JP7214720B2 - 被覆ターボ機械部品及び関連製造方法 - Google Patents
被覆ターボ機械部品及び関連製造方法 Download PDFInfo
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- 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
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- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
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- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
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- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
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- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
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- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
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- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
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- C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
- C23C4/11—Oxides
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- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/129—Flame spraying
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- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/134—Plasma spraying
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/18—After-treatment
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- 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
- F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
-
- 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
- F01D5/288—Protective coatings for blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
- F05D2230/312—Layer deposition by plasma spraying
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/512—Hydrophobic, i.e. being or having non-wettable properties
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Description
・機械的破損(層間剥離)に至る浸入層の強化;
・熱バリアの化学溶解及び異なる特性及び/又は体積を有する再結晶化生成物による不安定化
により分解する結果となる。
溶融CMASによる浸入経路を引き起こす熱機械効果による使用中のTBの亀裂;
被膜中のCMASの毛管浸入と不浸入遮断相の形成の反応速度の間の競争による浸入した厚さが変化する持続性。浸入した厚さが厚いほど、TBの機械的弱体化の危険性は大きい。実際、系の硬化が懸念されるため、CMASの浸入の停止にもかかわらず、耐用年数が制限される。
この液体不純物の毛管浸入を最小にするため、垂直亀裂のない、密な形態の抗CMAS被膜を用いることの必要性。この場合、系は異なる系の要素の熱膨張係数の差による熱機械応力に敏感になり、耐用年数が制限される。
-アルミノケイ酸カルシウムマグネシウムCMAS保護材料の粉末もしくは前駆体及び濡れ防止材の粉末もしくは前駆体又はそのいずれかの組合せを含有する少なくとも1つの懸濁液からのサスペンションプラズマ溶射法、
-アルミノケイ酸カルシウムマグネシウムCMAS保護材料の粉末もしくは前駆体及び濡れ防止材の粉末もしくは前駆体又はそのいずれかの組合せを含有する少なくとも1つの懸濁液からの高速フレーム溶射法、
-濡れ防止材の粉末もしくは前駆体を含有する溶液からのサスペンションプラズマ溶射法又は高速フレーム溶射法と組合せた、アルミノケイ酸カルシウムマグネシウムCMAS保護材料の粉末の大気圧プラズマ溶射法
のうち1つで行う、方法にも関する。
ジルコン酸希土類塩RE2Zr2O7(式中、RE=Y(イットリウム)、La(ランタン)、Ce(セリウム)、Pr(プラセオジム)、Nd(ネオジム)、Pm(プロメチウム)、Sm(サマリウム)、Eu(ユーロピウム)、Gd(ガドリニウム)、Tb(テルビウム)、Dy(ジスプロシウム)、Ho(ホルミウム)、Er(エルビウム)、Tm(ツリウム)、Yb(イッテルビウム)、Lu(ルテチウム)、一部もしくは完全に安定化されたジルコニア、デルタ相A′4B3O12(式中、A′はY、La、Ce、Pr、Nd、Pm、Sm、Eu、Gd、Tb、Dy、Ho、Er、Tm、Yb、及びLuから選ばれるあらゆる元素であり、BはZr、Hfである)、Y2O3とZrO2、Al2O3、又はTiO2を含む複合材、ヘキサアルミネート、スピネル、希土類REモノシリケート及びジシリケート(REはY、La、Ce、Pr、Nd、Pm、Sm、Eu、Gd、Tb、Dy、Ho、Er、Tm、Yb、Luである)。好ましくは、アルミノケイ酸カルシウムマグネシウムCMAS保護材料は、ジルコン酸希土類塩、ドープされたジルコン酸希土類塩、及びこれらの混合物より選ばれる。
-大気圧プラズマ溶射法(APS)、
-高速酸素燃料(HVOF)、
-サスペンションプラズマ溶射法(SPS)、
-溶液前駆体プラズマ溶射法(SPPS)、
-サスペンションーHVOF(S-HVOF)としても公知の高速サスペンションフレーム溶射法(HVSFS)
の1つによって形成及び成膜してもよい。
図5に示されているように、本発明によるガスタービンエンジン部品50の製造方法を、その上に複合アルミノケイ酸カルシウムマグネシウムCMAS保護層52をSPSにより塗布されたAM1ニッケルベース超合金からなる基材51上で行い、該保護層52は、本発明により、アルミノケイ酸カルシウムマグネシウムCMAS保護材料としてGd2Zr2O7の第一相及びCMAS濡れ防止材として保護層52中に分散された粒子の形態のCaF2第二相を含む。
図6に示されているように、本発明によるガスタービンエンジン部品70の製造方法を、その上に複合アルミノケイ酸カルシウムマグネシウムCMAS保護層72をSPSにより塗布されたAM1ニッケルベース超合金から成る基材71上で行い、該保護層72は、本発明により、アルミノケイ酸カルシウムマグネシウムCMAS保護材料としてGd2Zr2O7の第一相及びCMAS濡れ防止材として保護層72中に分散された粒子の形態のCaF2第二相を含む。
図7に示されているように、本発明によるガスタービンエンジン部品90の製造方法を、SPS及びAPSにより複合アルミノケイ酸カルシウムマグネシウムCMAS保護層92を成膜されたAM1ニッケルベース超合金からなる基材91上で実施し、保護層92は、本発明により、アルミノケイ酸カルシウムマグネシウムCMAS保護材料としてGd2Zr2O7の第一相及びCMAS濡れ防止材として保護層92中に分散された粒子の形態のCaF2第二相を含む。
Claims (9)
- 基材(21)、及び前記基材上に存在する少なくとも1つのアルミノケイ酸カルシウムマグネシウム(CMAS)保護層(24)を含む、被覆ガスタービンエンジン部品であって、前記層(24)が、アルミノケイ酸カルシウムマグネシウム(CMAS)保護材料の第一相(240)と、前記第一相中に分散された濡れ防止材の粒子を含む第二相を含み、 前記アルミノケイ酸カルシウムマグネシウム(CMAS)保護材料が一般式Ca 4 Re 6 (SiO 4 ) 6 OもしくはCa 2 Re 8 (SiO 4 ) 6 O 2 のアパタイト相又は一般式CaAl 2 Si 2 O 8 のアノーサイト相を形成することができる材料であり、
前記濡れ防止材が、以下の材料:
CaF2、
LnPO4(式中、Lnは、La(ランタン)、Gd(ガドリニウム)、Sm(サマリウム)、Nd(ネオジム)である)、
MAX相(Mn+1AXn、式中、nは、1、2、3であり、Mは、Sc(スカンジウム)、Y(イットリウム)、La(ランタン)、Mn(マンガン)、Re(レニウム)、W(タングステン)、Hf(ハフニウム)、Zr(ジルコニウム)、Ti(チタン)であり、Aは、IIIA族、IVA族、VA族、VIA族であり、XはC、Nである)、
AlN、及び
BN
より選ばれる材料又はこれらの材料の混合物に相当する、部品。 - 前記第一相(240)中に分散された濡れ防止材の粒子が、10nm~10μmの平均粒径を有する、請求項1に記載の部品。
- 前記第一相(240)中に分散された濡れ防止材の粒子の体積百分率が、1%~80%である、請求項1又は2に記載の部品。
- 前記第一相(240)中に分散された濡れ防止材の粒子の体積百分率が、保護層(24)の厚み方向で変化しており、前記粒子の体積百分率が、基材(21)に隣接する前記層の第1のゾーンと前記第1のゾーンから離れた前記層の第2のゾーンの間で徐々に増加する、請求項3に記載の部品。
- 前記アルミノケイ酸カルシウムマグネシウム(CMAS)保護層(24)が、1μm~1000μmの厚さを有する、請求項1~4のいずれか1項に記載の部品。
- 前記第一相(240)のアルミノケイ酸カルシウムマグネシウム(CMAS)保護材料が、アパタイト型相を形成することができ、かつ以下の材料:
希土類ジルコネート(RE2Zr2O7、式中、REは、La(ランタン)、Ce(セリウム)、Pr(プラセオジム)、Nd(ネオジム)、Pmプロメチウム)、Sm(サマリウム)、Eu(ユウロピウム)、Gd(ガドリニウム)、Tb(テルビウム)、Dy(ジスプロシウム)、Ho(ホルミウム)、Er(エルビウム)、Tm(ツリウム)、Yb(イッテルビウム)、Lu(ルテチウム)である)、
一部もしくは完全に安定化されたジルコニア、
デルタ相(A′4B3O12、式中、A′はY、La、Ce、Pr、Nd、Pm、Sm、Eu、Gd、Tb、Dy、Ho、Er、Tm、Yb、及びLuから選ばれるいずれかの元素であり、BはZr、Hfである)、
Y2O3とZrO2、Al2O3、又はTiO2を含む複合材、
ヘキサアルミネート、
スピネル、
希土類REモノシリケート及びジシリケート(REはY、La、Ce、Pr、Nd、Pm、Sm、Eu、Gd、Tb、Dy、Ho、Er、Tm、Yb、Luである)
の1つまたはこれらの材料の混合物である、請求項1~5のいずれか1項に記載の部品。 - 基材(21)とアルミノケイ酸カルシウムマグネシウム(CMAS)保護層(24)の間に挿入された熱バリア層(23)をさらに含む、請求項1~6のいずれか1項に記載の部品。
- 前記基材(21)が、ニッケルもしくはコバルトをベースとする超合金であり、かつその表面にアルミノボンドコート(22)もしくはセラミックマトリックス複合材料(CMC)層、又はアルミノ形成ボンドコートによりコートされたセラミックマトリックス複合材料(CMC)層を有する、請求項1~7のいずれか1項に記載の部品。
- 請求項1~8のいずれか1項に記載の部品の製造方法であって、基材(21)上又は基材上に存在する熱バイリア層(23)上にアルミノケイ酸カルシウムマグネシウム(CMAS)保護層(24)を直接形成する工程を少なくとも含み、この形成する工程が、以下の方法:
アルミノケイ酸カルシウムマグネシウム(CMAS)保護材料の粉末もしくは前駆体、及び濡れ防止材の粉末もしくは前駆体を含む少なくとも1つの懸濁液のサスペンジョンプラズマ溶射法、
アルミノケイ酸カルシウムマグネシウム(CMAS)保護材料の粉末もしくは前駆体、及び濡れ防止材の粉末もしくは前駆体を含む少なくとも1つの懸濁液の高速フレーム溶射法、
懸濁した濡れ防止セラミック材料の粉末もしくは濡れ防止セラミック材料の前駆体を含む溶液からのサスペンジョンプラズマ溶射法又は高速フレーム溶射法と組み合わせた、アルミノケイ酸カルシウムマグネシウム(CMAS)保護材料の粉末の大気圧プラズマ溶射法
の1つにより行われる方法。
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FR1755210A FR3067391B1 (fr) | 2017-06-12 | 2017-06-12 | Revetement anti-cmas a efficacite renforcee |
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PCT/FR2018/051359 WO2018229409A1 (fr) | 2017-06-12 | 2018-06-12 | Pièce de turbomachine revêtue et procédé de fabrication associé |
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US20210188721A1 (en) * | 2019-12-19 | 2021-06-24 | Rolls-Royce Corporation | Cmas-resistant abradable coatings |
CN111850454B (zh) * | 2020-07-30 | 2022-12-16 | 江苏大学 | 一种抗cmas侵蚀的热障涂层及制备方法 |
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