JP2011021602A - Coating for turbo machine - Google Patents

Coating for turbo machine Download PDF

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Publication number
JP2011021602A
JP2011021602A JP2010153545A JP2010153545A JP2011021602A JP 2011021602 A JP2011021602 A JP 2011021602A JP 2010153545 A JP2010153545 A JP 2010153545A JP 2010153545 A JP2010153545 A JP 2010153545A JP 2011021602 A JP2011021602 A JP 2011021602A
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Prior art keywords
coating
turbomachine
graphite
dovetail
slot
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Japanese (ja)
Inventor
David V Bucci
デビッド・ヴィー・ブッチ
Paul S Dimascio
ポール・エス・ディマジオ
Surinder S Pabla
シュリンダー・エス・パブラ
Jesse C Moses
ジェシー・シー・モーゼス
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General Electric Co
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General Electric Co
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    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10M—LUBRICATING COMPOSITIONS; USE OF CHEMICAL SUBSTANCES EITHER ALONE OR AS LUBRICATING INGREDIENTS IN A LUBRICATING COMPOSITION
    • C10M125/00—Lubricating compositions characterised by the additive being an inorganic material
    • C10M125/02—Carbon; Graphite
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10M—LUBRICATING COMPOSITIONS; USE OF CHEMICAL SUBSTANCES EITHER ALONE OR AS LUBRICATING INGREDIENTS IN A LUBRICATING COMPOSITION
    • C10M103/00—Lubricating compositions characterised by the base-material being an inorganic material
    • C10M103/02—Carbon; Graphite
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10M—LUBRICATING COMPOSITIONS; USE OF CHEMICAL SUBSTANCES EITHER ALONE OR AS LUBRICATING INGREDIENTS IN A LUBRICATING COMPOSITION
    • C10M111/00—Lubrication compositions characterised by the base-material being a mixture of two or more compounds covered by more than one of the main groups C10M101/00 - C10M109/00, each of these compounds being essential
    • C10M111/02—Lubrication compositions characterised by the base-material being a mixture of two or more compounds covered by more than one of the main groups C10M101/00 - C10M109/00, each of these compounds being essential at least one of them being a non-macromolecular organic compound
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10M—LUBRICATING COMPOSITIONS; USE OF CHEMICAL SUBSTANCES EITHER ALONE OR AS LUBRICATING INGREDIENTS IN A LUBRICATING COMPOSITION
    • C10M111/00—Lubrication compositions characterised by the base-material being a mixture of two or more compounds covered by more than one of the main groups C10M101/00 - C10M109/00, each of these compounds being essential
    • C10M111/04—Lubrication compositions characterised by the base-material being a mixture of two or more compounds covered by more than one of the main groups C10M101/00 - C10M109/00, each of these compounds being essential at least one of them being a macromolecular organic compound
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10M—LUBRICATING COMPOSITIONS; USE OF CHEMICAL SUBSTANCES EITHER ALONE OR AS LUBRICATING INGREDIENTS IN A LUBRICATING COMPOSITION
    • C10M2201/00—Inorganic compounds or elements as ingredients in lubricant compositions
    • C10M2201/04—Elements
    • C10M2201/041—Carbon; Graphite; Carbon black
    • C10M2201/0413—Carbon; Graphite; Carbon black used as base material
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10M—LUBRICATING COMPOSITIONS; USE OF CHEMICAL SUBSTANCES EITHER ALONE OR AS LUBRICATING INGREDIENTS IN A LUBRICATING COMPOSITION
    • C10M2201/00—Inorganic compounds or elements as ingredients in lubricant compositions
    • C10M2201/10—Compounds containing silicon
    • C10M2201/102—Silicates
    • C10M2201/1023—Silicates used as base material
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10N—INDEXING SCHEME ASSOCIATED WITH SUBCLASS C10M RELATING TO LUBRICATING COMPOSITIONS
    • C10N2030/00—Specified physical or chemical properties which is improved by the additive characterising the lubricating composition, e.g. multifunctional additives
    • C10N2030/06—Oiliness; Film-strength; Anti-wear; Resistance to extreme pressure
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10N—INDEXING SCHEME ASSOCIATED WITH SUBCLASS C10M RELATING TO LUBRICATING COMPOSITIONS
    • C10N2040/00—Specified use or application for which the lubricating composition is intended
    • C10N2040/12—Gas-turbines
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10N—INDEXING SCHEME ASSOCIATED WITH SUBCLASS C10M RELATING TO LUBRICATING COMPOSITIONS
    • C10N2050/00—Form in which the lubricant is applied to the material being lubricated
    • C10N2050/14—Composite materials or sliding materials in which lubricants are integrally molded

Abstract

<P>PROBLEM TO BE SOLVED: To improve gap-corrosion resistance and fretting resistance by reducing the trouble of high contact stress fretting and abrasion in a turbine or a compressor rotating blade on the contact surface between the turbine or the compressor wheel of a turbo machine. <P>SOLUTION: With respect to coating, including a graphite-based solid thin film lubricant material, for a turbo machine, the coating is applied to at least one of a rotating blade disc assembly 12 and a wheel slot 42, preferably to a dovetail 40 of the rotating blade disc assembly 12. <P>COPYRIGHT: (C)2011,JPO&INPIT

Description

本発明は回転ターボ機械の表面処理に関する。具体的には、本発明は、応力を受けるガスタービン部品の表面処理に関するものであり、さらに具体的には、ガスタービン圧縮機動翼部品は圧縮機ホイールとの接触面で応力を受けるが、その接触面の表面処理に関する。   The present invention relates to surface treatment of a rotary turbomachine. Specifically, the present invention relates to surface treatment of stressed gas turbine components, and more specifically, gas turbine compressor blade components are stressed at the contact surface with the compressor wheel. It relates to the surface treatment of the contact surface.

従来のガスタービン圧縮機動翼部品の構成では、圧縮機ホイールとの接触面で裸つまり無処理の圧縮機動翼が用いられることがある。例えば、圧縮機の圧縮機動翼は、ＣｒＭｏＶホイールなどの圧縮機ホイールと接触又は境界を画していることがある。こうした接触領域は、部品間の接触応力が高い領域である。こうした応力は、例えばフレッティングや磨耗などの弊害を招きかねない。こうした弊害を放置すると、部品の故障、関連ガスタービン装置の停止を招来しかねない。   In a conventional gas turbine compressor blade component configuration, a bare or untreated compressor blade may be used on the contact surface with the compressor wheel. For example, a compressor blade of a compressor may contact or delimit a compressor wheel such as a CrMoV wheel. Such a contact region is a region where contact stress between parts is high. Such stress can lead to adverse effects such as fretting and wear. If such adverse effects are left unattended, it may lead to component failure and related gas turbine equipment shutdown.

米国特許第４５９５３４０号明細書US Pat. No. 4,595,340

本発明の一実施形態では、グラファイト系固体薄膜潤滑材料を含む、ターボ機械用のコーティングを提供する。   In one embodiment of the present invention, a coating for a turbomachine comprising a graphite-based solid thin film lubricating material is provided.

本発明の別の実施形態では、グラファイト系固体薄膜潤滑材料を含むターボ機械用のコーティングであって、ターボ機械がスロットを有するホイールと、ダブテールを有するバケットとを少なくとも備えており、上記コーティングが、スロットとダブテールの少なくとも一方に施工されており、上記コーティングが、グラファイト系ドライフィルム潤滑剤、金属充填樹脂系、グラファイトとケイ酸塩バインダー、及び高温潤滑添加剤の少なくとも１種を含む、ターボ機械用のコーティングを提供する。   In another embodiment of the invention, a coating for a turbomachine comprising a graphite-based solid thin film lubricant material, wherein the turbomachine comprises at least a wheel having a slot and a bucket having a dovetail, the coating comprising: For turbomachinery, wherein the coating is applied to at least one of a slot and a dovetail, and the coating includes at least one of a graphite-based dry film lubricant, a metal-filled resin system, graphite and a silicate binder, and a high-temperature lubricant additive Provide coating.

本発明のさらに別の実施形態では、隙間腐食耐性及びフレッティング耐性の少なくとも一方をもたらすためのターボ機械のコーティング方法であって、当該方法が、コーティングを準備し、かつスロット及びタブテールの少なくとも一方にコーティングを施工することを含んでおり、上記コーティングがグラファイト系固体薄膜潤滑材料を含んでおり、上記ターボ機械が、スロットを有するホイールと、ダブテールを有するバケットとを少なくとも備えており、上記コーティングが、グラファイト系ドライフィルム潤滑剤、金属充填樹脂系、グラファイトとケイ酸塩バインダー、及び高温潤滑添加剤の少なくとも１種を含む、方法を提供する。   In yet another embodiment of the present invention, a turbomachine coating method for providing at least one of crevice corrosion resistance and fretting resistance, the method comprising providing a coating and at least one of a slot and a tab tail. Applying a coating, wherein the coating includes a graphite-based solid thin film lubricant material, and wherein the turbomachine comprises at least a wheel having a slot and a bucket having a dovetail, the coating comprising: A method is provided comprising at least one of a graphite-based dry film lubricant, a metal-filled resin system, graphite and a silicate binder, and a high temperature lubricant additive.

本発明の上記その他の特徴、態様及び利点については、図面と併せて以下の詳細な説明を参照することによって理解を深めることができるであろう。図面を通して、同様の部材には同様の符号を付した。   These and other features, aspects and advantages of the present invention may be better understood by reference to the following detailed description taken in conjunction with the drawings in which: Throughout the drawings, like reference numerals are used for like members.

本発明の実施形態として具体化し得るバランス調整具を有するタービン又は圧縮機ディスクの一部の斜視図。1 is a perspective view of a portion of a turbine or compressor disk having a balance adjuster that may be embodied as an embodiment of the present invention. 本発明の実施形態として具体化し得る、隣接する段の集成後にバランスウェイトを挿入することのできる２つの隣接する圧縮機段の一部の側面図。FIG. 3 is a side view of a portion of two adjacent compressor stages in which a balance weight can be inserted after the assembly of adjacent stages that can be embodied as an embodiment of the present invention. 本発明の実施形態として具体化し得る、隣接する段の集成後にバランスウェイトを挿入することのできる２つの隣接する圧縮機段の一部の別の側面図。FIG. 4 is another side view of a portion of two adjacent compressor stages in which a balance weight can be inserted after the assembly of adjacent stages that can be embodied as an embodiment of the present invention.

本発明は、ターボ機械全般、特にガスタービン又は蒸気タービンのタービンホイール及び圧縮機ホイールに幅広い用途を有するが、以下の説明では、説明の便宜上、ガスタービン又は蒸気タービンの圧縮機段に関する実施形態について説明する。これらの記載は本願発明の技術的範囲を限定するものではない。   Although the present invention has broad application to turbomachines in general, particularly turbine and compressor wheels of gas turbines or steam turbines, in the following description, for convenience of explanation, embodiments relating to compressor stages of gas turbines or steam turbines will be described. explain. These descriptions do not limit the technical scope of the present invention.

圧縮機段は、軸方向シャフトに装着又は一体に形成されるホイール又はディスクを備えるように製造される。雌ダブテールがホイールの表面に機械加工され、圧縮機動翼の雄ダブテール部分が雌ダブテールに嵌め込まれる。   The compressor stage is manufactured with a wheel or disk mounted on or integrally formed with the axial shaft. A female dovetail is machined into the wheel surface and the male dovetail portion of the compressor blade is fitted into the female dovetail.

図１に、圧縮機の一部、例えばガスタービンエンジンの圧縮機の一部を示す。圧縮機１０は、入口、第１段動翼ディスクアセンブリ１２、複数のステータ静翼１４とを備えており、第１段動翼ディスクアセンブリ１２は、エンジン又は圧縮機の長手方向中心線１６を中心として、ステータ静翼１４の上流にステータ静翼１４と同軸に配置されている。動翼ディスクアセンブリ１２は、ロータホイール又はロータディスク２０の周方向に離隔して植設された複数のロータ動翼１８を有する。   FIG. 1 shows a part of a compressor, for example, a part of a compressor of a gas turbine engine. The compressor 10 includes an inlet, a first stage blade disk assembly 12, and a plurality of stator vanes 14, the first stage blade disk assembly 12 centering on a longitudinal centerline 16 of the engine or compressor. The stator vane 14 is arranged coaxially with the stator vane 14 upstream of the stator vane 14. The rotor disk assembly 12 includes a plurality of rotor rotor blades 18 that are spaced apart from each other in the circumferential direction of the rotor wheel or the rotor disk 20.

さらに具体的には、図１及び図２に示すように、動翼１８は、先端２４と根元２６と前縁２８と後縁３０とを有する比較的薄い中実の翼形部２２を有する。動翼１８は、さらに、翼形部根元２６から横方向外側に張り出した略矩形のプラットフォーム３２も有する。プラットフォーム３２は、前縁２８から後縁３０に向かって、先端２４に向けて上向きに比較的急な傾斜をもち、圧縮機１０内の内側空気流の境界を画成する。プラットフォーム３２は、上流側の前端３４と下流側の後端３６とを有しており、後端３６は前端３４よりも大きな半径で配設される。動翼１８は、プラットフォーム３２から翼形部２２と同軸に延在するシャンク３８と、シャンク３８から延在する従来形状の軸方向挿入式ダブテール４０も有する。動翼１８は、タービン動翼に適した任意の材料から形成し得る。例えば、圧縮機動翼は、グラファイト、グラファイト含有材料、その他の炭素繊維材料の１種以上を含んでいてもよい。   More specifically, as shown in FIGS. 1 and 2, the blade 18 has a relatively thin solid airfoil 22 having a tip 24, a root 26, a leading edge 28 and a trailing edge 30. The blade 18 also has a generally rectangular platform 32 that projects laterally outward from the airfoil root 26. The platform 32 has a relatively steep slope upward from the leading edge 28 toward the trailing edge 30 and toward the tip 24 to define the inner air flow boundary within the compressor 10. The platform 32 has an upstream front end 34 and a downstream rear end 36, and the rear end 36 is disposed with a larger radius than the front end 34. The blade 18 also has a shank 38 that extends coaxially with the airfoil 22 from the platform 32 and a conventionally shaped axial insertion dovetail 40 that extends from the shank 38. The blade 18 may be formed from any material suitable for a turbine blade. For example, the compressor blade may include one or more of graphite, graphite-containing material, and other carbon fiber materials.

また、本発明の実施形態では、ターボ機械の動翼１８は、析出硬化性ニッケル基合金（インコネル７１８）のような超合金又はステンレス鋼などの素材から形成することもできる。   In the embodiment of the present invention, the rotor blade 18 of the turbomachine may be formed of a material such as a superalloy such as a precipitation hardening nickel base alloy (Inconel 718) or stainless steel.

ホイール又はディスク２０は、その外周４４に、動翼ダブテール４０と相補的な形状の複数の軸方向スロット４２が周方向に離隔して設けられており、そこに、ダブテール４０が挿入されて動翼１８が取り付けられる。空気４６が動翼１８及び静翼１４を通過するように導かれ、それらによって圧縮される。   The wheel or disk 20 is provided with a plurality of axial slots 42 that are complementary to the blade dovetail 40 on the outer periphery 44 and spaced apart in the circumferential direction, and the dovetail 40 is inserted into the blade or disk 20. 18 is attached. Air 46 is directed through the blade 18 and stationary blade 14 and is compressed by them.

タービンロータ及び動翼ディスクアセンブリ１２が回転する際に、ホイールスロット４２内での部品の運動と併せて圧縮機の動翼ダブテール４０とホイール２０との接触応力が発生する。こうした接触応力は、動翼ディスクアセンブリ１２に高接触応力フレッティング及び磨耗を生じるおそれがある。そこで、本発明の実施形態では、接触面の摩擦係数を低下させそれらの間のフレッティングを低減すべく、コーティングを動翼ディスクアセンブリ１２とスロット４２の少なくとも一方に施工する。   As the turbine rotor and blade disk assembly 12 rotates, contact stresses between the compressor blade dovetail 40 and the wheel 20 occur along with the movement of the parts in the wheel slot 42. Such contact stresses can cause high contact stress fretting and wear on the blade disk assembly 12. Thus, in an embodiment of the present invention, a coating is applied to at least one of the blade disk assembly 12 and the slot 42 to reduce the coefficient of friction of the contact surfaces and reduce fretting therebetween.

好ましくは、コーティング５０は、スロット４２内の動翼ディスクアセンブリ１２の表面に施工されるが、コーティング５０をホイールスロット４２に設けてもよい。コーティング５０は、動翼ディスクアセンブリ１２及び／又はスロット４２の隣接面の一方又は両方に施工できる。   Preferably, the coating 50 is applied to the surface of the blade disk assembly 12 in the slot 42, but the coating 50 may be provided in the wheel slot 42. The coating 50 can be applied to one or both of the blade disk assembly 12 and / or the adjacent surface of the slot 42.

しかし、動翼ディスクアセンブリ１２又はホイール２０を構成する材料（例えば二相ステンレス鋼を含む材料）にコーティングを施工するのは、これらの部品の幾何形状から難しいことがある。例えば、ある種のコーティングは、かかる材料で隙間腐食の問題を起こすことがある。そこで、本発明の実施形態では、コーティング５０は、グラファイト系固体薄膜潤滑コーティングを含む。さらに、コーティング５０は、動翼ディスクアセンブリ１２とホイールスロット４２の少なくとも一方に施工することのできる１種以上のグラファイト系ドライフィルム潤滑剤又は金属充填樹脂系を含んでいてもよい。これらのコーティング材料は、本発明の実施形態では、摩擦係数を低下させ、動翼ディスクアセンブリ１２とホイールスロット４２の間の磨耗を低減するために用いることができる。   However, it may be difficult to apply a coating to the material comprising the blade disk assembly 12 or the wheel 20 (eg, material including duplex stainless steel) due to the geometry of these parts. For example, certain coatings can cause crevice corrosion problems with such materials. Thus, in an embodiment of the present invention, the coating 50 includes a graphite-based solid thin film lubricating coating. Furthermore, the coating 50 may include one or more graphite-based dry film lubricants or metal-filled resin systems that can be applied to at least one of the blade disk assembly 12 and the wheel slot 42. These coating materials can be used in embodiments of the present invention to reduce the coefficient of friction and reduce wear between the blade disk assembly 12 and the wheel slot 42.

コーティング５０は、本発明の実施形態では、フレッティング耐性及び隙間腐食耐性の少なくとも一方をもたらす。   The coating 50 provides at least one of fretting resistance and crevice corrosion resistance in embodiments of the present invention.

コーティング５０はグラファイト材料を含んでおり、コーティングがグラファイトグリースを含んでいることも本発明の技術的範囲に属する。さらに、コーティング５０は、本願発明の実施形態では、モリブデングリースを単独で又は他のグラファイト系固体薄膜潤滑コーティングとの組合せで含んでいてもよい。   The coating 50 includes a graphite material, and it is within the scope of the present invention for the coating to include graphite grease. Furthermore, the coating 50 may include molybdenum grease alone or in combination with other graphite-based solid thin film lubricating coatings in embodiments of the present invention.

例えば、本発明の実施形態では、コーティング用の材料としては、特に限定されないが、潤滑剤、ドライ潤滑剤、適当な溶剤に添加した潤滑剤及び結合剤、油溶性スルホン酸界面活性剤／浸潤剤（例えば、ＨＯＨＭＡＮ ＰＬＡＴＩＮＧ ＆ ＭＦＧ社のＳｕｒｆＫｏｔｅ（登録商標）ＬＯＢ−１８００−Ｇ）、チタン含有潤滑剤（例えば、Ｔｉｏｄｉｚｅ社のＡｌｕｍａｚｉｔｅ ＺＤＡ）及びこれらの組合せが挙げられる。一般に、コーティングは潤滑剤を含んでおり、所望の材料特性を与える他の成分との組合せることもできる。例えば、ある例示的なコーティング材料は、グラファイトと共にケイ酸塩バインダー及びその他の高温潤滑剤を含んでいてもよい。動翼の用途、動翼の環境及び関連ターボ機械に応じて、他の添加剤が望ましいこともある。   For example, in the embodiment of the present invention, the coating material is not particularly limited, but is a lubricant, a dry lubricant, a lubricant and a binder added to an appropriate solvent, an oil-soluble sulfonic acid surfactant / wetting agent. (E.g., SurfKote (R) LOB-1800-G from HOHMAN PLATING & MFG), titanium-containing lubricants (e.g., Alumazete ZDA from Tiodize) and combinations thereof. Generally, the coating contains a lubricant and can be combined with other ingredients that provide the desired material properties. For example, an exemplary coating material may include a silicate binder and other high temperature lubricants along with graphite. Other additives may be desirable depending on the blade application, blade environment, and associated turbomachinery.

本発明の実施形態では、コーティング５０は、好ましくは、ホイールスロット４２と接触する動翼１８の圧縮機動翼ダブテール４０に施工される。ただし、コーティング５０は、必要に応じて、ダブテール４０及び／又はスロット４２のいずれの圧力面に施工してもよい。   In an embodiment of the invention, the coating 50 is preferably applied to the compressor blade dovetail 40 of the blade 18 that contacts the wheel slot 42. However, the coating 50 may be applied to any pressure surface of the dovetail 40 and / or the slot 42 as required.

本発明の実施形態では、コーティング５０は約０．０００５〜約０．００２インチの範囲の膜厚で施工される。コーティング５０は、ダブテール母金属／基材の磨耗、固着、フレッティングを防止することができる厚さに施工すればよい。   In an embodiment of the invention, coating 50 is applied with a film thickness in the range of about 0.0005 to about 0.002 inches. The coating 50 may be applied to a thickness that can prevent dovetail base metal / substrate wear, sticking, and fretting.

本発明の実施形態では、コーティング５０は、適当な塗工法で施工すればよい。塗工法の例としては、塗装、物理気相堆積法、プラズマ励起化学気相堆積法、化学堆積法などの堆積法、エッチング、化学スパッタリングのようなスパッタリング、粉末塗工、大気プラズマ溶射、低温スプレー、電気めっき及びこれらの組合せが挙げられる。   In the embodiment of the present invention, the coating 50 may be applied by an appropriate coating method. Examples of coating methods include: coating, physical vapor deposition, plasma-enhanced chemical vapor deposition, chemical deposition, etc., etching, sputtering such as chemical sputtering, powder coating, atmospheric plasma spraying, low temperature spraying Electroplating and combinations thereof.

従来のターボ機械では、裸の圧縮機動翼が、Ｃｒ−Ｍｏ−Ｖ鋼製のホイールと高い接触応力で押し合って、多くの弊害の中でも、特に過度のフレッティング及び磨耗を招くおそれがあった。こうした過度のフレッティング及び磨耗を、対処せずに放置しておくと、周部品の故障、並びにターボ機械及びガスタービン装置の停止を招くことが判明した。本発明では、動翼ダブテールに設けられたコーティングは、磨耗を低減してターボ機械の部品寿命を延ばすのに効果的である。こうした改良によって、ガスタービン及び／又は圧縮機の信頼性も向上する。また、本発明において、動翼のコーティングは、ターボ機械の手が届き難い領域（例えば動翼を摺動・挿入させるタービンホイールスロットなど）をコーティングすることに比べると、簡単で経済的でしかも信頼性が高い。   In conventional turbomachines, bare compressor blades pressed against a wheel made of Cr-Mo-V steel with high contact stress, and among many adverse effects, there was a risk of excessive fretting and wear in particular. . It has been found that leaving such excessive fretting and wear unaccounted for can lead to peripheral component failure and turbomachine and gas turbine equipment shut down. In the present invention, the coating on the blade dovetail is effective in reducing wear and extending the life of the turbomachine component. Such improvements also improve the reliability of the gas turbine and / or compressor. In addition, in the present invention, the coating of the moving blade is simpler, more economical and more reliable than coating a region that is difficult to reach by the turbomachine (for example, a turbine wheel slot for sliding and inserting the moving blade). High nature.

本発明の実施形態では、コーティングを設けた動翼は、フレッティングの問題に対する解決策を提供し、隙間腐食は起こらなくなる。本発明のコーティング５０は、ある種のコーティングを設けると隙間腐食の問題を起こす難点のあるＧＴＤ４５０動翼のような、超合金基材に塗工することができる。コーティングを設けた動翼は、ターボ機械の作動の結果、高い接触応力を生じたとしても、設計通り高い接触応力で作動することができる。また、本発明のコーティングで被覆された部品の故障率は、被覆していないものよりも低くなる。   In embodiments of the present invention, the blade provided with a coating provides a solution to the fretting problem and crevice corrosion does not occur. The coating 50 of the present invention can be applied to a superalloy substrate, such as a GTD450 blade, which has the disadvantage of causing crevice corrosion problems when certain types of coatings are provided. The moving blade provided with the coating can operate with a high contact stress as designed even if a high contact stress is generated as a result of the operation of the turbomachine. Also, the failure rate of parts coated with the coating of the present invention is lower than those not coated.

以上、本発明の幾つかの特徴について説明してきたが、当業者には様々な修正及び変更が明らかであろう。したがって、特許請求の範囲は、これらの修正及び変更を本発明の技術的範囲に属するものとして包含する。   While several features of the invention have been described above, various modifications and changes will be apparent to those skilled in the art. Accordingly, the claims encompass these modifications and changes as belonging to the technical scope of the present invention.

Claims (13)

グラファイト系固体薄膜潤滑材料を含む、ターボ機械用のコーティング。   A coating for turbomachinery that includes a graphite-based solid thin film lubricant. 当該コーティングが、隙間腐食耐性及びフレッティング耐性の少なくとも一方をもたらす、請求項１記載のターボ機械用のコーティング。   The turbomachine coating of claim 1, wherein the coating provides at least one of crevice corrosion resistance and fretting resistance. 前記ターボ機械が、スロットを有するホイールと、ダブテールを有するバケットとを少なくとも備えており、当該コーティングが、スロットとダブテールの少なくとも一方に施工される、請求項１記載のターボ機械用のコーティング。   The coating for a turbomachine according to claim 1, wherein the turbomachine includes at least a wheel having a slot and a bucket having a dovetail, and the coating is applied to at least one of the slot and the dovetail. 当該コーティングがダブテールに施工される、請求項３記載のターボ機械用のコーティング。   The turbomachinery coating of claim 3, wherein the coating is applied to the dovetail. 前記ターボ機械が超合金材料からなる、請求項３記載のターボ機械用のコーティング。   The coating for turbomachinery according to claim 3, wherein the turbomachine is made of a superalloy material. 当該コーティングが、グラファイト系ドライフィルム潤滑剤をむ、請求項１記載のターボ機械用のコーティング。   The turbomachinery coating of claim 1, wherein the coating comprises a graphite-based dry film lubricant. 当該コーティングが金属充填樹脂系を含む、請求項１記載のターボ機械用のコーティング。   The turbomachinery coating of claim 1, wherein the coating comprises a metal-filled resin system. 当該コーティングが、グラファイトとケイ酸塩バインダー及び高温潤滑添加剤の少なくとも１種類をさらに含む、請求項１記載のターボ機械用のコーティング。   The turbomachine coating of claim 1, wherein the coating further comprises at least one of graphite and a silicate binder and a high temperature lubricating additive. グラファイト系固体薄膜潤滑材料を含むターボ機械用のコーティングであって、ターボ機械がスロットを有するホイールと、ダブテールを有するバケットとを少なくとも備えており、当該コーティングが、スロットとダブテールの少なくとも一方に施工されており、当該コーティングが、グラファイト系ドライフィルム潤滑剤、金属充填樹脂系、グラファイトとケイ酸塩バインダー、及び高温潤滑添加剤の少なくとも１種を含む、ターボ機械用のコーティング。   A coating for a turbomachine comprising a graphite-based solid thin film lubricant material, the turbomachine comprising at least a wheel having a slot and a bucket having a dovetail, wherein the coating is applied to at least one of the slot and the dovetail. A coating for a turbomachine, wherein the coating comprises at least one of a graphite-based dry film lubricant, a metal-filled resin system, graphite and a silicate binder, and a high-temperature lubricant additive. 当該コーティングがダブテールに施工される、請求項９記載のターボ機械用のコーティング。   The turbomachinery coating of claim 9, wherein the coating is applied to the dovetail. 前記ターボ機械が超合金材料からなる、請求項９記載のターボ機械用のコーティング。   The coating for a turbomachine according to claim 9, wherein the turbomachine is made of a superalloy material. 当該コーティングが、隙間腐食耐性及びフレッティング耐性の少なくとも一方をもたらす、請求項９記載のターボ機械用のコーティング。   The coating for turbomachinery according to claim 9, wherein the coating provides at least one of crevice corrosion resistance and fretting resistance. 隙間腐食耐性及びフレッティング耐性の少なくとも一方をもたらすためのターボ機械のコーティング方法であって、当該方法が、
コーティングを準備し、かつ
スロット及びタブテールの少なくとも一方にコーティングを施工する
ことを含んでおり、上記コーティングがグラファイト系固体薄膜潤滑材料を含んでおり、上記ターボ機械が、スロットを有するホイールと、ダブテールを有するバケットとを少なくとも備えており、上記コーティングが、グラファイト系ドライフィルム潤滑剤、金属充填樹脂系、グラファイトとケイ酸塩バインダー、及び高温潤滑添加剤の少なくとも１種を含む、方法。 A turbomachine coating method for providing at least one of crevice corrosion resistance and fretting resistance, the method comprising:
Providing a coating and applying a coating to at least one of the slot and the tab tail, wherein the coating includes a graphite-based solid thin film lubricant material, and the turbomachine includes a slotted wheel and a dovetail. And a coating comprising at least one of a graphite-based dry film lubricant, a metal-filled resin system, graphite and a silicate binder, and a high temperature lubricant additive.
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