EP1458981A1 - Compresseur pour turbines a gaz - Google Patents

Compresseur pour turbines a gaz

Info

Publication number
EP1458981A1
EP1458981A1 EP02803485A EP02803485A EP1458981A1 EP 1458981 A1 EP1458981 A1 EP 1458981A1 EP 02803485 A EP02803485 A EP 02803485A EP 02803485 A EP02803485 A EP 02803485A EP 1458981 A1 EP1458981 A1 EP 1458981A1
Authority
EP
European Patent Office
Prior art keywords
layers
compressor
layer
coating
hardness
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.)
Granted
Application number
EP02803485A
Other languages
German (de)
English (en)
Other versions
EP1458981B1 (fr
Inventor
Francisco Blangetti
Harald Reiss
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1458981A1 publication Critical patent/EP1458981A1/fr
Application granted granted Critical
Publication of EP1458981B1 publication Critical patent/EP1458981B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/007—Preventing corrosion
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/224—Carbon, e.g. graphite
    • 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
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • 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
    • F05D2300/506—Hardness
    • 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
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/604—Amorphous
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/30—Self-sustaining carbon mass or layer with impregnant or other layer

Definitions

  • the invention relates to a compressor for gas turbines and in particular to a coating for protection against liquid drops and solid particles, which is applied to the surfaces of components in the inlet region of the compressor.
  • the components of compressors in turbines are exposed to various particles during compressor operation, which can permanently damage the surfaces of the components.
  • These particles include liquid drops, including water drops, as well as solid particles such as dust particles that get into the compressor with the air drawn in.
  • solid particles such as dust particles that get into the compressor with the air drawn in.
  • ice particles that can form due to desublimation due to the cooling of the air due to the acceleration of the air.
  • the components in the inlet area of the compressor particularly affect the blading of potential damage caused by these particles.
  • Drop erosion is caused, on the one hand, directly by the sprayed or sucked-in liquid drops on the surfaces of the components.
  • the sprayed drops are initially small, ie in the range of 10-20 micrometers in diameter. After a certain operating time, however, the spray nozzles are worn out in such a way that the drops they spray gradually reach a size of up to 100 micrometers in diameter.
  • a compressor for a gas turbine according to the invention has components, such as, for example, the blades, which are provided on their surfaces with a coating which contains at least two layers of an amorphous carbon or a plasma polymer.
  • the outermost layer of the coating has, in particular, hydrophobic properties.
  • All layers or layer systems with a low interfacial energy are suitable, provided that they are smaller than the surface tension of water.
  • these layers also have the surface hardness inherently high for amorphous carbon or a plasma polymer, for example from 500 to 3000 HV.
  • amorphous carbon or a plasma polymer is particularly suitable for materials with hydrophobic properties and also hardnesses of this size.
  • the hydrophobic property of the outermost layer prevents wetting of the surfaces. Impacting liquid drops interact very little with the surface because their interfacial energy is low. As a result, the liquid drops do not adhere to the surfaces, rather they roll over the surface while maintaining their small size and without merging with other drops or even a closed one
  • Hydrophobic layers such as those made of amorphous carbon also have dirt-repellent properties.
  • the fact that the liquid drops roll off immediately prevents a chemical interaction of the liquid or of components which are dissolved in the liquid with the surface. This then also avoids the deposition of other foreign material, which has a positive effect on the gas turbine performance and the service life of the coated components.
  • the components of the compressor have a protective coating which has a layer sequence with a layer pair or several layer pairs, the inner layer of a layer pair having a higher hardness compared to the outer layer of the layer pair and the outer one being relatively has low hardness.
  • the inner layer of the pair of layers has a hardness of 1500 to 3000 HV and the outer layer has a hardness of 500 HV to 1500 HV.
  • the individual layers of the layer sequence have thicknesses in the range from 0.1 to 2 micrometers each.
  • the thicknesses of the individual layers of the layer sequence are inversely related to their relative hardness.
  • the outer layer can have a thickness of 1.0 to 1.5 micrometers and the inner layer can have a thickness of 0.5 to 0.75 micrometers.
  • the surfaces of the components of the compressor have an adhesive layer on which one or more pairs of layers are applied.
  • an adhesive layer for example, a harder layer applied to titanium, which corresponds to the inner layer mentioned above, is suitable as the adhesive layer.
  • the hydrophobic coating contains amorphous carbon.
  • amorphous carbon in the following, this should be understood to mean hydrogen-containing carbon layers with a hydrogen content of 10 to 50 at% and with a ratio of sp 3 to sp 2 bonds between 0.1 to 0.9.
  • all amorphous or dense carbon layers produced by means of carbon or hydrocarbon precursors, as well as plasma polymer layers, polymer-like or dense carbon and hydrocarbon layers can be used, provided that they provide the hydrophobic and the mechanical or chemical properties of the amorphous carbon mentioned below Have production of individual layers or layer sequences.
  • Amorphous carbon also known as diamond-like carbon, is generally known for its exceptional hardness, chemical stability and also for its elasticity.
  • amorphous carbon has a low surface energy compared to the surface tension of water, so that a hydrophobic or water-repellent property is brought about.
  • the hardness of amorphous carbon can be changed by varying the parameters for the production of a coating.
  • a layer of relatively lower hardness is only to be understood as less hard compared to a hard layer.
  • a less hard layer in particular has a pronounced hydrophobic property.
  • the coating according to the invention can be implemented using various, generally known production processes, such as, for example, deposition by means of glow discharge in a plasma from hydrocarbon-containing precursors, ion beam coating and sputtering of carbon in hydrogen-containing working gas.
  • the substrate is exposed to a current of ions of several 100 eV.
  • the substrate is arranged in a reactor chamber in contact with a cathode, which is capacitively connected to a 13.56 MHz RF generator.
  • the grounded walls of the plasma chamber form a large counter electrode.
  • any hydrocarbon vapor or hydrocarbon gas can be used as the first working gas for the coating.
  • various gases are added to the first working gas.
  • nitrogen fluorine or silicon-containing gases, for example, high or low surface energies are achieved.
  • the addition of nitrogen also leads to an increase in the hardness of the resulting layer.
  • the resulting hardness of the layer can be controlled by changing the bias voltage across the electrodes between 100 and 1000 V, with a high bias voltage increasing a hard, amorphous carbon layer and a deep stress leads to an amorphous carbon layer with relatively lower hardness.
  • the compressor according to the invention all components that come into contact with the intake air or with injected liquids are provided with the layer sequence.
  • the components in the inlet area such as the blading and the bearing for the adjustable guide rail, are to be provided with it.
  • the invention is applicable to compressors for gas turbines of power plants of all kinds as well as turbine jet drives and other components in aircraft and ships, such as the leading edge of the wings of aircraft.
  • the components of the compressor according to the invention consist of materials such as titanium, stainless steels, chromium steels, aluminum and carbide formers.
  • the described sequence of layers with adhesive layer is perfectly suitable for application to these materials.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention concerne un compresseur destiné à une turbine à gaz présentant sur les surfaces de ses composants, notamment de ses ailettes, un revêtement destiné à protéger les surfaces de l'érosion. Le revêtement comprend au moins deux couches ou plusieurs paires de couches en carbone amorphe ou en plasmapolymère, les couches ayant une dureté intrinsèquement élevée et la couche externe du revêtement ayant des propriétés hydrophobes. La dureté d'une couche interne d'une paire de couche est encore plus élevée que celle de la couche externe. Le revêtement convient en particulier pour éviter l'érosion par l'abattement de gouttes de liquide, l'érosion par des particules solides telles que la glace, ainsi que l'encrassement résultant du dépôt de particules de poussière et de composantes dissoutes dans des liquides. Le revêtement permet d'augmenter la longévité des composants et la puissance de la turbine.
EP02803485A 2001-11-19 2002-11-12 Compresseur pour turbines a gaz Expired - Lifetime EP1458981B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH21252001 2001-11-19
CH212501 2001-11-19
PCT/IB2002/004745 WO2003044374A1 (fr) 2001-11-19 2002-11-12 Compresseur pour turbines a gaz

Publications (2)

Publication Number Publication Date
EP1458981A1 true EP1458981A1 (fr) 2004-09-22
EP1458981B1 EP1458981B1 (fr) 2005-07-20

Family

ID=4567609

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02803485A Expired - Lifetime EP1458981B1 (fr) 2001-11-19 2002-11-12 Compresseur pour turbines a gaz

Country Status (6)

Country Link
US (1) US7083389B2 (fr)
EP (1) EP1458981B1 (fr)
JP (1) JP2005518490A (fr)
AU (1) AU2002366009A1 (fr)
DE (1) DE50203708D1 (fr)
WO (1) WO2003044374A1 (fr)

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DE50203708D1 (de) 2001-11-19 2005-08-25 Alstom Technology Ltd Baden Verdichter für gasturbinen
GB2382847A (en) 2001-12-06 2003-06-11 Alstom Gas turbine wet compression
GB2382848A (en) 2001-12-06 2003-06-11 Alstom Gas turbine wet compression
US7247348B2 (en) * 2004-02-25 2007-07-24 Honeywell International, Inc. Method for manufacturing a erosion preventative diamond-like coating for a turbine engine compressor blade
CN1296517C (zh) * 2004-10-14 2007-01-24 北京工业大学 后续表面氟化处理的非晶碳薄膜疏水材料的制备方法
JP4611914B2 (ja) * 2006-02-28 2011-01-12 トーカロ株式会社 圧縮機翼及びその製造方法、並びに、火力発電用ガスタービン
JP2007327349A (ja) * 2006-06-06 2007-12-20 Tocalo Co Ltd 送液ポンプ用部材及びその製造方法
EP1925782A1 (fr) * 2006-11-23 2008-05-28 Siemens Aktiengesellschaft Revêtement non-mouillable de composants de turbine à vapeur humide
DE102007042124A1 (de) * 2007-09-05 2009-03-12 Lufthansa Technik Ag Triebwerksbauteil für eine Gasturbine
ES2652031T3 (es) 2008-06-12 2018-01-31 General Electric Company Compresor centrífugo para entornos de gas húmedo y procedimiento de fabricación
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JP5244495B2 (ja) * 2008-08-06 2013-07-24 三菱重工業株式会社 回転機械用の部品
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FR3003539B1 (fr) 2013-03-22 2016-04-15 European Aeronautic Defence & Space Co Eads France Structure anti-erosion pour aeronefs
US20140321976A1 (en) * 2013-04-26 2014-10-30 Sol-Electrica, Llc Modular thermal molecular adhesion turbine
CN106536860B (zh) 2014-04-09 2019-01-11 诺沃皮尼奥内股份有限公司 保护涡轮机的构件免受液滴侵蚀的方法、构件及涡轮机
WO2017222516A1 (fr) * 2016-06-22 2017-12-28 Siemens Aktiengesellschaft Procédé et système permettant de réduire des dommages dus à des impacts de gouttelettes de liquide par des surfaces superhydrophobes
WO2018106539A1 (fr) 2016-12-05 2018-06-14 Cummins Filtration Ip, Inc. Ensemble de séparation comprenant une turbine à impulsion en une seule pièce
WO2018129438A1 (fr) * 2017-01-09 2018-07-12 Cummins Filtration Ip, Inc. Turbine à impulsions avec surface non mouillante pour une efficacité hydraulique améliorée
WO2019103799A1 (fr) * 2017-11-21 2019-05-31 Bl Technologies, Inc. Amélioration du rendement d'une centrale à vapeur avec de nouveaux traitements de cycle de vapeur
US12030063B2 (en) 2018-02-02 2024-07-09 Cummins Filtration Ip, Inc. Separation assembly with a single-piece impulse turbine
WO2019204265A1 (fr) 2018-04-17 2019-10-24 Cummins Filtration Ip, Inc. Ensemble de séparation comprenant une turbine à impulsion à deux pièces
US11015474B2 (en) * 2018-10-19 2021-05-25 Raytheon Technologies Corporation Geometrically segmented abradable ceramic thermal barrier coating with improved spallation resistance
JP7146582B2 (ja) * 2018-11-08 2022-10-04 キヤノン株式会社 液体吐出ヘッド

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Also Published As

Publication number Publication date
DE50203708D1 (de) 2005-08-25
EP1458981B1 (fr) 2005-07-20
WO2003044374A1 (fr) 2003-05-30
US7083389B2 (en) 2006-08-01
US20040213675A1 (en) 2004-10-28
AU2002366009A1 (en) 2003-06-10
JP2005518490A (ja) 2005-06-23

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