0.8~1.2%,
Cu:1.2~1.5%,
Zr:0.05~0.10%, and
TiB2Ceramic particle: 2.0~3.0%,
Surplus is Al.
In certain embodiments, aluminum matrix composite of the present invention contains:
Zn:5.8~6.3%,
Mg:2.0~2.5%,
Cu:1.9~2.3%,
Zr:0.10~0.15%, and
TiB2Ceramic particle: 4.8~5.3%,
Surplus is Al.
In other embodiments, aluminum matrix composite of the present invention contains:
Zn:6.8~7.3%,
Mg:2.2~2.7%,
Cu:2.4~2.8%,
Zr:0.45~0.50%, and
TiB2Ceramic particle: 6.5~7.5%,
Surplus is Al.
In certain embodiments, aluminum matrix composite of the present invention contains:
Zn:4.0~7.0%,
Mg:0.8~2.2%,
Cu:1.2~2.1%,
Zr:0.05~0.12%, and
TiB2Ceramic particle: 2.0~5.0%,
Surplus is Al.
It is suitable for the invention TiB2The size of ceramic particle preferably in 300nm~1000nm, for example, 400~ Within the scope of 1000nm, or within the scope of 500~1000nm.
Preferably, it is suitable for the invention TiB2The grain shape of ceramic particle is nearly ball-type or hexagon, length Rectangular and subsphaeroidal any mixture.
Preferably, in aluminum matrix composite of the invention, TiB2Ceramic particle dispersion is distributed in the base, TiB2Ceramics Particle is clean with basal body interface.
Method comprising the following steps preparation can be used in aluminum matrix composite of the invention:
(1) make KBF4And K2TiF6Mixture and the blend melt of Mg and Al following chemical reaction occurs:
3K2TiF6+6KBF4+10Al→3TiB2+K3AlF6+9KAlF4；
(2) after reaction, the byproduct of reaction K for swimming in bath surface is removed3AlF6And KAlF4, obtain reaction and produce Object；With
(3) Zn, made of Al-Cu alloy, Al-Zr alloy are added in the reaction product of step (2) acquisition, after abundant melting, Logical high-purity argon gas and carbon trichloride powder carry out refinery by de-gassing, and pour into slab, then carry out solid solution and aging strengthening model, thus Obtain the aluminum matrix composite.
In general, obtaining the blend melt of the Mg and Al by the way that Mg to be added in the Al of fusing.It is melted in general, Mg accounts for mixing The mass ratio of body is 1.0~3.3%.
It then can be by KBF4And K2TiF6Mixture be added in the blend melt, make the salt mixture and described mixed It closes melt and the chemical reaction occurs.KBF4And K2TiF6Dosage should be sufficient to make TiB generated2Amount meet this paper institute The content requirement stated.
In step (3), in made of Al-Cu alloy, the mass ratio of Cu can within the scope of 40~60%, for example, about 50%.Al- In Zr alloy, the mass ratio of Zr can be within the scope of 5~15%, such as within the scope of about 8~12%, for example, about 10%.
In general, the solid solution and aging strengthening model in step (3) should meet the requirement of AMS2772.For example, solid solubility temperature is usual It is 466 DEG C~480 DEG C, such as 466~475 DEG C, 470~475 DEG C or 473~480 DEG C, soaking time is usually 1h~4h, such as 1h~3h, 2h~4h, 2h~3h etc..It is quenched after solution treatment, hardening media is water, naturally cools to casting after quenching Room temperature.The temperature of artificial aging is usually 117~123 DEG C, such as 117~121 DEG C, 120~123 DEG C, soaking time are usually 15~20h, such as 15~18h, 16~20h, it is air-cooled.
Herein, in the base, Zn and Mg forms main hardening constituent MgZn in the alloy2, MgZn2Mutually in the alloy Solubility with temperature reduces and sharply declines, disperse educt, has very strong age hardening capability.A certain number of Cu are added, The mechanical property of alloy can be improved and improve corrosion stability.Zr, which is added, can increase intensity of the alloy under new as-quenched and artificial Timeliness effect, while its anti-stress corrosion performance can also be improved.
In ingot casting preparation process, TiB2Ceramic particle can hinder growing up for crystal grain, in extruding and heat treatment process, Inhibiting effect is played to the Recovery and recrystallization of matrix.TiB2Ceramic particle dispersion is distributed in the base, can effectively be hindered The movement of dislocation.Due to the thermal expansion coefficient and TiB of matrix2There are larger differences for the thermal expansion coefficient of ceramic particle, therefore In preparation or heat treatment process, high density dislocation is easily formed in the base, generates invigoration effect.
Therefore, the present invention overcomes ceramic particle is poor in conjunction with basal body interface in addition aluminum matrix composite outside tradition, material The fatigue behaviour of material is poor, machines difficult technological difficulties；The boundary of aluminum matrix composite matrix and ceramic particle in the present invention Face is clean, is well combined, and ceramic particle is evenly distributed, as shown in Figure 1.The aluminum matrix composite that the present invention is prepared has excellent The relatively existing in-situ authigenic aluminum matrix composite of different mechanical property, especially plastic elongation rate and elasticity modulus has to be mentioned greatly very much It is high.Specifically, the yield strength of aluminum matrix composite of the invention is up to 550~700MPa, plastic elongation rate at the same time Up to 6% or more, endurance limit under rotating bending is up to 300MPa or more, it is sufficient to overcome the resultant force of existing aluminum matrix composite Learn the problem that performance is not able to satisfy the use demands of blades such as aero-engine booster stage first order stator blade.Moreover, this hair The preparation process of bright aluminum matrix composite is simple, at low cost, is suitble to large-scale industrialization promotion.
For the engine blade part for obtaining aluminum matrix composite, can will be answered by ceramic particle reinforced aluminium base of the invention Pressurization slab or the direct machine addition blade of bar stock made of condensation material can also first pass through die forging/hot forging and form blade forging, Numerical control processing forming is carried out again.
Specifically, aluminum matrix composite prepared in accordance with the present invention can prepare fan blade as in Figure 2-4.It should Fan blade has tenon position, stretches root segment and blade as the joining section at tenon position and blade position.It adopts at tenon position With arc-shaped or linear, wherein the axial length L of tenon is 50~500mm, preferably 200~500mm；Tenon apex angle Rs is 30~120 °, preferably 60~100 °；Tenon base angle Rd is 30~120 °, preferably 60~100 °；Tenon T wire length Lt be 20~ 60mm, preferably 25~60mm；Tenon width Lc is 20~70mm, preferably 25~70mm；Tenon T line height Hd is 5~40mm, excellent Select 10~40mm；Tenon contact surface height Hg is 5~30mm, preferably 10~30mm.Root segment is stretched as tenon position and blade portion The joining section of position, is connected using smooth curved surface, and rounding off radius of corner is 0.5~10mm, preferably 2~10mm.Blade has The section of high aspect ratio air foil shape, including front and rear edge；Wherein front and rear edge radius is between 0.1~3mm, blade bottom aerofoil profile with The torsional angle of blade tip aerofoil profile is between 5 °~90 °, preferably between 15~90 °；Blade tip axial length L 1 between 50~400mm, It is preferred that between 150~400mm.
Aluminum matrix composite prepared in accordance with the present invention can prepare booster stage first order stator leaf as illustrated in figs. 5-7 Piece.The booster stage first order stator blade has listrium and blade.L2 and L3 are between 10~500mm for listrium length, preferably exist Between 10~100mm, and form pipes' analysis.Blade has the section of air foil shape, including front and rear edge；Wherein front and rear edge radius exists Between 0.1~3mm, the torsional angle of blade bottom aerofoil profile and blade tip aerofoil profile is between 1 °~90 °, preferably between 1 °~30 °, blade tip Axial length L 1 is between 10~300mm, and preferably between 10~100mm, blade height H1 is between 10~500mm, preferably Between 50~150mm.
Aluminum matrix composite prepared in accordance with the present invention can prepare booster stage first order rotor leaf as seen in figs. 8-10 Piece.The booster stage first order rotor blade has tenon position, as the listrium at tenon position and the joining section at blade position, And blade.Tenon position is using circumferential or axial linear, and wherein the axial length L 3 of tenon is excellent between 10~200mm It is selected between 20~50mm；Tenon angle R1 is between 30 °~150 °, preferably between 60 °~100 °.Listrium is as tenon portion The joining section of position and blade position, and form pipes' analysis.Blade has the section of air foil shape, including front and rear edge；Wherein front and back Edge radius is between 0.1~3mm, and the torsional angle of blade bottom aerofoil profile and blade tip aerofoil profile is between 1 °~90 °, preferably at 15 °~90 ° Between, blade tip axial length L 1 is between 10~300mm, and preferably between 10~150mm, blade height H1 is in 10~500mm Between, preferably between 50~150mm, listrium axial length L 2 is between 10~400mm, preferably between 30~170mm.
The present invention will be hereafter illustrated in a manner of specific embodiment.It should be understood that these embodiments are only illustrative, and Do not limit the present invention.Used method and process conditions in embodiment, unless otherwise stated, being the side of this field routine Method and process conditions.Moreover, it will be understood that herein, the terms such as " containing ", " comprising " also include " by ... form ", " by ... constitute ".
Embodiment 1
Component and its mass percent of the invention are as follows: Zn:4%, Mg:0.8%, Cu:1.2%, Zr:0.05%, TiB2: 2%, surplus Al.
Preparation process is as follows: commercial-purity aluminium being added in crucible, melts aluminium ingot, technical pure Mg is pressed into, by KFB4、 K2TiF6Then uniformly mixing salt-mixture is added in melt, carry out mechanical stirring, makes salt-mixture that hair occur with melt and answers, reacts After, it takes out hair and answers by-product, technical pure Zn, Al-Cu, Al-Zr intermediate alloy is then added, refinery by de-gassing pours into Then slab is squeezed into bar stock by slab, bar stock is through following solid solution and aging strengthening model: solid solubility temperature is 466 DEG C~480 DEG C, soaking time is 1h~4h, and hardening media is water (room temperature), and 120 DEG C of artificial aging temperature, soaking time is 15~20h, empty It is cold.Heat treatment process should meet the requirement of AMS2772.
The aluminum matrix composite prepared through above procedure, TiB2The size of particle is in 300~1000nm, grain shape master It to be nearly ball-type or hexagon, rectangle and subsphaeroidal mixing, particle dispersion is distributed in the base, TiB2Particle and matrix Clean interfaces, no interfacial reaction, are well combined.
The average mechanical property of material: σ is measured according to ASTM B 557M and ASTM E 111b=630MPa, σ0.2= 560MPa, δ=10%, E=70GPa.
Embodiment 2
Component and its mass percent of the invention are as follows: Zn:6%, Mg:2.2%, Cu:2.1%, Zr:0.12%, TiB2: 5%, surplus Al.
Preparation process is as follows: commercial-purity aluminium being added in crucible, melts aluminium ingot, technical pure Mg is pressed into, by KFB4、 K2TiF6Then uniformly mixing salt-mixture is added in melt, carry out mechanical stirring, makes salt-mixture that hair occur with melt and answers, reacts After, it takes out hair and answers by-product, technical pure Zn, Al-Cu, Al-Zr intermediate alloy is then added, refinery by de-gassing pours into Then slab is squeezed into bar stock by slab, bar stock is through following solid solution and aging strengthening model: solid solubility temperature is 466 DEG C~480 DEG C, Soaking time is 1h~4h, and hardening media is water (room temperature), and 120 DEG C of artificial aging temperature, soaking time is 15~20h, air-cooled. Heat treatment process should meet the requirement of AMS2772.
The aluminum matrix composite prepared through above procedure, TiB2The size of particle is in 300~1000nm, grain shape master Will be to be subsphaeroidal, particle dispersion is distributed in the base, TiB2Particle is clean with basal body interface, and no interfacial reaction is well combined.Knot Fruit can be found in Fig. 1.
The average mechanical property of material: σ is measured according to ASTM B 557M and ASTM E 111b=700MPa, σ0.2= 630MPa, δ=8%, E=75GPa.
Embodiment 3
Component and its mass percent of the invention are as follows: Zn:7%, Mg:2.5%, Cu:2.6%, Zr:0.5%, TiB2: 8%, surplus Al.
Preparation process is as follows: commercial-purity aluminium being added in crucible, melts aluminium ingot, technical pure Mg is pressed into, by KFB4、 K2TiF6Then uniformly mixing salt-mixture is added in melt, carry out mechanical stirring, makes salt-mixture that hair occur with melt and answers, reacts After, it takes out hair and answers by-product, technical pure Zn, Al-Cu, Al-Zr intermediate alloy is then added, refinery by de-gassing pours into Then slab is squeezed into bar stock by slab, bar stock is through following solid solution and aging strengthening model: solid solubility temperature is 466 DEG C~480 DEG C, Soaking time is 1h~4h, and hardening media is water (room temperature), and 120 DEG C of artificial aging temperature, soaking time is 15~20h, air-cooled. Heat treatment process should meet the requirement of AMS2772.
The aluminum matrix composite prepared through above procedure, TiB2The size of particle is in 300~1000nm, grain shape master It to be nearly ball-type, particle dispersion is distributed in the base, TiB2Particle is clean with basal body interface, and no interfacial reaction is well combined.
The average mechanical property of material: σ is measured according to ASTM B 557M and ASTM E 111b=790MPa, σ0.2= 680MPa, δ=6%, E=85GPa.
Embodiment 4
Aluminum matrix composite prepared in accordance with the present invention can prepare fan blade as in Figure 2-4.
Tenon position uses arc-shaped or linear, and wherein the axial length L of tenon is 50~500mm, tenon apex angle Rs is 30~120 °, and tenon base angle Rd is 30~120 °, and tenon T wire length Lt is 20~60mm, and tenon width Lc is 20~70mm, Tenon T line height Hd is 5~40mm, and tenon contact surface height Hg is 5~40mm.
Joining section of the root segment as tenon position and blade position is stretched, is connected using smooth surface, smoothly transit fillet half Diameter is 0.5~10mm.
Blade has the section of high aspect ratio air foil shape, including front and rear edge；Wherein front and rear edge radius 0.1~3mm it Between, the torsional angle of blade bottom aerofoil profile and blade tip aerofoil profile is between 5 °~90 °, and blade tip axial length L 1 is between 50~300mm.
Embodiment 5
Aluminum matrix composite prepared in accordance with the present invention can prepare booster stage first order stator leaf as illustrated in figs. 5-7 Piece.
L2 and L3 are between 10~500mm for listrium length, and form pipes' analysis.
Blade has the section of air foil shape, including front and rear edge；Wherein front and rear edge radius is between 0.1~3mm, blade bottom The torsional angle of portion's aerofoil profile and blade tip aerofoil profile is between 1 °~90 °, and blade tip axial length L 1 is between 10~300mm, blade height H1 Between 10~500mm.
Embodiment 6
Aluminum matrix composite prepared in accordance with the present invention can prepare booster stage first order rotor leaf as seen in figs. 8-10 Piece.
Tenon position is using circumferential or axial linear, and wherein the axial length L 3 of tenon is between 10~200mm, tenon Head angle R1 is between 30~150 °.
Joining section of the listrium as tenon position and blade position, and form pipes' analysis.
Blade has the section of air foil shape, including front and rear edge；Wherein front and rear edge radius is between 0.1~3mm, blade bottom The torsional angle of portion's aerofoil profile and blade tip aerofoil profile is between 1 °~90 °, and blade tip axial length L 1 is between 10~300mm, blade height H1 Between 10~500mm, listrium axial length L 2 is between 10~400mm.

Claims (29)

1. a kind of blade of aviation engine, which is characterized in that the blade is prepared using aluminum matrix composite；
The blade of aviation engine is selected from fan blade, booster stage first order stator blade and rotor blade；
In the fan blade,
Tenon position uses arc-shaped or linear, and wherein the axial length L of tenon is 50~500mm；Tenon apex angle Rs is 30~120 °；Tenon base angle Rd is 30~120 °；Tenon T wire length Lt is 20~60mm；Tenon width Lc is 20~70mm；Tenon T line height Hd is 5~40mm；Tenon contact surface height Hg is 5~30mm；
Joining section of the root segment as tenon position and blade position is stretched, is connected using smooth curved surface, rounding off radius of corner is 0.5~10mm；
Blade has the section of high aspect ratio air foil shape, including front and rear edge；Wherein front and rear edge radius is between 0.1~3mm, leaf The torsional angle of body bottom aerofoil profile and blade tip aerofoil profile is between 5 °~90 °；Blade tip axial length L 1 is between 50~400mm；
In the booster stage first order stator blade,
L2 and L3 are between 10~500mm for listrium length, and form pipes' analysis；
Blade has the section of air foil shape, including front and rear edge；Wherein front and rear edge radius is between 0.1~3mm, the blade bottom wing The torsional angle of type and blade tip aerofoil profile is between 1 °~90 °, and blade tip axial length L 1 is between 10~300mm, and blade height H1 is 10 Between~500mm；
In the booster stage first order rotor blade,
Wherein the axial length L 3 of tenon is between 10~200mm；Tenon angle R1 is between 30 °~150 °；
Joining section of the listrium as tenon position and blade position, and form pipes' analysis；
Blade has the section of air foil shape, including front and rear edge；Wherein front and rear edge radius is between 0.1~3mm, the blade bottom wing The torsional angle of type and blade tip aerofoil profile is between 1 °~90 °, and blade tip axial length L 1 is between 10~300mm, and blade height H1 is 10 Between~500mm, listrium axial length L 2 is between 10~400mm；
The aluminum matrix composite includes:
Zn:4.0~10.0%,
Mg:0.8~3.0%,
Cu:1.0~3.0%,
Zr:0.05~0.5%, and
TiB2Ceramic particle: 1.0~10.0%, the TiB2The size of ceramic particle is in 300nm~1000nm, grain shape Nearly ball-type or hexagon, rectangle and subsphaeroidal mixture,
Surplus is Al.
2. blade of aviation engine as described in claim 1, which is characterized in that the aluminum matrix composite contains:
Zn:4.0~6.0%,
Mg:0.8~2.2%,
Cu:1.2~2.1%,
Zr:0.05~0.12%, and
TiB2Ceramic particle: 2.0~5.0%,
Surplus is Al.
3. blade of aviation engine as described in claim 1, which is characterized in that the aluminum matrix composite contains:
Zn:4.0~7.0%,
Mg:0.8~2.5%,
Cu:1.2~2.6%,
Zr:0.05~0.5%, and
TiB2Ceramic particle: 2.0~7.0%,
Surplus is Al.
4. blade of aviation engine as described in claim 1, which is characterized in that the aluminum matrix composite contains:
Zn:6.0~7.0%,
Mg:2.2~2.5%,
Cu:2.1~2.6%,
Zr:0.12~0.3%, and
TiB2Ceramic particle: 5.0~7.0%,
Surplus is Al.
5. blade of aviation engine as described in claim 1, which is characterized in that the aluminum matrix composite contains:
Zn:5.5~6.0%,
Mg:1.5~2.2%,
Cu:1.8~2.1%,
Zr:0.10~0.15%, and
TiB2Ceramic particle: 4.5~5.5%,
Surplus is Al.
6. blade of aviation engine as described in claim 1, which is characterized in that the aluminum matrix composite contains:
Zn:4.0~4.5%,
Mg:0.8~1.2%,
Cu:1.2~1.5%,
Zr:0.05~0.10%, and
TiB2Ceramic particle: 2.0~3.0%,
Surplus is Al.
7. blade of aviation engine as described in claim 1, which is characterized in that the aluminum matrix composite contains:
Zn:5.8~6.3%,
Mg:2.0~2.5%,
Cu:1.9~2.3%,
Zr:0.10~0.15%, and
TiB2Ceramic particle: 4.8~5.3%,
Surplus is Al.
8. blade of aviation engine as described in claim 1, which is characterized in that the aluminum matrix composite contains:
Zn:6.8~7.3%,
Mg:2.2~2.7%,
Cu:2.4~2.8%,
Zr:0.45~0.50%, and
TiB2Ceramic particle: 6.5~7.5%,
Surplus is Al.
9. blade of aviation engine as described in claim 1, which is characterized in that the aluminum matrix composite contains:
Zn:4.0~7.0%,
Mg:0.8~2.2%,
Cu:1.2~2.1%,
Zr:0.05~0.12%, and
TiB2Ceramic particle: 2.0~5.0%,
Surplus is Al.
10. blade of aviation engine as described in claim 1, which is characterized in that in the fan blade, the axial direction of tenon is long Degree L is 200~500mm.
11. blade of aviation engine as described in claim 1, which is characterized in that in the fan blade, tenon apex angle Rs is 60~100 °.
12. blade of aviation engine as described in claim 1, which is characterized in that in the fan blade, tenon base angle Rd is 60~100 °.
13. blade of aviation engine as described in claim 1, which is characterized in that in the fan blade, tenon T wire length Lt For 25~60mm.
14. blade of aviation engine as described in claim 1, which is characterized in that in the fan blade, tenon width Lc is 25~70mm.
15. blade of aviation engine as described in claim 1, which is characterized in that in the fan blade, tenon T line height Hd is 10~40mm.
16. blade of aviation engine as described in claim 1, which is characterized in that in the fan blade, tenon contact surface is high Degree Hg is 10~30mm.
17. blade of aviation engine as described in claim 1, which is characterized in that in the fan blade, rounding off fillet Radius is 2~10mm.
18. blade of aviation engine as described in claim 1, which is characterized in that in the fan blade, blade bottom aerofoil profile Torsional angle with blade tip aerofoil profile is between 15~90 °.
19. blade of aviation engine as described in claim 1, which is characterized in that in the fan blade, blade tip axial length L1 is between 150~400mm.
20. blade of aviation engine as described in claim 1, which is characterized in that in the booster stage first order stator blade, L2 and L3 are between 10~100mm for listrium length, and form pipes' analysis.
21. blade of aviation engine as described in claim 1, which is characterized in that in the booster stage first order stator blade, The torsional angle of blade bottom aerofoil profile and blade tip aerofoil profile is between 1 °~30 °.
22. blade of aviation engine as described in claim 1, which is characterized in that in the booster stage first order stator blade, Blade tip axial length L 1 is between 10~100mm.
23. blade of aviation engine as described in claim 1, which is characterized in that in the booster stage first order stator blade, Blade height H1 is between 50~150mm.
24. blade of aviation engine as described in claim 1, which is characterized in that in the booster stage first order rotor blade, Wherein the axial length L 3 of tenon is between 20~50mm.
25. blade of aviation engine as described in claim 1, which is characterized in that in the booster stage first order rotor blade, Tenon angle R1 is between 60 °~100 °.
26. blade of aviation engine as described in claim 1, which is characterized in that in the booster stage first order rotor blade, The torsional angle of blade bottom aerofoil profile and blade tip aerofoil profile is between 15 °~90 °.
27. blade of aviation engine as described in claim 1, which is characterized in that in the booster stage first order rotor blade, Blade tip axial length L 1 is between 10~150mm.
28. blade of aviation engine as described in claim 1, which is characterized in that in the booster stage first order rotor blade, Blade height H1 is between 50~150mm.
29. blade of aviation engine as described in claim 1, which is characterized in that in the booster stage first order rotor blade, Listrium axial length L 2 is between 30~170mm.
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