JP6328398B2 - High strength titanium alloy with excellent oxidation resistance and compressor parts using the same - Google Patents
High strength titanium alloy with excellent oxidation resistance and compressor parts using the same Download PDFInfo
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- 229910001069 Ti alloy Inorganic materials 0.000 title claims description 38
- 230000003647 oxidation Effects 0.000 title claims description 33
- 238000007254 oxidation reaction Methods 0.000 title claims description 33
- 229910045601 alloy Inorganic materials 0.000 claims description 18
- 239000000956 alloy Substances 0.000 claims description 18
- 238000000034 method Methods 0.000 claims description 13
- 230000000052 comparative effect Effects 0.000 claims description 10
- 238000002844 melting Methods 0.000 claims description 8
- 230000008018 melting Effects 0.000 claims description 8
- 239000010936 titanium Substances 0.000 claims description 8
- 238000004519 manufacturing process Methods 0.000 claims description 5
- 229910052750 molybdenum Inorganic materials 0.000 claims description 5
- 229910052710 silicon Inorganic materials 0.000 claims description 5
- 229910052726 zirconium Inorganic materials 0.000 claims description 5
- 239000012535 impurity Substances 0.000 claims description 4
- 239000000203 mixture Substances 0.000 claims description 4
- 238000010894 electron beam technology Methods 0.000 claims description 3
- 230000006698 induction Effects 0.000 claims description 3
- 229910052758 niobium Inorganic materials 0.000 claims description 3
- 229910052718 tin Inorganic materials 0.000 claims description 3
- 229910052721 tungsten Inorganic materials 0.000 claims description 3
- 238000010313 vacuum arc remelting Methods 0.000 claims description 3
- 229910052727 yttrium Inorganic materials 0.000 claims description 3
- 229910052802 copper Inorganic materials 0.000 claims description 2
- 229910052733 gallium Inorganic materials 0.000 claims description 2
- 229910052735 hafnium Inorganic materials 0.000 claims description 2
- 229910052715 tantalum Inorganic materials 0.000 claims 2
- 230000007423 decrease Effects 0.000 description 7
- 239000006104 solid solution Substances 0.000 description 6
- 239000000567 combustion gas Substances 0.000 description 5
- 230000000087 stabilizing effect Effects 0.000 description 4
- 238000005728 strengthening Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 229910000765 intermetallic Inorganic materials 0.000 description 3
- 229910021330 Ti3Al Inorganic materials 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 229910052742 iron Inorganic materials 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000007935 neutral effect Effects 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910021332 silicide Inorganic materials 0.000 description 2
- FVBUAEGBCNSCDD-UHFFFAOYSA-N silicide(4-) Chemical compound [Si-4] FVBUAEGBCNSCDD-UHFFFAOYSA-N 0.000 description 2
- 229910052684 Cerium Inorganic materials 0.000 description 1
- MKYBYDHXWVHEJW-UHFFFAOYSA-N N-[1-oxo-1-(2,4,6,7-tetrahydrotriazolo[4,5-c]pyridin-5-yl)propan-2-yl]-2-[[3-(trifluoromethoxy)phenyl]methylamino]pyrimidine-5-carboxamide Chemical class O=C(C(C)NC(=O)C=1C=NC(=NC=1)NCC1=CC(=CC=C1)OC(F)(F)F)N1CC2=C(CC1)NN=N2 MKYBYDHXWVHEJW-UHFFFAOYSA-N 0.000 description 1
- 229910052804 chromium Inorganic materials 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000011978 dissolution method Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 229910052746 lanthanum Inorganic materials 0.000 description 1
- 229910052748 manganese Inorganic materials 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
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Description
本発明は、耐熱チタン合金に関し、特に高温における優れた耐酸化性を有し、航空機エンジン内部コンプレッサーブレードやコンプレッサーディスク等の高温、高応力下で使用される部材として好適な耐熱チタン合金に関する。
また、本発明は当該耐熱チタン合金を用いたコンプレッサー部品に関する。
The present invention relates to a heat-resistant titanium alloy, and particularly to a heat-resistant titanium alloy having excellent oxidation resistance at high temperatures and suitable as a member used under high temperature and high stress, such as an aircraft engine internal compressor blade and a compressor disk.
The present invention also relates to a compressor component using the heat resistant titanium alloy.
耐熱チタン合金は航空機エンジンの部品、例えば、コンプレッサーブレードやコンプレッサーディスクに広く使用されている。高温ガスに曝される中、この材料にはコーティングが施されていないため、材料そのものの特性が部材の寿命を決定する。これまで、航空機エンジンの熱効率向上のため、燃焼ガス温度が上昇してきた。それに伴い、新しいコンプレッサー部材が開発され、耐用温度が向上した。 Heat resistant titanium alloys are widely used in aircraft engine parts such as compressor blades and compressor disks. Since this material is not coated during exposure to hot gases, the properties of the material itself determine the life of the member. In the past, combustion gas temperatures have increased to improve the thermal efficiency of aircraft engines. Along with that, a new compressor member was developed and its service temperature was improved.
米国において、Ｓｉが添加されたＴｉ−６２４２Ｓ合金（Ａｌ：６質量％、Ｓｎ：２質量％、Ｚｒ：４質量％、Ｍｏ：２質量％で残部がＴｉからなる合金）が開発され、その後、英国でさらに耐用温度が高いＩＭＩ８３４（Ａｌ：５．８質量％、Ｓｎ：４質量％、Ｚｒ：３．５質量％、Ｍｏ：０．３質量％、Ｎｂ：１質量％、Ｓｉ：０．３質量％、Ｃ：０．０６質量％で残部がＴｉからなる合金）（特許文献１）が開発されている。このＩＭＩ８３４は高温６００℃で高強度を有する合金として、航空機エンジンのコンプレッサーブレードへの使用実績を有している。 In the United States, a Ti-6242S alloy (Al: 6% by mass, Sn: 2% by mass, Zr: 4% by mass, Mo: 2% by mass, and the balance comprising Ti) is developed in the United States. IMI834 (Al: 5.8 mass%, Sn: 4 mass%, Zr: 3.5 mass%, Mo: 0.3 mass%, Nb: 1 mass%, Si: 0.3 An alloy (mass%, C: 0.06 mass% with the balance being Ti) (Patent Document 1) has been developed. This IMI834 is an alloy having high strength at a high temperature of 600 ° C. and has a track record of use in compressor blades for aircraft engines.
しかし、近年のさらなる燃焼ガス温度上昇によって、高温酸化の部材損傷への影響は大きくなるため、高温酸化により損傷が生じにくい耐酸化性に優れたチタン合金の開発が期待されている。 However, due to the recent increase in combustion gas temperature, the influence of high-temperature oxidation on member damage increases, and therefore, development of a titanium alloy having excellent oxidation resistance that is unlikely to be damaged by high-temperature oxidation is expected.
耐酸化性に優れたチタン合金はこれまでにも開発されている。特許文献２では、Ａｌが質量３％未満で、軽量かつ室温での加工性、耐酸化性に優れたチタン合金が提案されている。特許文献３では耐食性、耐酸化性に優れたチタン合金が、特許文献４ではＡｌの添加量を０．３質量％未満に規制した耐酸化性に優れるチタン合金が開発されている。 Titanium alloys with excellent oxidation resistance have been developed so far. Patent Document 2 proposes a titanium alloy having a mass of less than 3%, light weight, excellent workability at room temperature, and excellent oxidation resistance. In Patent Document 3, a titanium alloy excellent in corrosion resistance and oxidation resistance is developed. In Patent Document 4, a titanium alloy excellent in oxidation resistance in which the amount of Al added is regulated to less than 0.3% by mass has been developed.
また、特許文献５は酸化しやすいＦｅを含有するにも関わらず耐酸化性と強度を兼ね備えたチタン合金を提案している。 Patent Document 5 proposes a titanium alloy having both oxidation resistance and strength despite containing Fe that is easily oxidized.
しかしながら、特許文献１では耐酸化特性が報告されておらず、高温での耐酸化性が明らかでない。特許文献２に記載された発明は質量％でＡｌを０．４〜２．５％、Ｎｂを０．３〜１．１％、Ｆｅを０．０６％以下、酸素を０．１％以下を含有するチタン合金である。特許文献３に記載された発明は質量％でＡｌを０．３〜１．５％、Ｓｉを０．１〜１．０％含有するチタン合金である。特許文献４に記載された発明は質量％でＡｌを０．３％、未満、Ｓｉを０．１５〜２．０％含有するチタン合金である。しかし、これら特許文献２、３は、アルファ相固溶強化に有効なＡｌの添加量が３％未満と少ない上、その他の固溶強化元素が添加されておらず、引張強さ６００ＭＰａ（室温）に達していない。このため航空機エンジンのコンプレッサー後段部材として不適当である。また特許文献４についても、特許文献２、３と同様に強度が低いと予想されるが強度試験の結果は報告されていない。 However, Patent Document 1 does not report oxidation resistance characteristics, and oxidation resistance at high temperatures is not clear. In the invention described in Patent Document 2, Al is 0.4 to 2.5% by mass, Nb is 0.3 to 1.1%, Fe is 0.06% or less, and oxygen is 0.1% or less. It is a titanium alloy containing. The invention described in Patent Document 3 is a titanium alloy containing 0.3 to 1.5% Al and 0.1 to 1.0% Si by mass%. The invention described in Patent Document 4 is a titanium alloy containing 0.3% by weight of Al and less than 0.15% to 2.0% Si by mass%. However, in these Patent Documents 2 and 3, the addition amount of Al effective for alpha phase solid solution strengthening is as small as less than 3%, and no other solid solution strengthening elements are added, and the tensile strength is 600 MPa (room temperature). Not reached. For this reason, it is unsuitable as a compressor latter stage member of an aircraft engine. Also, Patent Document 4 is expected to have a low strength as in Patent Documents 2 and 3, but the results of the strength test have not been reported.
特許文献５に記載された発明は質量％でＦｅを０．２〜５％、酸素を０．０５〜０．７５％含み、Ｚｒを特定の範囲内で含有する耐酸化性に優れたチタン合金であり、発明例ではＳｉ，Ｃｒ，Ｎｉ，Ｍｎ，Ｎ，Ｃも含んだチタン合金が報告されたが、強度は必ずしも十分でなかった。 The invention described in Patent Document 5 is a titanium alloy excellent in oxidation resistance containing 0.2 to 5% Fe, 0.05 to 0.75% oxygen, and Zr within a specific range by mass%. In the example of the invention, a titanium alloy containing Si, Cr, Ni, Mn, N, and C was reported, but the strength was not always sufficient.
近年、航空機エンジンの熱効率向上のため、燃焼ガス温度が高温化されており、さらに高温で優れた耐酸化性を有する耐熱チタン合金の実現が期待されている。本発明はメタル温度が７５０℃のような、従来よりも高温で耐酸化性に優れた高強度チタン合金およびその合金を用いたコンプレッサー部品を提供することを目的とする。 In recent years, in order to improve the thermal efficiency of aircraft engines, the combustion gas temperature has been increased, and further, it is expected to realize a heat-resistant titanium alloy having excellent oxidation resistance at a high temperature. An object of the present invention is to provide a high-strength titanium alloy having a metal temperature of 750 ° C. and superior oxidation resistance at a higher temperature than before, and a compressor component using the alloy.
本発明のチタン合金は、上記の課題を解決する手段として以下のことを特徴としている。
本発明の第１のチタン合金は、合金組成を質量％として、Ａｌ：４−７質量％、Ｇａ：１−６質量％、Ｚｒ：２−５質量％、Ｍｏ：０−３質量％、Ｗ：０−２質量％、Ｎｂ：０−１質量％、Ｔａ：０−２質量％、Ｓｉ：０−０．５質量％を含有すると共に、Ｓｎ：０質量％であり、残部がＴｉと不可避的不純物からなる組成を有し、試験温度７５０℃での耐酸化性が、Ｓｎを含有すると共に、Ｇａを含有しない比較合金（表１に記載の比較合金１）よりも優れていることを特徴とする。
本発明の第二のチタン合金は、前記Ｇａを含有しない比較合金が、Ａｌ：５．８質量％、Ｓｎ：４．０質量％、Ｇａ：０質量％、Ｚｒ：３．５質量％、Ｍｏ：０．３質量％、Ｗ：０質量％、Ｎｂ：１．０質量％、Ｔａ：０質量％、Ｓｉ：０．３質量％を含有し、残部がＴｉと不可避的不純物からなる組成を有するとよい。
The titanium alloy of the present invention is characterized by the following as means for solving the above problems.
The first titanium alloy of the present invention has an alloy composition of mass%, Al: 4-7 mass% , Ga: 1-6 mass%, Zr: 2-5 mass%, Mo: 0-3 mass%, W : 0-2% by mass, Nb: 0-1% by mass, Ta: 0-2% by mass, Si: 0-0.5% by mass , Sn: 0% by mass, the balance being inevitable with Ti It has a composition composed of mechanical impurities, and its oxidation resistance at a test temperature of 750 ° C. is superior to that of a comparative alloy containing Sn and not containing Ga (comparative alloy 1 described in Table 1). And
In the second titanium alloy of the present invention, the comparative alloy containing no Ga is Al: 5.8 mass%, Sn: 4.0 mass%, Ga: 0 mass%, Zr: 3.5 mass%, Mo : 0.3% by mass, W: 0% by mass, Nb: 1.0% by mass, Ta: 0% by mass, Si: 0.3% by mass, with the balance being composed of Ti and inevitable impurities Good.
本発明の第三のチタン合金は、上記第一又は第二のチタン合金において、さらに、Ｖ：４質量％以下、Ｈｆ：２質量％以下、Ｃｕ：１質量％以下、Ｂ＋Ｃ：０．２質量％以下、Ｙ：０．２質量％以下、Ｌａ：０．２質量％以下、Ｃｅ：０．２質量％以下の元素のいずれか１種または２種以上を含有する。
The third titanium alloy of the present invention is the above first or second titanium alloy, further V: 4 mass% or less, Hf: 2 mass% or less, Cu: 1 mass% or less, B + C: 0.2 mass %, Y: 0.2% by mass or less, La: 0.2% by mass or less, Ce: 0.2% by mass or less of any one element or two or more elements.
本発明の第四は、上記第一から第三のチタン合金を用いて、コンプレッサー部品を消耗電極式真空アーク再溶解法、電子ビーム溶解法、プラズマアーク溶解法、又はコールドクルシブル誘導溶解法の何れか一種類により製造する方法である。
本発明の第五は、上記コンプレッサー部品は、コンプレッサーブレード又はコンプレッサーディスクであることを特徴とする第四に記載の製造方法である。
According to a fourth aspect of the present invention, the compressor parts are made of the consumable electrode type vacuum arc remelting method, the electron beam melting method, the plasma arc melting method, or the cold-crucible induction melting method using the first to third titanium alloys. It is the method of manufacturing by any one kind .
A fifth aspect of the present invention is the manufacturing method according to the fourth aspect, wherein the compressor component is a compressor blade or a compressor disk.
本発明によれば、航空機エンジンの燃焼ガス温度が高温化されるなか、従来よりも高い温度で優れた耐酸化性を有するチタン合金が提供される。従来であれば、燃焼ガス温度が高温化された場合、特に耐酸化性が問題となるが、本発明合金は高温での耐酸化性を特に重視したチタン合金であることから従来のような問題は改善される。 ADVANTAGE OF THE INVENTION According to this invention, the titanium alloy which has the oxidation resistance which was excellent in the temperature higher than before is provided, while the combustion gas temperature of an aircraft engine is raised. Conventionally, when the combustion gas temperature is raised, oxidation resistance becomes a problem in particular. However, the present invention alloy is a titanium alloy that places special emphasis on oxidation resistance at high temperature, so the conventional problem Is improved.
本発明のチタン合金は耐酸化性に優れており、航空機エンジンのコンプレッサーブレードとして従来よりも高温で長時間使用された場合、長時間の使用に耐え、その経済効果は大きい。 The titanium alloy of the present invention has excellent oxidation resistance, and when used as a compressor blade for an aircraft engine at a higher temperature for a longer time than before, it can withstand long-time use and has a great economic effect.
本発明は上記のとおりの特徴をもつものであるが、以下にその実施の形態について説明する。 The present invention has the features as described above, and an embodiment thereof will be described below.
本発明のチタン合金の合金元素の限定理由は以下のとおりである。 The reasons for limiting the alloy elements of the titanium alloy of the present invention are as follows.
Ａｌはアルファ相を安定化させ、強度向上に有効であるが、１２質量％より多いとＴｉ３Ａｌの体積率が増加し、アルファ量が減少し、脆化する。よって、０．１−１２質量％、とする。好ましくは、３−９質量％、さらに最も好ましくは４−７質量％である。 Al stabilizes the alpha phase and is effective in improving the strength. However, if it exceeds 12% by mass, the volume ratio of Ti3Al increases, the alpha content decreases, and embrittlement occurs. Therefore, 0.1-12 mass%. Preferably, it is 3-9% by mass, and most preferably 4-7% by mass.
Ｓｎは中性型元素であり、強度向上に有効であるが、多量の添加は耐酸化性の低下をもたらす。Ｓｎは０−７質量％の範囲とする。好ましくは０−６質量％。さらに最も好ましくは０−５質量％の範囲である。 Sn is a neutral element and is effective in improving the strength, but a large amount of addition causes a decrease in oxidation resistance. Sn is in the range of 0-7% by mass. Preferably 0-6 mass%. More preferably, it is the range of 0-5 mass%.
Ｇａはアルファ相を安定化させ、固溶強化の作用がある。また、金属間化合物Ｔｉ３Ａｌを安定化させるが、１０質量％を超えると延性が低下するため、０．１−１０質量％とする。好ましくは０．５−８質量％、さらに最も好ましくは１−６質量％の範囲である。 Ga stabilizes the alpha phase and has the effect of strengthening the solid solution. Moreover, although intermetallic compound Ti3Al is stabilized, since ductility will fall when it exceeds 10 mass%, it shall be 0.1-10 mass%. Preferably it is 0.5-8 mass%, More preferably, it is the range of 1-6 mass%.
ＺｒはＴｉと全率固溶で中性型元素である。固溶強化の作用があり、０．１―７質量％とするが、７質量％を超えると延性が低下する。好ましくは１−６質量％、さらに最も好ましくは２−５質量％の範囲である。 Zr is a neutral element with a solid solution with Ti. It has the effect of solid solution strengthening and is 0.1-7% by mass, but if it exceeds 7% by mass, the ductility is lowered. Preferably it is 1-6 mass%, More preferably, it is the range of 2-5 mass%.
Ｍｏはベータ相安定化元素であり、強度向上と加工性向上に有効である。また、高温で疲労強度と引張・圧縮強度の向上に有効である。Ｍｏは５質量％以下とするが、５質量％を超えると強度が低下する。好ましくは４％以下、さらに最も好ましくは３質量％以下の範囲である。 Mo is a beta phase stabilizing element and is effective in improving strength and workability. It is also effective for improving fatigue strength and tensile / compressive strength at high temperatures. Mo is 5% by mass or less, but if it exceeds 5% by mass, the strength decreases. Preferably it is 4% or less, More preferably, it is the range of 3 mass% or less.
ＷはＭｏと同様にベータ相安定化元素であり、強度向上、加工性向上に有効であるが、多量添加は強度低下、密度上昇をもたらす。よって、４質量％以下とする。好ましくは３％以下、さらに最も好ましくは２質量％以下である。 W is a beta phase stabilizing element like Mo, and is effective for improving strength and workability. However, addition of a large amount causes a decrease in strength and an increase in density. Therefore, it is 4 mass% or less. Preferably it is 3% or less, More preferably, it is 2 mass% or less.
Ｎｂはベータ相安定化元素であり、加工性向上、耐酸化性向上に有効である。しかし、多量添加は強度が低下する。Ｎｂは０−３質量％とする。好ましくは０−２質量％。さらに最も好ましくは０−１質量％の範囲である。 Nb is a beta phase stabilizing element and is effective in improving workability and oxidation resistance. However, the strength decreases when a large amount is added. Nb is 0-3 mass%. Preferably 0-2 mass%. More preferably, it is the range of 0-1 mass%.
ＴａはＭｏと同様に強度向上、加工性向上に有効である。しかし、４質量％以上では強度が低下するため、０−４質量％とする。好ましくは０−３質量％。さらに最も好ましくは０−２質量％の範囲である。 Ta, like Mo, is effective for improving strength and workability. However, if the content is 4% by mass or more, the strength decreases, so 0-4% by mass. Preferably 0-3 mass%. More preferably, it is the range of 0-2 mass%.
Ｓｉは固溶により高温強度の向上に寄与する。また微細な金属間化合物のシリサイドを析出させ、強度を向上させる。さらには耐酸化性向上に有効である。しかし、２質量％を超えると、シリサイドが粗大化し、強度が低下するため、２質量％以下とする。好ましくは０−１質量％。さらに最も好ましくは０−０．５質量％と範囲である。 Si contributes to the improvement of high temperature strength by solid solution. In addition, fine intermetallic compound silicide is deposited to improve the strength. Furthermore, it is effective for improving oxidation resistance. However, if it exceeds 2% by mass, the silicide becomes coarse and the strength is lowered. Preferably 0-1 mass%. More preferably, the range is 0-0.5% by mass.
Ｖはベータ相安定化元素であり、加工性を向上させる。ただし、４質量％を超えると、耐酸化性が低下するため、４質量％以下と規定する。 V is a beta phase stabilizing element and improves workability. However, if it exceeds 4% by mass, the oxidation resistance decreases, so it is defined as 4% by mass or less.
ＨｆはＺｒと同様にＴｉと全率固溶する中性型元素である。強度向上に寄与するが、多量の添加は密度上昇をもたらすため、２質量％以下と規定する。 Hf is a neutral-type element that is solid-dissolved with Ti in the same manner as Zr. Although it contributes to strength improvement, a large amount of addition causes an increase in density, so it is defined as 2% by mass or less.
Ｃｕは疲労特性の向上に寄与するが、多量添加すると金属間化合物が析出し、延性が低下する。Ｃｕは１質量％以下と規定する。 Cu contributes to the improvement of fatigue properties, but when added in a large amount, an intermetallic compound is precipitated and ductility is lowered. Cu is defined as 1% by mass or less.
ＢとＣは強度向上に有効である。しかし、過度の添加は延性を害するため、ＢまたはＣの１種あるいは２種の添加量を０．２質量％以下と規定する。 B and C are effective for improving the strength. However, excessive addition impairs ductility, so the amount of one or two of B or C added is defined as 0.2% by mass or less.
Ｙ、Ｌａ、Ｃｅは高温で酸化皮膜の密着性を向上させ、耐酸化性向上に寄与する元素である。しかし、過度の添加は強度を低下させることからＹ：０．２質量％以下、Ｌａ：０．２質量％以下、Ｃｅ：０．２質量％以下と規定する。 Y, La, and Ce are elements that improve the adhesion of the oxide film at high temperatures and contribute to the improvement of oxidation resistance. However, since excessive addition reduces strength, it is defined as Y: 0.2% by mass or less, La: 0.2% by mass or less, and Ce: 0.2% by mass or less.
以上のとおり、この出願の耐酸化性に優れたチタン合金は従来公知の製造方法の手順や条件を勘案して、消耗電極式真空アーク再溶解法、電子ビーム溶解法、プラズマアーク溶解法、コールドクルシブル誘導溶解法により製造することができる。 As described above, the titanium alloy having excellent oxidation resistance in this application is considered to be a consumable electrode type vacuum arc remelting method, electron beam melting method, plasma arc melting method, cold method in consideration of the procedure and conditions of a conventionally known manufacturing method. It can be produced by a crucible induction dissolution method.
そこで以下に実施例を説明する。もちろん以下の例によって発明が限定されることはない。 Accordingly, examples will be described below. Of course, the invention is not limited by the following examples.
下記表１の各組成を有するチタン合金を溶製した。
得られた各々の合金について、直径８ｍｍ、高さ４ｍｍの試料を調整し、これを用いて耐酸化性を評価した。 About each obtained alloy, the sample of diameter 8mm and height 4mm was prepared, and oxidation resistance was evaluated using this.
耐酸化性試験は大気中において、試験温度７５０℃で実施した。この試験温度で、２０、４５、７０、９０、１１０、１４０、２４０時間のそれぞれにおいて、試料を炉外に取り出し、試料が冷却した後、重量変化を測定した。その後、再び炉に戻し、試験時間をカウントし、７５０℃で維持した。これを２４０時間まで行った。 The oxidation resistance test was performed in the air at a test temperature of 750 ° C. At this test temperature, at each of 20, 45, 70, 90, 110, 140, and 240 hours, the sample was taken out of the furnace, and after the sample cooled, the weight change was measured. Then, it returned to the furnace again, the test time was counted, and it maintained at 750 degreeC. This was done for up to 240 hours.
その結果、図１に示したように試験時間２４０時間の範囲で、Ｇａ含有の実施例１、２および３において、使用実績のある比較合金２（ＴＩＭＥＴ８３４）を上回る耐酸化性を持つ新しいチタン合金を見出した。なお、Ｇａを含まない比較合金１では耐酸化性が劣る。 As a result, as shown in FIG. 1, a new titanium alloy having an oxidation resistance exceeding that of Comparative Alloy 2 (TIMET834) that has been used in Ga-containing Examples 1, 2, and 3 within a test time range of 240 hours. I found. The comparative alloy 1 that does not contain Ga is inferior in oxidation resistance.
強度試験は、実施例１、２および３、比較合金１においてＪＩＳ規格Ｚ２２４１に準拠して室温の引張試験を実施した。その結果、図２に示したように、本発明のチタン合金は、０．２％耐力および引張強さ共に比較合金１よりも優れた強度であった。 For the strength test, a tensile test at room temperature was performed in Examples 1, 2 and 3, and Comparative Alloy 1 in accordance with JIS standard Z2241. As a result, as shown in FIG. 2, the titanium alloy of the present invention was superior to Comparative Alloy 1 in both 0.2% proof stress and tensile strength.
本発明のチタン合金は耐酸化性に優れており、航空機エンジンのコンプレッサーブレードやコンプレッサーディスクなどの高温部材、並びに、火力発電所のタービン部材、内燃機関の耐熱性部材に用いて好適である。
The titanium alloy of the present invention has excellent oxidation resistance, and is suitable for use in high-temperature members such as compressor blades and compressor disks of aircraft engines, turbine members of thermal power plants, and heat-resistant members of internal combustion engines.
Claims (5)
試験温度７５０℃での耐酸化性が、Ｓｎを含有すると共に、Ｇａを含有しない比較合金（表１に記載の比較合金１）よりも優れていることを特徴とするチタン合金。 Al: 4-7 mass% , Ga: 1-6 mass%, Zr: 2-5 mass%, Mo: 0-3 mass%, W: 0-2 mass%, Nb: 0-1 mass%, Ta: 0-2% by mass, Si: 0-0.5% by mass and Sn: 0% by mass, with the balance being composed of Ti and inevitable impurities,
A titanium alloy characterized in that the oxidation resistance at a test temperature of 750 ° C. is superior to that of a comparative alloy containing Sn and not containing Ga (comparative alloy 1 described in Table 1) .
The manufacturing method according to claim 4, wherein the compressor component is a compressor blade or a compressor disk.
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| CN106636749B (en) * | 2017-02-16 | 2018-10-16 | 燕山大学 | A method of obtaining titanium alloy martensitic structure |
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