JP2014185636A - 耐エロージョン性及び耐コロージョン性のコーティング系を備えるターボ機械部品並びに当該ターボ機械部品の製造方法 - Google Patents
耐エロージョン性及び耐コロージョン性のコーティング系を備えるターボ機械部品並びに当該ターボ機械部品の製造方法 Download PDFInfo
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- 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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- 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
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- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
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- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/34—Sputtering
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- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
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- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
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- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/341—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one carbide layer
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- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/347—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with layers adapted for cutting tools or wear applications
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- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/40—Coatings including alternating layers following a pattern, a periodic or defined repetition
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- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/40—Coatings including alternating layers following a pattern, a periodic or defined repetition
- C23C28/42—Coatings including alternating layers following a pattern, a periodic or defined repetition characterized by the composition of the alternating layers
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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
- F01D5/288—Protective coatings for blades
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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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
Abstract
【解決手段】本発明に係る定置型のターボ機械のターボ機械部品(10)では、10%〜18%クロム高合金鋼、チタン合金、ニッケル基合金又はコバルト基合金からなる、基材表面(19)を有する基材(16)と、耐エロージョン性及び耐コロージョン性のコーティング系(17,18,20)と、を備え、該コーティング系(17,18,19)は、前記ターボ機械部品(10)の基材表面(19)上に析出され、耐コロージョン性の層として働く第1の層(17)と、該第1の層(17)上に析出され、耐エロージョン性の層として働く第2の層(18)と、を有し、前記第1の層(17)は、Zr単層であり、前記第2の層(18)は、W/WC複層であるようにした。
【選択図】図3
Description
a)10%〜18%クロム高合金鋼、チタン合金、ニッケル基合金又はコバルト基合金からなる、基材表面を有する基材を備えるターボ機械部品を用意し;
b)基材表面上に耐コロージョン性の第1の層を析出し、その際、第1の層をZr単層コーティングとし;かつ
c)耐コロージョン性の第1の層上に耐エロージョン性の第2の層を析出し、その際、第2の層をW/WC複層コーティングとし、これにより第1の層をボンドコートとして使用する;
というステップを有する。
a)10%〜18%クロム高合金鋼、チタン合金、ニッケル基合金又はコバルト基合金からなる、基材表面19を有する基材16を備えるターボ機械部品10を用意し(図4A);
b)基材表面19上に耐コロージョン性の第1の層17を析出し(図4B)、その際、第1の層17をZr単層として析出し;かつ
c)耐コロージョン性の第1の層17上に耐エロージョン性の第2の層18を析出し、その際、第2の層18をW/WC複層コーティングとして析出し、これにより第1の層17をボンドコートとして使用する(図4C);
というステップを有する。
Claims (12)
- 定置型のターボ機械のターボ機械部品(10)であって、
10%〜18%クロム高合金鋼、チタン合金、ニッケル基合金又はコバルト基合金からなる、基材表面(19)を有する基材(16)と、
耐エロージョン性及び耐コロージョン性のコーティング系(17,18,20)と、
を備え、該コーティング系(17,18,20)は、
前記ターボ機械部品(10)の基材表面(19)上に析出され、耐コロージョン性の層として働く第1の層(17)と、
該第1の層(17)上に析出され、耐エロージョン性の層として働く第2の層(18)と、
を有し、前記第1の層(17)は、Zr単層であり、前記第2の層(18)は、W/WC複層であることを特徴とする、定置型のターボ機械のターボ機械部品。 - 前記第1の層(17)は、実質的に前記第2の層(18)の厚さより薄い厚さを有する、請求項1記載のターボ機械部品。
- 前記第1の層(17)は、3〜10μmの厚さを有し、前記第2の層(18)は、15〜23μmの厚さを有する、請求項2記載のターボ機械部品。
- 前記第2の層(18)は、10層以上の交互のWとWCとの副層(18a,b)を有する、請求項1記載のターボ機械部品。
- 前記第2の層(18)は、それぞれ0.75μm〜1.25μmの厚さを有する10層のWの副層と10層のWCの副層とを有する、請求項4記載のターボ機械部品。
- 前記ターボ機械部品(10)は、前記第1の層(17)により完全にコーティングされており、前記第2の層(18)は、高いエロージョン負荷を有する場所にのみ設けられている、請求項1記載のターボ機械部品。
- 前記ターボ機械部品(10)は、前縁(14)及び後縁(15)を有する翼(11)を備える、ガスタービンのコンプレッサブレード(10)又はベーンであり、前記第2の層(18)は、前記前縁(14)に設けられている、請求項1記載のターボ機械部品。
- 請求項1記載のターボ機械部品(10)を製造する方法であって:
a)10%〜18%クロム高合金鋼、チタン合金、ニッケル基合金又はコバルト基合金からなる、基材表面(19)を有する基材(16)を備えるターボ機械部品(10)を用意し;
b)前記基材表面(19)上に耐コロージョン性の第1の層(17)を析出し、その際、該第1の層(17)をZr単層コーティングとして析出し;かつ
c)前記耐コロージョン性の第1の層(17)上に耐エロージョン性の第2の層(18)を析出し、その際、該第2の層(18)をW/WC複層コーティングとして析出し、これにより前記第1の層(17)をボンドコートとして使用する;
というステップを有することを特徴とする、ターボ機械部品を製造する方法。 - 前記耐コロージョン性の第1の層(17)を3〜10μmの厚さで析出する、請求項8記載の方法。
- 同じ厚さのW及びWCの単層又は副層(18a,b)を、前記複層(18)の全体の厚さが15〜23μmとなるまで、交互に析出する、請求項8記載の方法。
- 前記層(17,18)の析出を標準的なマグネトロンスパッタ法を用いて行う、請求項8から10までのいずれか1項記載の方法。
- 前記層(17,18)の析出を、好適に方向付けられたガス流と組み合わされたホローカソードグロー放電を基礎とするガスフロースパッタ法により行う、請求項8から10までのいずれか1項記載の方法。
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WO2016158765A1 (ja) * | 2015-04-02 | 2016-10-06 | 株式会社Ihi | エンジン用圧縮機翼 |
WO2017077801A1 (ja) * | 2015-11-06 | 2017-05-11 | 株式会社Ihi | 耐食性コーティングを有するエンジン用圧縮機翼およびそのコーティング方法 |
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EP2767616A1 (en) | 2013-02-15 | 2014-08-20 | Alstom Technology Ltd | Turbomachine component with an erosion and corrosion resistant coating system and method for manufacturing such a component |
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US11686208B2 (en) | 2020-02-06 | 2023-06-27 | Rolls-Royce Corporation | Abrasive coating for high-temperature mechanical systems |
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WO2016104303A1 (ja) * | 2014-12-25 | 2016-06-30 | 株式会社Ihi | エンジン用圧縮機翼 |
JPWO2016104303A1 (ja) * | 2014-12-25 | 2017-09-07 | 株式会社Ihi | エンジン用圧縮機翼 |
US10619644B2 (en) | 2014-12-25 | 2020-04-14 | Ihi Corporation | Compressor vane or blade for engine |
WO2016158765A1 (ja) * | 2015-04-02 | 2016-10-06 | 株式会社Ihi | エンジン用圧縮機翼 |
JP2016196820A (ja) * | 2015-04-02 | 2016-11-24 | 株式会社Ihi | エンジン用圧縮機翼 |
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Also Published As
Publication number | Publication date |
---|---|
US20140234096A1 (en) | 2014-08-21 |
EP2767616A1 (en) | 2014-08-20 |
US10041360B2 (en) | 2018-08-07 |
KR20140103066A (ko) | 2014-08-25 |
CN103993913A (zh) | 2014-08-20 |
CN103993913B (zh) | 2017-03-01 |
RU2014105551A (ru) | 2015-08-20 |
RU2594092C2 (ru) | 2016-08-10 |
CA2842589A1 (en) | 2014-08-15 |
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