• 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:
    A turbine repair method includes providing a damaged turbine component (101A, B, C), wherein the turbine component has a cavity surrounded by one or more wells, wherein in the cavity during operation a higher pressure than in the region outside of the one or more wells, wherein due to the damage an opening has formed between the higher pressure region and the lower pressure region, introducing particles into the higher pressure region and at least partially repairing the opening between the higher pressure region and the region lower pressure with at least one of the particles to form a repaired turbine component (101A, B, C). The repaired turbine component (101A, B, C) has a ceramic matrix composite layer and in the region of an opening between a cavity with higher pressure during operation of the turbine and a region with lower pressure outside of the turbine component (101A-C) during operation of the turbine. Silicon material is deposited and surrounded by the ceramic matrix composite material.
    公开号:CH708638B1
    申请号:CH00101/15
    申请日:2013-06-28
    公开日:2018-03-15
    发明作者:Das Rupak；Mcconnell Delvaux John；Jose Garcia-Crespo Andres
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    description
    Statement of Federally Sponsored Research or Development The United States Government retains licensing rights to this invention and the right to require, under limited circumstances, that the patentee may grant to others reasonable terms under the terms of Government Contract No. DE-FC26-05N T42 643, granted by the United Stated Department of Energy, granted a license.
    Field of the Invention The present invention relates, according to the independent claims, to a method of repairing a turbine component and a turbine component repaired by the method.
    Background of the Invention Gas turbine components are exposed to both thermally, mechanically and chemically hostile environments. For example, in the compressor section of a gas turbine atmospheric air at e.g. compressed 10 to 25 times the atmospheric pressure and heated adiabatically, during operation, e.g. between 427 ° C to 677 ° C (800 ° F and 1250 ° F). This heated and compressed air is passed into a burner where it is mixed with fuel. The fuel is ignited and the combustion process heats the gases to very high temperatures, e.g. to more than 1650 ° C (3000 ° F). These hot gases flow through the turbine, where blades fixed to rotating turbine disks extract energy to drive the fan and compressor of the turbine and through the exhaust system, where the gases provide enough energy to rotate a generator rotor Generate electricity.
    Operation under these conditions may cause susceptibility to damage, e.g. by foreign objects that hit turbine components, such as blades. Damage to blades may result in reduced turbine efficiency, more frequent repairs, shorter duration between scheduled repairs, and / or cost inefficiency.
    [0005] A method of on-site turbine repair, a repaired coating, and a repaired turbine component that do not suffer from one or more of the above disadvantages would be desirable in the art.
    Brief Description of the Invention A method of repairing a component of a turbine according to the invention includes providing a damaged turbine component having a cavity surrounded by one or more layers enclosing a ceramic matrix composite material and extending around the turbine component a higher pressure prevails in the cavity during operation of the turbine than in a region outside the one or more layers, and wherein due to damage of the turbine component an opening forms between the cavity and the region outside the turbine component and the pressure difference between the cavity and the Removing region outside the turbine component, and also introducing particles during operation of the turbine through the cavity, which migrate to the opening, and at least partially repairing the opening between the cavity and the region outside the Turbinenba Partly by at least one of the particles at least partially fills the opening and increases the pressure difference between the cavity and the region outside the turbine component again.
    A turbine component that has been repaired by the inventive method by at least partially filled during repair an opening between a cavity with during operation of the turbine higher pressure and a region with lower pressure during operation of the turbine pressure outside of the turbine component , comprises a ceramic matrix composite material layer, and in the region of the opening a silicon material is deposited and surrounded by the ceramic matrix composite material.
    Other features and advantages of the present invention will become apparent from the following more detailed description of the preferred embodiment, taken in conjunction with the accompanying drawings, which illustrate, by way of example, the principles of the invention.
    Short description of the drawing [0009]
    1 schematically illustrates an exemplary turbine repair method of an exemplary turbine component according to the disclosure.
    FIG. 2 schematically illustrates an exemplary turbine repair method of an exemplary coating according to the disclosure. FIG.
    Wherever possible, the same reference numerals are shown in the figures to represent the same parts therein.
    DETAILED DESCRIPTION OF THE INVENTION Provided is an exemplary turbine repair method and repaired turbine component. Embodiments of the present disclosure extend the useful life of turbine components, allow for the repair of coatings and / or turbine components in place, prevent damage due to oxidation, prevent fouling of engine components or combinations thereof. One embodiment allows silicon molecules to travel through a cooling passage and adhere to walls of openings formed by damage from foreign and / or owned objects, e.g., by Braun's motion and / or thermal energy. The molecules are eventually oxidized to silica and reduce the recession rates of ceramic matrix composite substrates due to increased localized amount of SiO 2 molecules near the damaged portion.
    Figs. 1 and 2 schematically show an exemplary turbine repair method. Each of FIGS. 1 and 2 shows a turbine component 101A, followed by the turbine component 101B after the occurrence of the damage, and the turbine component 101C after repair according to an embodiment of the method. Fig. 2 shows sectional views corresponding to Fig. 1 along lines A-A, B-B and C-C. The turbine repair method is usable with a suitable turbine component 101. As shown in FIG. 1, in one embodiment, the turbine component is a turbine blade 100 or a turbine blade. Other suitable turbine components include a dovetail, a shaft, a platform, a wing, a tip cap, a dendrite, or other suitable component having a pressure differential.
    As shown in FIG. 2, the turbine component 101 includes a higher pressure region 103 and a lower pressure region 105. The higher pressure region 103 of the turbine component 101 is bonded by one or more layers including a ceramic matrix composite material 121. In one embodiment, the ceramic matrix composite material 121 defines a cavity within the turbine component 101, such as a core of the turbine blade 100. In one embodiment, the core is broken into two or more cavities.
    Near the lower pressure region 105, in one embodiment, the turbine component 101 includes a coating, such as an environmental barrier coating (EBC) 115, on the turbine component 101. In one embodiment, the EBC 115 extends around the turbine component 101, such as through a suction side and through a print page. The EBC 115 includes an appropriate number of layers or materials that are capable of operating under the conditions of the lower pressure region 105. The layer (s) of the EBC 115 is / are applied by a suitable method capable of depositing material onto ceramic matrix composites. For example, suitable methods include atmospheric plasma spraying, implantation of reactive ions, chemical vapor deposition, plasma enhanced chemical vapor deposition, dip coating, electrophoretic deposition, or a combination thereof. Suitable layers are those based on silicon and / or include silica, such as a bond coat, which provides chemical compatibility with ceramic matrix composites. Another suitable layer is a transition layer such as barium strontium aluminosilicate (BSAS), (Yb, Y) 2Si207, mullite with barium strontium aluminosilicate, or a combination thereof, resistance to water vapor penetration, chemical compatibility with the bond coat, coefficient of thermal expansion, compatible with ceramic matrix composites or imparting a combination thereof. Another suitable layer is an upper coating, such as Y2Si05 or barium strontium aluminosilicate, which provides water vapor release and / or a thermal expansion coefficient compatible with ceramic matrix composites. In further embodiments, EBC 115 includes a thermally grown oxide layer.
    During operation of a turbine employing the turbine component 101, the higher pressure region 103 and the lower pressure region 105 are under different conditions. During operation, for example, the higher pressure region 103 is at a higher pressure than the lower pressure region 105, resulting in the pressure differential. The pressure differential decreases after a portion of EBC 115 and ceramic matrix composite material 121 has been removed, e.g. by damage by foreign objects to the region 105 of lower pressure. Such damage forms an opening 109 between the higher pressure region 103 and the lower pressure region 105.
    In one embodiment, the turbine component 101A operates against damage by the foreign object at a predetermined range of pressure differential, e.g. between about 3% and 10% more than an outer zone (such as a hot gas path) and / or greater than about 0.21 bar (3 psi), greater than about 0.34 bar (5 psi), at about 0.34 bar (5 psi), between about 0.21 bar (3 psi) and about 0.48 bar (7 psi) or between about 0.34 bar (5 psi) and about 0.48 bar (7 psi). After the damage by a foreign object has occurred, the pressure difference between the higher pressure region 103 and the lower pressure region 105 of the turbine component 101B decreases. In one embodiment, the reduced pressure differential is identified, allowing identification of the damage without visual inspection. Due to the occurrence of the damage by the foreign object, the turbine repair method is used.
    Additionally or alternatively, such identification of damage by a foreign object is capable of being based on monitoring a predetermined pressure range for the region 103 of higher pressure and / or a predetermined pressure range for the region 105 of lesser pressure. In one embodiment, the predetermined pressure range for the higher pressure region 103 is between about 3% and about 10% more than one
    Outside zone (such as a hot gas path and / or lower pressure region 105). After being damaged by a foreign object, the pressure within the higher pressure region 103 is reduced.
    The higher pressure region 103 and the lower pressure region 105 may also operate under temperature differences, resulting in a temperature difference. For example, in one embodiment, the higher pressure region 103 operates at a lower temperature, such as between about 471 ° C (700 ° F) and about 816 ° C (1500 ° F), and the lower pressure region 105 operates at a higher one Temperature, such as between 649 ° C (1200 ° F) and about 1371 ° C (2500 ° F).
    The opening 109 may be formed by the damage by the foreign object between the higher pressure region 103 and the lower pressure region 105, resulting in a drop in the pressure difference between the higher pressure region 103 and the lower pressure region 105. The foreign object is of random size based on structured particles and / or agglomerates coming from upstream sections. In one embodiment, the damage by the foreign article corresponds to a foreign particle having a dimension of greater than about 1.4 mm, greater than about 1.6 mm, greater than about 1.8 mm, greater than about 2.0 mm, or greater than about 2.2 mm. The opening 109 has a void geometry formed by the EBC 115 and the ceramic matrix composite material 121. In one embodiment, the opening 109 is, for example, a channel, a cylindrical recess or hole, a conical recess or hole, a frusto-conical recess or hole, a split, or any combination thereof.
    To repair the damage, the opening 109 is at least partially repaired by one or more of the particles 107 introduced by the higher pressure region 103. In one embodiment, the particles 107 are introduced through a feed 123 disposed, for example, in the dovetail portion of the turbine blade 100. The particles 107 migrate to the opening 109, e.g., based on the pressure differential, and contact the ceramic matrix composite 121. Some of the particles 107 contact the EBC 115 and / or are ejected into the lower pressure region 105. The particles 107 which contact the EBC 115 do not adhere significantly. At least a portion of the particles 107 that contact the ceramic matrix composite 121 adhere. These particles 107 interrupt the orifice 109 and thereby at least partially fill the entire damaged passage and allow, for example, the increase in pressure differential to differentiate the higher pressure region 103 and the lower pressure region 105 within the operating range prevailing before Damage by the foreign object was present, and at least partially repair the turbine component 101C. In one embodiment, the particles 107 are converted to other materials by the presence of heat and / or oxygen, such as a molten ceramic and / or an oxidized material (e.g., silica).
    The particles 107 are suitable particles that are introduced into the higher pressure region 103 and at least partially repair the opening 109. In one embodiment, the particles 107 include elemental silicon. In another embodiment, the oxygen and / or moisture of the higher pressure region 103 oxidize some or all of the particles 107 to silica.
    The particles 107 are of a suitable geometry and size which permit introduction into the higher pressure region 103 and at least partially repair the opening 109. In one embodiment, one or more of the particles 107 are spheroidal, spherical, cuboidal, substantially planar, complexed, or a combination thereof. In one embodiment, one or more of the nanosize particles 107, e.g. they have a maximum dimension within a nanometer range, such as between about 2 nm and 10 nm, between about 5 nm and about 6 nm, less than about 20 nm, less than about 10 nm or less than 5 nm. In one embodiment, one or more the particles 107 a pm size, eg they have a maximum dimension within a pm range, such as less than about 2 pm, less than about 1 pm, between about 1 pm and about 2 pm, or about 1 pm.
    The particles 107 are introduced in a suitable manner so as to allow, for example, the continued operation of a non-stop turbine using the turbine component 101. In one embodiment, the particles 107 are suspended in a fluid, such as a liquid and / or a gas. In one embodiment, the particles 107 are introduced by injection into the feeder 123, e.g. with air and / or other gases.
    In one embodiment, the particles 107 are introduced with air. In one embodiment, the particles with the air at weight ppm Si are between about 0.07 and about 4, between about 0.07 and about 0.2, between about 1 and about 2, between about 2 and about 3, or between about 3 and about 4 introduced.
    In one embodiment, the particles 107 are intermittently introduced, for example, to form about one-thousandth of an inch of material in the opening 109 per day, at a rate of about 4 moles or any other suitable rate that allows the turbine component 101 is repaired. In one embodiment, the particles 107 are introduced during operation of a turbine into which the turbine component is inserted.
    After repairing, the turbine component 101, like the blade 100, encloses a repaired region III of the repaired coating with a silica material 202 deposited on and surrounded by the ceramic matrix composite material 121, corresponding to a region of damage by one A foreign object such as the opening 109. In one embodiment, the silica material 202 is deposited on and completely surrounded by a portion of the ceramic matrix composite 121 and / or EBC 115. In one embodiment
    权利要求:
    Claims (17)
    [1]
    The silica material 202 includes intercalated elemental silicon that has not been oxidized. In this embodiment, the repaired region has a hardness between the hardness of silica and silicon. claims
    A method of repairing a turbine component (101A, B, C) comprising: providing a damaged turbine component (101A, B, C), the turbine component (101A, B, C) having a cavity (103) surrounded by one or more layers (121) enclosing a ceramic matrix composite material and extending around the turbine component (101A-C), wherein in the cavity (103) a higher pressure prevails during operation of the turbine than in a region ( 1.05) lower pressure outside the one or more layers (121), wherein due to damage of the turbine component (101A-C), an opening (103) between the higher pressure cavity (103) and the lower pressure region (105) outside of the turbine component (101A-C) and the pressure difference between the cavity (103) and the region (105) outside the turbine component (101A-C) has decreased, introducing particles (107) during operation of the turbine dur ch the higher pressure cavity (103) that migrates to the opening (109) and at least partially repairing the opening (109) between the cavity (103) and the lower pressure region (105) outside the turbine component (101A-C) by at least one of the particles (107) at least partially fills the opening (109) and the pressure difference between the cavity (103) and the region (105) outside the turbine component (101A-C) increases again.
    [2]
    The method of claim 1, further comprising identifying the pressure differential between the cavity (103) and the lower pressure region (105) outside the turbine component (101A-C) prior to introducing the particles (107) into the cavity (103).
    [3]
    3. The method of claim 1, wherein the pressure in the cavity (103) is 3% higher than the pressure in the region (105) outside the turbine component (101A-C).
    [4]
    4. The method of claim 1, wherein the pressure in the cavity (103) is 10% higher than the pressure in the region (105) outside the turbine component (101A-C).
    [5]
    5. The method of claim 1, wherein the pressure in the cavity (103) is between 3% and 10% higher than the pressure in the region (105) outside the turbine component (101A-C).
    [6]
    The method of claim 1, wherein the particles (107) include elemental silicon.
    [7]
    The method of claim 1, wherein the region (105) outside the turbine component (101A-C) is at a temperature between 649 ° C, 1200 ° F, and 1371 ° C, 2500 ° F.
    [8]
    The method of claim 1, wherein the cavity (103) is at a temperature between 371 ° C, 700 ° F, and 816 ° C, 1500 ° F.
    [9]
    The method of claim 1, wherein the particles (107) are smaller than 20 nm.
    [10]
    10. The method of claim 1, wherein the particles (107) are smaller than 2 pm.
    [11]
    11. The method of claim 1, wherein the introduction of the particles (107) is effected by injection with compressed air.
    [12]
    12. The method of claim 1, wherein the turbine component to be repaired is a turbine blade (100), a shroud ring or a nozzle.
    [13]
    13. The method of claim 1, wherein the repaired turbine component (101A-C) has a deposited silicon material surrounded by a ceramic matrix composite material (121) in the region of the opening.
    [14]
    14. The method of claim 1, wherein at least a portion of the particles (107) which at least partially fill the opening (109) are oxidized.
    [15]
    15. The method of claim 1, wherein at least a portion of the particles (107) is melted after at least partially repairing the opening (109).
    [16]
    A turbine component (101A-C) repaired by the method of claim 1, wherein, during repair, having an opening (109) between a cavity (103) having higher pressure during operation of the turbine and a region (105) during operation 101A-C), wherein the turbine component (101A-C) comprises: a ceramic matrix composite material layer (121) and wherein a silicon material is deposited in the region of the opening and separated from the ceramic matrix composite material (101A-C). 121) is surrounded.
    [17]
    17. The turbine component (101A-C) of claim 16, wherein the silicon material deposited in the region of the opening comprises a silicon dioxide material.
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    同族专利:
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    US20140030464A1|2014-01-30|
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    WO2014022040A2|2014-02-06|
    JP2015525851A|2015-09-07|
    WO2014022040A3|2014-05-08|
    US9175402B2|2015-11-03|
    JP6154902B2|2017-06-28|
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2021-01-29| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US13/561,445|US9175402B2|2012-07-30|2012-07-30|Turbine repair process, repaired coating, and repaired turbine component|
    PCT/US2013/048404|WO2014022040A2|2012-07-30|2013-06-28|Turbine repair process, repaired coating, and repaired turbine component|
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