• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    According to the invention, a coating method is provided. The coating method includes providing a turbine component (105), applying a coating-repellent material (101) to a predetermined region (104) of the turbine component (105), and applying a coating material (102) to the turbine component. The coating-repellent material (101) rejects the coating material (102) from the predetermined region (104) of the turbine component (105) to at least partially form a channel. A coating method for a hot gas path turbine component and a coated product are also disclosed.
    公开号:CH708100B1
    申请号:CH00724/14
    申请日:2014-05-13
    公开日:2018-05-31
    发明作者:James Healy Michael；Wesley Harris John Jr
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Description Field of the Invention The present invention relates to coating methods and coated parts for turbine components. More specifically, this invention relates to heat-seal coating processes and to parts having a heat-insulating layer for turbine components.
    Background of the Invention Temperature limits of the materials of turbine components present a limit to increasing turbine operating temperatures, and hence turbine efficiency. The limitations of the cooling capabilities of such turbine components are an aspect that leads to such temperature limits. For example, the absence of adequate cooling and / or operation at or above predetermined temperatures may result in fatigue due to thermal expansion and contraction of the turbine components. In addition, turbine components are subject to a temperature profile that has a temperature gradient. The temperature profile and / or the temperature gradient may heat different portions of a turbine component at different rates, particularly during startup or shutdown of the operation. Such uneven heating may result in low load cycle fatigue, which is undesirable because it reduces the overall life of the turbine component.
    The formation of channels or grooves on the surface of the turbine component material may provide additional cooling to the component. However, it can be difficult to fabricate the near-surface cooling channels. Near-surface cooling channels may also cause difficulties in repairing the turbine component. In addition, the machining of grooves or channels extending through a coating to a base material may result in scoring and / or cutting of the base material. One method of making channels or channels extending through the coating to the base material involves the use of a jet of water. Adjusting the depth of the gutter with a jet of water can be difficult, often resulting in the gutter extending into the base material. In addition, machining the material can lead to undesirable characteristics, such as the inability to restore or repair the components that have already been machined.
    [0004] A turbine component coating process and a coated turbine component that do not suffer from one or more of the disadvantages mentioned above would be desirable in the art.
    Brief Description of the Invention The invention is defined by the independent claim.
    The coating-repellent material may be an elastomer, a silicone-based composite or a combination thereof.
    The coating method of any of the above-mentioned embodiments may have the feature that the coating material is an adhesive coating, a thermal barrier coating, or a combination thereof.
    The coating method of any of the above-mentioned embodiments may have the feature that the predetermined range of turbine components has a preformed channel.
    The coating method of any of the above-mentioned embodiments further has the feature of removing the coating-repellent material from the predetermined region of the turbine component.
    The coating method may further include the feature of removing the coating-repellent material with a lye agent.
    Alternatively, the coating method may further include the feature of removing the coating-repellent material using a release agent.
    Alternatively, the coating method may further include the feature of removing the coating-repellent material by heat.
    The above-mentioned coating method of any embodiment may have the feature that the removal of the coating-repellent material exposes a substrate surface.
    The coating method of any of the above-mentioned embodiments may further comprise machining cooling holes in the exposed substrate surface within the channel.
    The coating method of any of the above-mentioned embodiments may have the feature that the application of the coating material takes place on an exposed portion of the adhesion coating.
    The coating method of any of the above-mentioned embodiments may have the feature that the door-bin component is a shroud.
    The coating method of any of the above-mentioned embodiments may have the feature that the turin component is a hot gas path turbine component.
    The coating method of any of the above-mentioned embodiments may have the feature that the hot gas path turbine component is a blade.
    The coating method of any of the above-mentioned embodiments may have the feature that the hot gas path turbine component is a vane.
    The coating method of any of the above-mentioned embodiments may have the feature that the tur-bin component comprises an alloy.
    The coating method of any of the above-mentioned embodiments may have the feature that the door-bin component contains metal.
    The coating method of any of the above-mentioned embodiments may have the feature that the turpentine component comprises a ceramic matrix composite.
    Other features and advantages of the present invention will become apparent from the following detailed description of the preferred embodiment taken in conjunction with the accompanying drawings which illustrate, by way of example, the principles of the invention.
    The features described in connection with the device can also be used in the method and vice versa.
    Brief description of the drawings [0025]
    1 is a perspective view of a turbine blade with a coating-repellent material according to one embodiment of the invention;
    FIG. 2 is a perspective view of a turbine shroud having a coating repellent material according to one embodiment of the invention; FIG.
    3 is a cross-sectional view of a coating-repellent tape according to an embodiment of the invention;
    4 is a cross-sectional view of a coating-repellent tape according to an embodiment of the invention;
    5 is a cross-sectional view of a coating-repellent tape according to an embodiment of the invention;
    6 is a cross-sectional view of a coating-repellent tape according to an embodiment of the invention;
    7 is a cross-sectional view of a coating-repellent tape according to an embodiment of the invention;
    Fig. 8 is a sectional view of a coating-repellent material in a channel according to an embodiment of the invention,
    Fig. 9 is a sectional view of a coating-repellent material in a channel according to an embodiment of the invention,
    10 is a perspective view of a coating repellent material in a channel according to an embodiment of the invention.
    Wherever possible, the same reference numbers will be used throughout the drawings to represent the same parts.
    DETAILED DESCRIPTION OF THE INVENTION A coating process for a coated turbine component will be exemplified. The embodiments of the present disclosure reduce scoring of a metal of a component, increase efficiency in channel fabrication, reduce the cost of channel fabrication, improve control of channel fabrication, increase exposure of the substrate material, or a combination thereof, in comparison to methods and parts that do not make use of one or more of the features described herein.
    Referring to FIGS. 1 and 2, a coating-repellent material 101 is applied to a predetermined region 104 of a turbine component 105. The predetermined area 104 includes a portion of a substrate surface 103. The substrate surface 103, as used herein, refers to the outermost surface of the turbine cup component 105 prior to application of a coating material 102. The turbine component 105 is any suitable turbine component having film cooling, for example a turbine blade (or bucket), a vane, a shroud, a seal near the flowpath, a sidewall, a dovetail, or a combination thereof. Suitable materials for the turbine component 105 include, but are not limited to, a ceramic matrix composite, an alloy, a directionally solidified metal, a single crystal metal, an equiaxed metal, another suitable metal composition, or a combination thereof. Referring to FIG. 1, in one embodiment, the turbine component 105 is a hot gas path component such as, but not limited to, a turbine blade 110 (or blade), a vane, or a combination thereof. An appropriate position for the predetermined portion 104 of the turbine component 105 includes, but is not limited to, a suction side 123, a pressure side 122, a leading edge 120, a trailing edge 121, a sidewall, a platform, or a combination thereof.
    Referring to FIG. 2, in one embodiment, the turbine component 105 is a gas turbine component, such as but not limited to a shroud 210. The shroud 210 includes at least a forward section 220, a rearward section 221, a first edge 222 and a second edge 223.
    Referring to Figs. 1 and 2, the coating material 102 is applied to the turbine component 105. The coating-repellent material 101 rejects the coating material 102 from the predetermined region 104, whereby a channel 106 is formed in the turbine component 105. The channel 106 extends through the coating material 102 to the Substratflche 103. The removal of the coating-repellent material 101 exposes the channel 106. In one embodiment, the predetermined region 104 has a preformed channel in the substrate surface 103 of the turbine component 105.
    In one embodiment, cooling holes are machined into the substrate surface 103 that is exposed through the channel 106 after the coating-repellent material 101 has been removed. In one embodiment, the cooling holes are machined into the substrate surface 103 and then covered by the coating-repellent material 101. The cooling holes may be machined using any suitable machining method including, but not limited to, water jet machining, EDM machining, electrochemical machining, laser drilling, or a combination thereof. In one embodiment, the coating-repellent material 101 is used to mask the turbine component 105.
    Referring to Figs. 3, 4, 5, 6 and 7, suitable geometries of the coating material 101 include longitudinal strips having geometric profiles, such as a rectangle, a circle 301, a square 302, a triangle 303, a quadrilateral four-sided body 304 or a combination thereof, but are not limited thereto. The elongated strips of the coating-repellent material 101 are applied to the predetermined region 104 over a length of the substrate surface 103. A suitable structure of the coating-repellent material 101 includes, but is not limited to, rigid, flexible, twisted, curved, straight, pieced (e.g., broken, apertured) segments, or a combination thereof.
    In one embodiment, the coating-repellent material 101 is a preformed material, such as a wire, a tube, a strip, a strand, a plate, or a combination thereof. The coating-repellent material 101 is bonded to the substrate surface 103 or rests on the substrate surface 103. Specifying the size and / or contour of the coating-repellent material 101 allows for improved adjustment of a depth of the channel 106. In one embodiment, the coating-repellent material 101 is applied to the substrate pre-determined portion of the turbine component 105 is applied and cured. Suitable curing methods of the antireflective material 101 include, but are not limited to, thermal curing, radiation curing, such as electron beam curing (EBC), or ultraviolet (UV) curing, catalytic curing, or a combination thereof. In one embodiment, the thermal cure includes heating the coating-repellent material 101 to 250 ° F (121 ° C) for 30 minutes. In general, suitable thermal curing temperatures are between about 100 ° F (38 ° C) and about 400 ° F (204 ° C) between about 150 ° F (66 ° C) and about 350 ° F (178 ° C), between about 200 ° F (93 ° C) and about 400 ° F (204 ° C), between about 200 ° F (93 ° C) and about 300 ° F (149 ° C), between about 225 ° F (107 ° C) and about 275 ° F ° F (135 ° C) or any combination, sub-combination, range or sub-range thereof, but are not limited thereto. Suitable thermal cure durations include, but are not limited to, between about 10 minutes and about 60 minutes, between about 10 minutes and about 50 minutes, between about 20 minutes and about 40 minutes, between about 25 minutes and about 35 minutes, or any combination, subcombination , any area or subarea thereof.
    The coating-repellent material 101 contains any material suitable for repelling the coating material 102. Suitable materials for the coating-repellent material 101 include, but are not limited to elastomeric, silicone-based composite materials or combinations thereof. One suitable material has the composition of between about 20% and about 30% methyl vinyl / di-methyl vinyl / vinyl terminated siloxane, between about 20% and about 30% vinyl silicone fluid, between about 15% and about 30% ground quartz, between about 3% and about 9% silanol-terminated PDMS, up to about 0.5% sodium aluminum sulfo-silicate, up to about 1% vinyl tris- (2-methoxy-ethoxy) silane, up to about 1% titanium dioxide, up to about 2% silica, up to about 1% Stoddard solvent, up to about 0.5% neodecanoic acid, rare earth salts, up to about 0.5% 2-ethylhexanoate a rare earth and up to about 0.2% magnesium ferrite.
    After curing, the position of the coating-repellent material 101 is maintained until the coating-repellent material 101 is removed. In one embodiment, the coating repellent material 101 is removed thermally or chemically using agents including, but not limited to, suds agents, release agents, release gels, solvents, heat, or combinations thereof. In one embodiment, the coating-repellent material 101 is partially or completely evaporated while the coating material 102 is applied so that at least a portion of the coating-repellent material is removed after the application has been completed. The removal of the coating-repellent material 101 opens a channel 106 and exposes the substrate surface 103 without scoring or cutting the substrate surface. After removal of the coating-repellent material 101, the channel 106 permits cooling of the turbine component 105, such as micro-cooling, near-wall cooling, and / or film cooling.
    In one embodiment, the coating material 102 includes one or more layers of the adhesion coating 402 and one or more layers of the thermal barrier coating (TWC) 401. The repelling of the adhesion coating 402 and / or the heat-seal coating 401 at least partially forms the channel 106 when the coating material 102 is applied. Referring to FIG. 8 (section AA in FIG. 1), in one embodiment, the coating-repellent material 101 extends away from the substrate surface 103 and forms a protruding portion 801. The protruding portion 801 facilitates removal of the coating-repellent material 101 in which it is removed provides an enlarged area for physically gripping the coating material 101.
    Referring to FIG. 9 (section AA in FIG. 1), in one embodiment, the coating-repellent material 101 is substantially in line with the coating material 102. An exposed portion 501 of the adhesion coating 402 is formed by passing the heat-seal coating 401 through the non-coating material 101 is rejected. In another embodiment, the exposed portion 501 of the adhesion coating 402 is covered by additional application of a heat-seal coating 401. The covering of the exposed portion 401 of the adhesion coating 402 reduces wear and / or degradation of the bond coat 402 during use of the turbine component 105. In addition, the shape, geometry, position, size, length, thickness, or thickness Diameter of the coating-repellent material as 101, or a combination thereof, the shape of the channel 106 (see for example Fig. 10).
    In one embodiment, the bond coat 402 is applied to the substrate surface 403 of the turbine component 105 while being rejected by the coating repellent material 101. In one embodiment, the heat seal coating 401 is applied to the substrate surface 103 and no bond coat 402 is applied to the substrate surface 103 of the turbine component 105. Suitable compositions of bond coat 402 include but are not limited to FeCrAlY, CoCrAlY, NiCrAlY, or a combination thereof.
    In one embodiment, the thermal barrier coating 401 is applied to the adhesion coating 402, being rejected by the coating-repellent material 101. In one embodiment, the adhesion coating 402 is applied to the substrate surface 103 and the heat seal coating 401 is not applied to the substrate surface 103 of the turbine component 105. Suitable compositions of the heat seal coating 401 include, but are not limited to, Y203 stabilized ZrO 2, any yttrium-stabilized zirconium, or a combination thereof.
    While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes may be made and elements may be substituted with equivalents without departing from the scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the scope of the invention. Therefore, it is intended that the invention not be limited by the specific embodiments described, as the preferred embodiment for carrying out the invention, but that the invention includes all embodiments, which are within the scope of the appended patent claims.
    A coating method and a coated product are provided. The coating process includes providing a turbine component, applying a coating-repellent material to a predetermined region of the turbine component, and applying a coating material to the turbineene component. The coating-repellent material rejects the coating material from the predetermined region of the turbine component to at least partially form a channel. A coating method for a hot gas path turbine component and a coated product are also disclosed.
    权利要求:
    Claims (7)
    [1]
    claims
    A coating method, comprising: providing a turbine component; Applying or applying a coating-repellent material to a predetermined area of the turbineene component; Applying a coating material to the turbine component; wherein the coating-repellent material repels the coating material from the predetermined region of the turbine component to at least partially form a channel, and removing the coating-repellent material from the predetermined region of the turbine component.
    [2]
    The coating method of claim 1, wherein the coating-repellent material is an elastomer, a silicone-based composite, or a combination thereof.
    [3]
    The coating method according to claim 1 or 2, wherein the coating material is an adhesion coating, a heat-insulating coating or a combination thereof.
    [4]
    The coating method of any one of claims 1 to 3, wherein the predetermined portion of the turbine component has a preformed channel and / or the method further comprises machining cooling holes in the substrate surface exposed within the channel.
    [5]
    The coating method according to any one of claims 1 to 4, further comprising removing the coating-facing material with a lye agent and / or further removing the coating-repellent material by means of a release agent and / or further removing the coating-repellent material by means of heat and / or wherein removing the coating-repellent material exposes a substrate surface.
    [6]
    A coating method according to any one of claims 1 to 5, wherein the application of the coating material is to an exposed portion of an adhesion coating.
    [7]
    The coating method of claim 1, wherein the turbine component is a shroud or wherein the turbine component is a hot gas path turbine component or wherein the hot gas path turbine component is a blade or wherein the hot gas path turbine component is a vane.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP1828544B1|2011-06-22|Method to produce a component comprising an embedded channel and component
    DE602005005102T2|2009-03-26|High temperature smooth wear-resistant on-site repairable coating
    CH708100B1|2018-05-31|Coating process.
    DE102011057170A1|2012-07-05|Method for producing a film-cooled article
    EP1669545A1|2006-06-14|Coating system, use and method of manufacturing such a coating system
    DE102006028297A1|2007-12-27|Method of repairing inlet coverings
    DE102005055391A1|2006-06-08|Thermal barrier coating for the side surfaces of turbine blade platforms and application methods
    WO2007101465A1|2007-09-13|Method for coating a blade and blade of a gas turbine
    CH704833A1|2012-10-15|Component for a turbo machine and a method of manufacturing such a component.
    EP3228415A1|2017-10-11|Method of producing a workpiece using coating and additive manufacturing ; corresponding workpiece
    EP1707301B1|2008-06-18|Process for applying fibre mats on the surface or a recess of a component
    EP1661640A1|2006-05-31|Method for producing a lost pattern and a core introduced into the pattern
    DE112016000144T5|2017-07-06|Heat insulation structure of the combustion chamber of an engine
    WO2009006871A2|2009-01-15|Turbomachine blade with weaar-resistant layer
    EP2845918A1|2015-03-11|Method for at least partially coating a blade, a coating device and a blade
    DE102004050474A1|2006-04-20|Process for producing a component coated with a wear protection coating
    EP1465739B1|2007-03-21|Method for coating a substrate having holes
    EP2581468A1|2013-04-17|Method for applying an anti-wear protective coating to a flow engine component
    EP1645652A1|2006-04-12|Process for the manufacture of a layer system
    DE102015207463A1|2016-10-27|Printed repair plaster for turbine components
    EP2372087A1|2011-10-05|Components with an external wall which can be exposed to a hot gas of a gas turbine and method for producing such a component
    EP2628816A1|2013-08-21|Method for applying a heat insulation layer
    DE102004028672A1|2006-01-05|Coating inner surfaces of hollow gas turbine blades used in an aircraft engine comprises preparing the blade with a hollow chamber, arranging a metal foil in the chamber and welding the metal foil to the inner surface
    WO2016087215A1|2016-06-09|Method for coating a turbine blade
    EP1772529A1|2007-04-11|Dry chemical composition, use thereof to form a layer systemand method for coating
    同族专利:
    公开号 | 公开日
    US20160032736A1|2016-02-04|
    DE102014106295A1|2014-11-20|
    JP2014223620A|2014-12-04|
    JP6475419B2|2019-02-27|
    CH708100A2|2014-11-28|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4743462A|1986-07-14|1988-05-10|United Technologies Corporation|Method for preventing closure of cooling holes in hollow, air cooled turbine engine components during application of a plasma spray coating|
    JPH11117704A|1997-10-13|1999-04-27|Toshiba Corp|Gas turbine parts and manufacture thereof|
    US6234755B1|1999-10-04|2001-05-22|General Electric Company|Method for improving the cooling effectiveness of a gaseous coolant stream, and related articles of manufacture|
    US6551061B2|2001-03-27|2003-04-22|General Electric Company|Process for forming micro cooling channels inside a thermal barrier coating system without masking material|
    EP1350860A1|2002-04-04|2003-10-08|ALSTOM Ltd|Process of masking cooling holes of a gas turbine component|
    US20050084657A1|2002-08-02|2005-04-21|Minoru Ohara|Method for forming heat shielding film, masking pin and tail pipe of combustor|
    JP5271688B2|2008-12-17|2013-08-21|三菱重工業株式会社|Gas turbine components|
    US20120114868A1|2010-11-10|2012-05-10|General Electric Company|Method of fabricating a component using a fugitive coating|
    US8753071B2|2010-12-22|2014-06-17|General Electric Company|Cooling channel systems for high-temperature components covered by coatings, and related processes|RU2658173C2|2014-03-03|2018-06-19|Сименс Акциенгезелльшафт|Rotor component for a rotor assembly of a fluid powered machine, a rotor assembly and a machine, a method for manufacturing such rotor component and a method for controlling its concentricity|
    JP5905631B1|2015-09-15|2016-04-20|三菱日立パワーシステムズ株式会社|Rotor blade, gas turbine provided with the same, and method of manufacturing rotor blade|
    DE102018201453A1|2018-01-31|2019-08-01|MTU Aero Engines AG|Process for the production of a mask in layers|
    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    优先权:
    申请号 | 申请日 | 专利标题
    US13/894,500|US20160032736A1|2013-05-15|2013-05-15|Coating process and coated article|
    [返回顶部]