EP4071258B1 - Manufacturing method of aircraft member - Google Patents
Manufacturing method of aircraft member Download PDFInfo
- Publication number
- EP4071258B1 EP4071258B1 EP21209865.1A EP21209865A EP4071258B1 EP 4071258 B1 EP4071258 B1 EP 4071258B1 EP 21209865 A EP21209865 A EP 21209865A EP 4071258 B1 EP4071258 B1 EP 4071258B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- extrusion
- equal
- atom
- billet
- temperature
- 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.)
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- 238000004519 manufacturing process Methods 0.000 title claims description 24
- 238000001125 extrusion Methods 0.000 claims description 105
- 229910052782 aluminium Inorganic materials 0.000 claims description 42
- 229910052749 magnesium Inorganic materials 0.000 claims description 35
- 229910045601 alloy Inorganic materials 0.000 claims description 29
- 239000000956 alloy Substances 0.000 claims description 29
- 150000001875 compounds Chemical class 0.000 claims description 22
- 238000012545 processing Methods 0.000 claims description 22
- 238000002844 melting Methods 0.000 claims description 15
- 230000008018 melting Effects 0.000 claims description 15
- 239000012535 impurity Substances 0.000 claims description 3
- 239000011777 magnesium Substances 0.000 description 36
- 239000000463 material Substances 0.000 description 31
- 238000005260 corrosion Methods 0.000 description 21
- 229910000861 Mg alloy Inorganic materials 0.000 description 19
- 230000007797 corrosion Effects 0.000 description 19
- 229910000838 Al alloy Inorganic materials 0.000 description 8
- 238000012360 testing method Methods 0.000 description 7
- 229910008455 Si—Ca Inorganic materials 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 238000005259 measurement Methods 0.000 description 4
- 238000005266 casting Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 229910014458 Ca-Si Inorganic materials 0.000 description 2
- FAPWRFPIFSIZLT-UHFFFAOYSA-M Sodium chloride Chemical compound [Na+].[Cl-] FAPWRFPIFSIZLT-UHFFFAOYSA-M 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 239000006185 dispersion Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 239000003507 refrigerant Substances 0.000 description 2
- UTPYTEWRMXITIN-YDWXAUTNSA-N 1-methyl-3-[(e)-[(3e)-3-(methylcarbamothioylhydrazinylidene)butan-2-ylidene]amino]thiourea Chemical compound CNC(=S)N\N=C(/C)\C(\C)=N\NC(=S)NC UTPYTEWRMXITIN-YDWXAUTNSA-N 0.000 description 1
- 238000007744 chromate conversion coating Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 229910000765 intermetallic Inorganic materials 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000010587 phase diagram Methods 0.000 description 1
- 239000002244 precipitate Substances 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 150000003839 salts Chemical class 0.000 description 1
- 239000011780 sodium chloride Substances 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C23/00—Alloys based on magnesium
- C22C23/02—Alloys based on magnesium with aluminium as the next major constituent
-
- 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
- C22F1/06—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of magnesium or alloys based thereon
Definitions
- the present disclosure relates to a manufacturing method of an aircraft member, in particular, a manufacturing method of a secondary structure member of an aircraft.
- the magnesium alloy needs substantially the same manufacturing cost as an aluminum alloy and has specific strength greater than or equal to the aluminum alloy (see Japanese Patent Laid-Open No. 2008-536013 , Japanese Patent Laid-Open No. 2010-209452 ).
- a magnesium alloy is an active metal and thus requires anti-corrosion treatment.
- Japanese Patent Laid-Open No. 2008-536013 a non-chromate conversion coating is formed on the surface of the magnesium alloy to improve corrosion resistance.
- Japanese Patent Laid-Open No. 2010-209452 discloses a magnesium alloy member having high corrosion resistance that does not require anti-corrosion treatment by defining the number and the size of fine precipitates containing both Mg and Al that are present in a surface layer region.
- Japanese Patent Application Laid-Open No. 2008-536013 and Japanese Patent Application Laid-Open No. 2010-209452 are examples of the related art.
- a material applied to an aircraft member is required to balance strength (tensile strength) and ductility (elongation).
- Magnesium alloys have lower strength than aluminum alloys. Thus, it is required to improve the strength, but the strength of magnesium alloy is in a trade-off relationship with ductility, and it is difficult to balance the strength and the ductility.
- a magnesium alloy member is manufactured by using a billet casted by using an ingot made of a magnesium alloy.
- US2016369378 also discloses a magnesium alloy used in aircraft applications which is extruded and comprises a dispersion of (Mg,Al)2Ca.
- the crystal grain diameter and the microstructure of a magnesium alloy are varied depending on processing conditions, and then the strength and the ductility of magnesium alloy are varied.
- Fig. 5 illustrates a metallographic structure photograph of an Mg-Al-Ca-Si based alloy as an example. As illustrated in Fig. 5 , ⁇ -Mg (Al, Ca being dissolved into a solid solution), an Mg-Si-Ca compound, an (Mg, Al) 2 Ca compound (C36), and the like are included in the metallographic structure.
- Fig. 6 illustrates a metallographic structure photograph of an Mg-Si-Ca compound.
- Fig. 7 illustrates a metallographic structure photograph of an (Mg, Al) 2 Ca compound.
- the present disclosure has been made in view of the above problems and intends to provide a manufacturing method that enables stable acquisition of a magnesium alloy member having both good strength and ductility regardless of a billet size.
- the manufacturing method of an aircraft member of the present disclosure employs the following measures and as given in the claims.
- the present disclosure provides a manufacturing method of an aircraft member to perform extrusion processing by using an Mg-Al-Ca based alloy containing an (Mg, Al) 2 Ca compound
- the manufacturing method of an aircraft member includes: selecting a billet of an Mg-Al-Ca based alloy containing Al: greater than or equal to 6 atom% and less than or equal to 8 atom% and Ca: greater than or equal to 3 atom% and less than or equal to 4 atom%, optionally Mn: less than or equal to 0.3 atom% and optionally Si: less than or equal to 0.1 atom% with respect to the whole amount, the remaining part being Mg and unavoidable impurities; and extruding the billet under a condition where a temperature of the billet is maintained to be lower than a melting temperature of the (Mg, Al) 2 Ca compound, wherein the billet contains the (Mg, Al) 2 Ca compound by greater than or equal to 10 volume% and less than or equal to 35 volume%, the (Mg, Al) 2 Ca compound
- a billet whose Al content and Ca content are within the above range is used, and extrusion processing conditions are optimized, so that an aircraft member having both good strength and ductility can be obtained more stably than in the conventional methods. Further, according to the manufacturing method of the present disclosure, an aircraft member that meets required incombustibility can be obtained.
- a manufacturing method according to the present disclosure is suitable for manufacturing a secondary structure member for an aircraft.
- the secondary structure member is a member installed in a primary structure member such as a stringer.
- the secondary structure member is a clip, a bracket, a metal fitting used for fastening pipes, a seat frame, or the like.
- the secondary structure member is not loaded as heavily as the primary structure member.
- an aircraft member is extruded by using an Mg-Al-Ca based alloy billet including an (Mg, Al) 2 Ca compound (hereinafter, (Mg, Al) 2 Ca).
- the extrusion processing is performed under a condition where the billet temperature is maintained to be lower than a melting temperature of the (Mg, Al) 2 Ca compound.
- (Mg, Al) 2 Ca is dispersed in a metallographic structure.
- the above Mg-Al-Ca based alloy (billet) is a casting manufactured by melt casting.
- the cooling rate during billet casting is lower than or equal to 1000 K/sec, preferably, lower than or equal to 100 K/sec.
- the diameter of the billet is greater than or equal to 29 mm and less than or equal to 180 mm.
- the diameter of the billet may be greater than or equal to 69 mm.
- an Mg-Al-Ca based alloy containing Al of greater than or equal to 6 atom% and less than or equal to 8 atom% and Ca of greater than or equal to 3 atom% and less than or equal to 4 atom% with respect to the whole amount is selected.
- the Mg-Al-Ca based alloy may contain Mn of greater than 0 atom% and less than or equal to 0.3 atom%, preferably, greater than or equal to 0.01 and less than or equal to 0.05.
- the remaining part of the Mg-Al-Ca based alloy (billet) is made of Mg. This not only means that the whole remaining part is made of Mg but also indicates that the remaining part may include impurities or other elements to the extent that does not affect the alloy characteristics.
- the Mg-Al-Ca based alloy does not contain Si. This not only means that the Si content is 0 atom% but also indicates that Si may be unavoidably contained (for example, less than or equal to 0.1 atom%).
- the above Mg-Al-Ca based alloy (billet) contains an (Mg, Al) 2 Ca compound.
- (Mg, Al) 2 Ca is contained by greater than or equal to 10 volume% and less than or equal to 35 volume%, preferably, greater than or equal to 10 volume% and less than or equal to 30 volume%.
- the melting temperature of (Mg, Al) 2 Ca is 490 degrees Celsius.
- the melting temperature is derived from a phase diagram.
- the billet temperature during extrusion processing may be maintained to be lower than the melting temperature by setting an extrusion temperature and an extrusion exit rate.
- the "extrusion exit rate” is a rate at which a material is extruded from an extrusion mold (die) during extrusion molding.
- a extrusion ratio may be higher than or equal to 10 and lower than or equal to 80.
- the cross section of the extruded material may be an L-shape, a T-shape, or a Z-shape, for example.
- the billet of the Mg-Al-Ca based alloy may be heat-treated at a temperature higher than or equal to 400 degrees Celsius and lower than or equal to 500 degrees Celsius for a period longer than or equal to one hour and shorter than or equal to six hours before extrusion processing.
- the processing temperature is preferably higher than or equal to 450 degrees Celsius and lower than or equal to 500 degrees Celsius. More desirably, the processing time is made shorter, which is about one hour.
- Billets were extruded under predetermined conditions, and the tensile strength (FTY) and the ductility (elongation/EL) of the obtained extruded material were measured.
- FTY tensile strength
- EL ductility
- Fig. 1 and Table 1 illustrate measurement results.
- the horizontal axis (x-axis) represents an extrusion temperature (degrees Celsius)
- the vertical axis (y-axis) represents an extrusion exit rate Ve (m/min)
- a circle (O) plot x: 375 degrees Celsius, y: 3.6 m/min
- a circle plot x: 450 degrees Celsius, y: 0.9 m/min.
- a colored portion on the right side of the above-described straight line in the sheet is a region of conditions where the material temperature during extrusion (billet temperature) exceeds 490 degrees Celsius.
- Table 1 Extrusion material No. Extrusion condition Tensile strength (MPa) Ductility (%) Extrusion temperature (°C) Extrusion exit rate (m/min) 1 350 2.7 290 5.6 2 375 3.6 281 6.0 3 2.7 283 6.2 4 0.9 310 3.5 5 400 1.5 294 5.3 6 0.9 294 4.7 7 420 1.5 280 5.5 8 425 2.7 264 1.6 9 450 0.9 270 7.1
- the extruded material (a cross (X) plot /extruded material No. 8) extruded under a condition where the billet temperature exceeds 490 degrees Celsius (the billet being melted) had tensile strength of 264 MPa and ductility of 1.6%.
- all the extruded materials (circle plots /extruded materials No. 1 to 7, 9) extruded under a condition of a billet temperature at which no melting occurs (the temperature being maintained to be lower than the billet melting temperature) had tensile strength greater than or equal to 270 MPa and ductility greater than or equal to 3%.
- Fig. 2 illustrates a range of preferable extrusion processing conditions suggested from the result of Fig. 1 .
- the horizontal axis (x-axis) represents an extrusion temperature (degrees Celsius)
- the vertical axis (y-axis) represents an extrusion exit rate Ve (m/min)
- a long dashed double-short dashed line represents a preferable range
- a shaded portion between the solid line and the long dashed double-short dashed line is a region that represents a more preferable range.
- a colored portion on the right side of the above-described straight line in the sheet is a region of conditions where the material temperature during extru
- the extrusion temperature is higher than or equal to 350 degrees Celsius, and the extrusion exit rate is higher than or equal to 0.3 m/min.
- the extrusion temperature is lower than 350 degrees Celsius, the fluidity of the billet is deteriorated, which makes extrusion difficult.
- the extrusion exit rate is lower than 0.3 m/min, it becomes difficult to perform rate control of the extrusion apparatus.
- Fig. 3 and Table 2 illustrate results obtained by measuring the tensile strength (FTY) and the ductility (elongation/EL) of extruded materials obtained by performing extrusion processing by using billets whose Al and Ca contents are larger than values of the range defined in the present embodiment.
- Extruded materials No. 12 to 23 were heated by using a heater, and the temperatures at the time of ignition were measured. The extrusion ratio during extrusion processing was 15. The measurement results are illustrated in Table 3.
- Table 3 Extruded material No. Billet ( ⁇ 69mm) Composition Extrusion condition Ignition temperature (°C) Extrusion temperature (°C) Extrusion exit rate (m/min) Measurement result Average 12 Mg-8Al-4Ca-0.015Mn 375 3.6 1033 1038 13 1062 14 1020 15 Mg-8Al-4Ca-0.015Mn 450 0.9 1036 1039 16 1049 17 1032 18 Mg-6Al-3Ca 400 0.9 1080 1077 19 1075 20 1077 21 Mg-6Al-3Ca-0.05Mn 400 0.9 1017 1061 22 1082 23 1085 Reference : Elektron 43 845 869 865 898
- salt water 5% NaCl
- Fig. 4 illustrates results of the corrosion test.
- the vertical axis represents a corrosion rate (mm/year), and a bar of each test piece represents an average value.
- the corrosion rate (average) of Mg-10Al-5Ca was 0.75 mm/year.
- the corrosion rate (average) of Mg-10Al-5Ca-0.015Mn was 0.125 mm/year. Accordingly, it was confirmed that the presence of Mn affects the corrosion rate.
- the corrosion rate (average) of Mg-8Al-4Ca-0.015Mn containing Mn was also low such as 0.175 mm/year.
- the corrosion rate (average) of Elektron 43 was 0.425 mm/year. It was confirmed that the Mg-Al-Ca based alloy containing Mn has a lower corrosion rate than Elektron 43.
- the corrosion rate (average) of 7075-T6 was 0.15 mm/year. It was confirmed that the Mg-Al-Ca based alloy containing Mn has the same corrosion rate as 7075-T6.
- a refrigerant, a design method of the same, and a freezing machine filled with the refrigerant described in the above embodiment are understood as follows, for example.
- the present disclosure relates to a manufacturing method of an aircraft member to perform extrusion processing by using an Mg-Al-Ca based alloy containing (Mg, Al) 2 Ca.
- a billet of an Mg-Al-Ca based alloy containing Al: greater than or equal to 6 atom% and less than or equal to 8 atom% and Ca: greater than or equal to 3 atom% and less than or equal to 4 atom% with respect to the whole amount is selected, and the billet is extruded under a condition where the temperature of the billet is maintained to be lower than a melting temperature of the (Mg, Al) 2 Ca.
- the melting temperature of (Mg, Al) 2 Ca is 490 degrees Celsius.
- the Mg-Al-Ca based alloy described above has less specific gravity than an aluminum alloy used in a conventional aircraft field. Therefore, the weight can be reduced by 10% or more as compared to an aluminum alloy member by processing such an Mg-Al-Ca based alloy into an aircraft member.
- (Mg, Al) 2 Ca that is a C36 type compound is a hard compound.
- (Mg, Al) 2 Ca is dispersed in a metallographic structure, high strength and relatively large ductility can be obtained.
- the degree of dispersion of (Mg, Al) 2 Ca may be greater than or equal to 1 piece/ ⁇ m 2 . It is preferable that (Mg, Al) 2 Ca be fine (for example, less than or equal to 2 um).
- Addition of Ca can improve the incombustibility and the mechanical property of the extruded material (aircraft member). If the Ca content is excessively high, this makes it difficult to obtain a solidified state of the magnesium alloy, and extrusion processing becomes difficult. If the Ca content is excessively low, it is not possible to obtain sufficient incombustibility.
- Addition of Al can improve the mechanical property and the corrosion resistance of the extruded material. If the Al content is excessively high, it is not possible to obtain sufficient strength. If the Al content is excessively low, it is not possible to obtain sufficient ductility.
- Increased contents of Al and Ca contained in an Mg-Al-Ca based alloy may become a factor of coarsening (Mg, Al) 2 Ca in a metallographic structure. If the (Mg, Al) 2 Ca is coarsened, the ductility of the extruded material is likely to be reduced. With the contents of Al and Ca being within the range described above, this may result in an extruded material having desired ductility.
- the condition is set by an extrusion temperature and an extrusion exit rate, and with respect to a straight line connecting a first plot (x: 375 degrees Celsius, y: 3.6 m/min) to a second plot (x: 450 degrees Celsius, y: 0.9 m/min) in a graph of the x-y coordinate system where the x-axis represents the extrusion temperature (degrees Celsius) and the y-axis represents the extrusion exit rate (m/min), the extrusion temperature and the extrusion exit rate may be selected from values on the straight line or a range in which x and y are smaller than values on the straight line.
- the temperature of the billet can be maintained to be lower than the melting temperature of the (Mg, Al) 2 Ca during extrusion processing. Coordinates of the first plot and the second plot are obtained by actual measurement, which are highly reliable. Therefore, an extruded material having both good tensile strength and ductility can be more stably manufactured than in the conventional materials.
- the extrusion temperature in the condition be higher than or equal to 350 degrees Celsius. If the extrusion temperature is excessively low, the fluidity of the billet is reduced, which makes the extrusion difficult.
- the extrusion exit rate in the condition be higher than or equal to 0.3 m/min.
- the Mg-Al-Ca based alloy may contain Mn of greater than 0 atom% and less than or equal to 0.3 atom%.
- Mn has an effect of improving the corrosion resistance even with a small amount.
- the ductility of the extruded material is reduced in accordance with an increase in the addition amount.
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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)
- Extrusion Of Metal (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2021066471A JP7356116B2 (ja) | 2021-04-09 | 2021-04-09 | 航空機部材の製造方法 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP4071258A1 EP4071258A1 (en) | 2022-10-12 |
EP4071258B1 true EP4071258B1 (en) | 2024-01-17 |
Family
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP21209865.1A Active EP4071258B1 (en) | 2021-04-09 | 2021-11-23 | Manufacturing method of aircraft member |
Country Status (2)
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EP (1) | EP4071258B1 (ja) |
JP (1) | JP7356116B2 (ja) |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP3030338B1 (ja) * | 1998-10-05 | 2000-04-10 | 工業技術院長 | 高強度難燃性マグネシウム合金の製造方法 |
US7695771B2 (en) | 2005-04-14 | 2010-04-13 | Chemetall Gmbh | Process for forming a well visible non-chromate conversion coating for magnesium and magnesium alloys |
JP4539572B2 (ja) * | 2006-01-27 | 2010-09-08 | 株式会社豊田中央研究所 | 鋳造用マグネシウム合金および鋳物 |
JP2009119511A (ja) * | 2007-11-16 | 2009-06-04 | Sankyo Tateyama Aluminium Inc | Al添加マグネシウム合金押出管材の製造方法 |
JP5289904B2 (ja) * | 2008-11-18 | 2013-09-11 | 三協立山株式会社 | マグネシウム合金押出形材の製造方法 |
JP2010209452A (ja) | 2009-03-12 | 2010-09-24 | Sumitomo Electric Ind Ltd | マグネシウム合金部材 |
JP2010242146A (ja) * | 2009-04-03 | 2010-10-28 | Toyota Central R&D Labs Inc | マグネシウム合金およびマグネシウム合金部材 |
JP2012097309A (ja) * | 2010-10-29 | 2012-05-24 | Sanden Corp | マグネシウム合金部材、エアコン用圧縮機及びマグネシウム合金部材の製造方法 |
US10138535B2 (en) * | 2013-10-23 | 2018-11-27 | National University Corporation Kumamoto University | Magnesium alloy and method of manufacturing same |
JP6452042B2 (ja) * | 2015-03-13 | 2019-01-16 | 三協立山株式会社 | マグネシウム合金の製造方法 |
JP6667764B2 (ja) * | 2015-09-24 | 2020-03-18 | 国立大学法人富山大学 | マグネシウム合金及びそれを用いた鍛造品 |
JP2021063256A (ja) * | 2019-10-11 | 2021-04-22 | 三菱重工業株式会社 | 航空機部材の製造方法 |
WO2021157748A1 (ja) * | 2020-02-07 | 2021-08-12 | 国立大学法人 熊本大学 | マグネシウム合金及びその製造方法 |
-
2021
- 2021-04-09 JP JP2021066471A patent/JP7356116B2/ja active Active
- 2021-11-23 EP EP21209865.1A patent/EP4071258B1/en active Active
Also Published As
Publication number | Publication date |
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JP7356116B2 (ja) | 2023-10-04 |
EP4071258A1 (en) | 2022-10-12 |
JP2022161560A (ja) | 2022-10-21 |
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