• 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 component (100) is disclosed. The turbine component (100) includes an outer shroud (101) and an inner shroud (103) having a first hook portion (105) extending over a first portion (109) of the outer shroud (101) and a second hook portion (107) which extends over a second section (111) of the outer cover strip (101). A first hook gap (113), a second hook gap (115), a first radial gap (114) and a second radial gap (116) are arranged and arranged to allow the inner shroud (103) to be subjected to thermal stress from the outer shroud (11). 101). Additionally or alternatively, the inner shroud (103) contains ceramic matrix composite fibers having a thermal conductivity of less than 200 W / m ⋅ K and more than 10 W / m ⋅ K.
    公开号:CH709761B1
    申请号:CH00753/15
    申请日:2015-05-27
    公开日:2019-07-15
    发明作者:Woodrow Roberts Frederic Jr；Curtis Taxacher Glenn；John Kittleson Jacob；John Morgan Victor
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    description
    Field of the Invention The present invention relates to turbine components. More particularly, the present invention relates to turbine components having an inner shroud and an outer shroud.
    Background of the Invention Operation of turbine components and power generation systems at higher temperature and pressure allows for improved efficiency and operation in new configurations. A selection of materials capable of operating at such higher temperatures and pressures is difficult. Such materials can be too expensive, difficult to produce or difficult to manufacture. In addition, the use of such different materials may require a change in cooling mechanisms that may cause other complications.
    In general, the use of less material for similar or improved operation is desired. Using less material reduces weight, lowers manufacturing costs, lowers material costs, and offers several other benefits. However, the use of less material can generate complicated geometric requirements and / or unwanted forces that were not previously generated, e.g. Create tension forces. In addition, as in the case of using different materials, the use of less material may require complicated and / or expensive changes to the cooling mechanism, which may entail other complications.
    Thus, there is a continuing desire to produce materials capable of withstanding higher temperatures and pressures which can be employed in lower amounts / weights capable of operation without causing undesirable forces which are capable of use under operating conditions without the need for complex and / or expensive cooling mechanisms.
    [0005] A turbine component that exhibits one or more improvements over the prior art would be desirable in the art.
    Summary of the Invention The invention relates to a turbine component, an outer shroud, and an inner shroud having a first hook portion extending over a first portion of the outer shroud and a second hook portion extending over a second portion of the outer shroud. The first hook portion and the first portion define a first hook gap, and the second hook portion and the second portion define a second hook gap. A first radial gap extends between the first hook region opposite the first hook gap and the outer cover tape, and a second radial gap extends between the second hook region opposite the second hook gap and the outer cover tape. The first hook gap, the second hook gap, the first radial gap, and the second radial gap are configured and arranged to allow the inner shroud to deflect from the outer shroud under thermal stress.
    In the aforementioned turbine component, the inner shroud may include a ceramic matrix composite.
    The ceramic matrix composite may include a SiC fiber and a SiC matrix.
    In particular, the SiC fiber in the ceramic matrix composite may have a concentration, by volume, of at least 20%.
    In the turbine component of any kind mentioned above, the outer shroud may contain a metal or a metallic material.
    In the turbine component of any kind mentioned above, the inner shroud may have a thermal conductivity of less than 200 W / m K.
    Furthermore, the inner shroud may have a thermal conductivity of more than 10 W / m K.
    The inner shroud preferably has a thermal conductivity of about 120 W / m K.
    In the turbine component of any kind mentioned above, the inner shroud and the outer shroud preferably do not join during operation of the turbine component.
    In one embodiment, the turbine component may further include an impact plate disposed between the inner shroud and the outer shroud.
    The impact plate may contain a metal.
    In the turbine component of any kind mentioned above, the outer shroud may include an inner cavity.
    The inner cavity may be pressurized.
    In particular, the inner cavity may be pressurized to a pressure equal to or greater than the pressure of the hot gas path.
    The turbine component of any of the aforementioned types may further include a transverse gap extending parallel to at least a portion of the inner shroud between the first hook portion and the second hook portion.
    Additionally or alternatively, the turbine component may further include an additional inner shroud disposed adjacent the inner shroud and extending over the first portion of the outer shroud and the second portion of the outer shroud.
    Further additionally or in another alternative, the turbine component may further include an environmental barrier coating positioned at least on a portion of the inner cover tape to contact the hot gas path.
    The environmental barrier coating may be an abradable enema coating.
    The turbine component comprises an outer shroud and an inner shroud having a first hook portion extending over a first portion of the outer shroud and a second hook portion extending over a second portion of the outer shroud. The inner shroud may include a ceramic matrix composite having a thermal conductivity of less than 200 W / m K and more than 10 W / m K.
    The first hook portion and the first portion define a first hook gap, and the second hook portion and the second portion define a second hook gap, wherein the first hook gap and the second hook gap are arranged and arranged to allow the inner cover tape under thermal stress to deflect from the outer shroud. The inner shroud may contain ceramic matrix composite fibers having a thermal conductivity of less than 200 W / m K and more than 10 W / m K.
    Other features and advantages of the present invention will become apparent from the following more detailed description, taken in conjunction with the accompanying drawings, which illustrate, by way of example, the principles of the invention.
    Brief description of the drawings [0027]
    FIG. 1 is a perspective view of one embodiment of a component having an inner cover tape and an outer cover tape according to the disclosure. FIG.
    Wherever possible, the same reference numbers will be used throughout the drawings to identify like parts throughout.
    Detailed Description of the Invention [0029] A turbine component is provided. For example, in comparison to prior art concepts, embodiments of the present disclosure are capable of being easier to repair and replace, withstand higher temperatures and pressures, can be used in smaller amounts / weights, are capable of operation without undesirable effects Forcing forces can be used under operational conditions without the use of complicated and / or expensive cooling mechanisms, and / or are capable of mechanical loading to reduce leakage, thereby improving the operating efficiency of a machine.
    Fig. 1 shows an embodiment of a turbine component 100 that may be used in, for example, a power generation system, a turbine, or both. The turbine component 100 includes an outer shroud 101 and an inner shroud 103 having a first hook portion 105 extending over a first portion 109 of the outer shroud 101 and a second hook portion 107 extending over a second portion 111 of the outer shroud 101. The first hook portion 105 and the first portion 109 define a first hook gap 113, and the second hook portion 107 and the second portion 111 define a second hook gap 115. A first radial gap 114 extends between the first hook portion 105 opposite the first hook gap 113 and the first hook portion Outer shroud 101, and a second radial gap 116 extends between the second hook portion 107 opposite the second hook gap 115 and the outer shroud 101. The first hook gap 113, the second hook gap 115, the first radial gap 114 and the second radial gap 116 are arranged and arranged to allow the inner shroud 103 to deflect from the outer shroud 101 under thermal stress.
    The first hook gap 113, the second hook gap 115, the first radial gap 114 and the second radial gap 116 have any suitable geometry that allows deflection to reduce or eliminate stress during operation of the turbine component 100 , In one embodiment, a suitable geometry includes, for example, cuboid channels extending above the inner cover tape 103.
    Although the term "hook" is used, and FIG. 1 shows a first curved portion 102, a first planar portion 104 near the first curved portion 102, a second curved portion 106 near the first planar portion 104, and a second planar portion 108 in the vicinity of the second curved portion 106, with the second planar portion 108 extending substantially parallel to the inner shroud and a hot gas path 119, is an angled, arcuate, curled, curved, or other arrangement that is separated into at least three separate ones Levels extends to understand by the term "hooks". Other suitable geometries include a rectangular prism, a slot, a portion of a cylinder (such as a half-cylinder), an arc having a planar or substantially planar boundary that connects the ends of the arc, or any other geometry that allows for deflection but are not limited to these.
    The first hook portion 105, the first radial gap 114 and the first portion 109 are located near a leading edge 127 as compared to a trailing edge 129. The second hook portion 107, the second radial gap 116 and the second portion 111 are located near the trailing edge 129, as compared to the leading edge 127. The first hook portion 105 and the second hook portion 107 adjustably secure the inner shroud 103 to the outer shroud 101. In one embodiment, the inner shroud 103 and the outer shroud 101 may be secured together without screwing, based on the first hook portion 105 extending over the first portion 109 of the outer cover tape 101, and on the second hook portion 107 extending over the second portion 111 of the outer cover tape 101. Any other suitable mechanisms may be used to further secure the outer shroud 101 and the inner shroud 103 as well as additional inner shrouds in embodiments having multiple inner shrouds 103.
    In one embodiment, the arrangement of the outer cover tape 101 and the inner cover tape 103 in conjunction with the selected materials allows for optional removal, repair and / or replacement of the inner cover tape 103 from the outer cover tape 101. For example, in one embodiment, the inner cover tape 103 and the Outer shroud 101 under suitable operating conditions of the turbine component 100 not together. As used herein, the term "connect" refers to a local yield or local deformation of the outer cover tape 101, e.g. above the second planar section 108. Suitable operating conditions include, but are not limited to, temperatures from about 1200 ° F to above 3200 ° F (about 650 ° C to about 1760 ° C).
    The inner shroud 103 and the outer shroud 101 include any suitable materials capable of being used under the operating conditions of the power generation system, the turbine, or any other system that uses the turbine component 100. In one embodiment, the outer shroud 101 includes a metal or metallic material, such as a metal. a nickel-based alloy or corrosion-resistant steel. In one embodiment, the inner shroud 103 includes a ceramic matrix composite. As used herein, the term "ceramic matrix composite" includes, but is not limited to, carbon fiber reinforced carbon (C / C), carbon fiber reinforced silicon carbide (C / SiC), silicon carbide fiber reinforced silicon carbide (SiC / SiC), and silicon carbide fiber reinforced oxide matrix composite , In one embodiment, the ceramic matrix composite has increased extensibility, fracture toughness, thermal shock resistance, dynamic resilience and improved anisotropic properties as compared to a monolithic ceramic structure. A suitable ceramic matrix composite contains e.g. a SiC fiber and a SiC matrix, with the SiC fiber at a concentration, by volume, in the ceramic matrix composite of e.g. at least about 20%, at least about 23%, at least about 28%, at least about 30%, between about 23% and about 32%, or any suitable combination, subcombination, range or subrange thereof.
    The materials for the inner shroud 103 are selected to provide a selected range of thermal conductivity for the turbine component 100. In one embodiment, the thermal conductivity of the inner cover tape 103 and / or the material for the inner cover tape 103 is less than 200 W / m K, less than 150 W / m K, less than 140 W / m K, less than 130 W / m K or any combination, subcombination, range or subarea thereof. Additionally or alternatively, the thermal conductivity of the inner cover tape 103 and / or the material for the inner cover tape 103 in one embodiment is more than 10 W / m K, less than 50 W / m K, more than 100 W / m K, less than 110 W / m K or any combination, subcombination, range or subrange thereof. In one embodiment, the thermal conductivity is 120 W / m K.
    The inner shroud 103 and / or the outer belt 101 contains / include any other suitable features that do not adversely affect a deflection under thermal stress. For example, in one embodiment, outer band 101 includes an internal cavity 117 that allows flow of fluid (e.g., air or compressed air). The inner cavity 117 may be e.g. be sealed by means of wedge gaskets on peripheral surfaces of the turbine component 100 and by means of compliant seals on the leading edge 127 and / or the trailing edge 129. In one embodiment, the internal cavity 117 is pressurized, e.g. up to more than the operating pressure and / or the pressure of the hot gas path 119, which extends along the removed portion of the inner cover tape 103 relative to the outer shroud 101. In one embodiment, a cross gap 121 extends parallel, substantially parallel or tangentially between the inner shroud 103 and the outer shroud 101 from the first hook region 105 to the second hook region 107, and allows the heat from the inner shroud 103 to the outer shroud 101 is transmitted. In another embodiment, an impact plate 123 between the inner cover tape 103 and the outer cover tape 101 is attached. The impact plate 123 includes a material identical to, similar to, or different from the inner cover tape 103, and achieves cooling by heat transfer to the inner cavity 117.
    The inner cover tape 103 includes any suitable features to suit operating parameters such as e.g. Temperature or pressure resulting from being positioned to be in contact with the hot gases within the hot gas path 119. For example, in one embodiment, the inner shroud 103 includes an environmental barrier coating 125 disposed on a portion or on all surfaces of the inner shroud 103 that are positioned to contact the hot gases in the hot gas path 119. The environmental barrier coating 125 is any suitable coating capable of operating in the hot gas path 119. In order to adjust the blade tips at a distance, in one embodiment, an abradable run-in coating (not shown) is included on the inner shroud 103 within the hot gas path 119. Suitable materials for the environmental barrier coating 125 and abradable drainage coating include, but are not limited to, barium strontium aluminum silicates, mullite, yttrium stabilized zirconium, yttrium mono- and di-silicates, ytterbium mono- and disilicates and their combinations.
    Although the invention has been described with reference to one or more exemplary embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof 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 essential scope thereof. It is therefore intended that the invention not be limited to the specific embodiment disclosed for practicing the invention, but that the invention should include all embodiments falling within the scope of the appended claims.
    A turbine component is disclosed. The turbine component includes an outer shroud and an inner shroud having a first hook portion extending over a first portion of the outer shroud and a second hook portion extending over a second portion of the outer shroud. A first hook gap, a second hook gap, a first radial gap and a second radial gap are arranged and arranged to allow the inner shroud to deflect from the outer shroud under thermal stress. Additionally or alternatively, the inner shroud contains ceramic matrix composite fibers having a thermal conductivity of less than 200 W / m K and more than 10 W / m K.
    权利要求:
    Claims (8)
    [1]
    claims
    A turbine component (100) comprising: an outer shroud (101); and an inner cover tape (103) having a first hook portion (105) extending over a first portion (109) of the outer cover tape (101) and a second hook portion (107) extending over a second portion (111) of the Outer shroud (101) extends; wherein the first hook portion (105) and the first portion (109) define a first hook gap (113) and the second hook portion (107) and the second portion (111) define a second hook gap (115); wherein a first radial gap (114) extends between the first hook portion (105) opposite the first hook gap (113) and the outer cover tape (101) and a second radial gap (116) between the second hook portion (107) opposite the second hook gap (115) and the outer shroud (101); wherein the first hook gap (113), the second hook gap (115), the first radial gap (114) and the second radial gap (116) are arranged and arranged to allow the inner shroud (103) under thermal stress from the outer shroud (101) to deflect.
    [2]
    2. turbine component (100) according to claim 1, wherein the inner shroud (103) includes a ceramic matrix composite; wherein the ceramic matrix composite preferably includes a SiC fiber and a SiC matrix; wherein the SiC fiber may have a concentration in the ceramic matrix composite of at least 20% by volume.
    [3]
    3. Turbine component (100) according to claim 1 or 2, wherein the outer shroud (101) contains a metal or a metallic material; and / or wherein the inner shroud (103) and the outer shroud (101) are configured such that they do not interconnect during operation of the turbine component (100).
    [4]
    4. turbine component (100) according to any one of the preceding claims, wherein the inner shroud (103) has a thermal conductivity of less than 200 W / m K and / or wherein the inner shroud (103) has a thermal conductivity of more than 10 W / m K. ; wherein the inner shroud (103) preferably has a thermal conductivity of about 120 W / mK.
    [5]
    5. turbine component (100) according to any one of the preceding claims, further comprising an impact plate (123) which is arranged between the inner shroud (103) and the outer shroud (101); wherein the impact plate (123) preferably comprises a metal.
    [6]
    A turbine component (100) according to any one of the preceding claims, wherein the outer shroud (101) includes an inner cavity (117); wherein the inner cavity (117) is preferably pressurizable; wherein the inner cavity (117) can be acted upon by a pressure which is equal to or greater than the pressure of a hot gas path (119).
    [7]
    A turbine component (100) according to any one of the preceding claims, further comprising a transverse gap (121) extending parallel to at least a portion of the inner shroud (103) between the first hook portion (105) and the second hook portion (107); and / or further comprising an additional inner shroud disposed adjacent the inner shroud (103) and extending over the first portion (109) of the outer shroud (101) and the second portion (111) of the outer shroud (101).
    [8]
    A turbine component (100) according to any one of claims 6 or 7, further comprising an environmental barrier coating (125) disposed on at least a portion of the inner shroud (103) to contact the hot gas path (119); wherein the environmental barrier coating (125) is preferably an abradable enema coating.
    类似技术:
    公开号 | 公开日 | 专利标题
    CH709761B1|2019-07-15|Turbine component.
    DE60314032T2|2008-01-24|Shroud segment, manufacturing method of a shroud segment, and shroud assembly for a turbine engine
    DE102011002172A1|2011-12-29|Turbine shroud sealing device
    DE102015100874A1|2015-07-30|Sealing device for providing a seal in a turbomachine
    DE102016114997A1|2017-02-23|Turbine shroud assembly
    EP1219787B1|2005-12-21|Gas turbine blade and gas turbine
    EP2846002A1|2015-03-11|Gas turbine
    WO2005070613A1|2005-08-04|Method for repairing a component of a turbomachine
    DE102016100043A1|2016-07-21|Turbine shroud assembly
    DE102011050961A1|2012-03-01|Turbine blade arrangement
    DE3345263A1|1984-06-20|CERAMIC TURBINE SHOVEL
    DE102008002863A1|2008-12-04|Sealing ring with dovetail molding section
    DE102009049018A1|2010-04-15|Component for a high-temperature steam turbine and high-temperature steam turbine
    EP2282014A1|2011-02-09|Ring-shaped flow channel section for a turbo engine
    EP3015715A1|2016-05-04|Stator vane ring for a turbomaschine and turbomaschine
    WO2007028353A1|2007-03-15|Turbomachinery and sealing element for turbomachinery
    DE102017127628A1|2019-05-23|Turbine and turbocharger
    DE102014111204A1|2015-02-26|Turbine system and adapter
    EP2431570A1|2012-03-21|Steam turbine with a dummy piston and wet steam blockage
    EP2216512A1|2010-08-11|Triple shell steam turbine
    DE102012200539A1|2013-07-18|Shielding device for turbine housing of thermal gas turbine, has restriction element for limiting flow channel in sections between high pressure side and low pressure side of turbine housing, where bar is arranged in flow channel
    DE102011008812A1|2012-07-19|intermediate housing
    CH711014B1|2021-03-31|Sealing arrangement with a thermal barrier for turbo machinery.
    DE202019000710U1|2019-04-23|Oval steam turbine casing
    EP2161415A2|2010-03-10|Device and method for reducing the pressure on a dividing fugue between at least two neighbouring sections
    同族专利:
    公开号 | 公开日
    CN105275513A|2016-01-27|
    JP6979751B2|2021-12-15|
    CN105275513B|2018-07-24|
    CH709761A2|2015-12-15|
    JP2015227661A|2015-12-17|
    DE102015107848A1|2015-12-03|
    US20150345308A1|2015-12-03|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    JPH10331602A|1997-05-29|1998-12-15|Toshiba Corp|Gas turbine|
    US6702550B2|2002-01-16|2004-03-09|General Electric Company|Turbine shroud segment and shroud assembly|
    DE10204860A1|2002-02-06|2003-08-14|Man Technologie Gmbh|Fiber composite ceramic material, used e.g. for heat engine, heat exchanger, hot gas pipe or nozzle or plasma containing vessel, has heat-conducting three-dimensional fabric with silicon carbide matrix produced in three stages|
    US6758653B2|2002-09-09|2004-07-06|Siemens Westinghouse Power Corporation|Ceramic matrix composite component for a gas turbine engine|
    US7090459B2|2004-03-31|2006-08-15|General Electric Company|Hybrid seal and system and method incorporating the same|
    US7063503B2|2004-04-15|2006-06-20|Pratt & Whitney Canada Corp.|Turbine shroud cooling system|
    US8147192B2|2008-09-19|2012-04-03|General Electric Company|Dual stage turbine shroud|
    FR2949810B1|2009-09-04|2013-06-28|Turbomeca|DEVICE FOR SUPPORTING A TURBINE RING, TURBINE WITH SUCH A DEVICE AND TURBOMOTOR WITH SUCH A TURBINE|
    US20120076927A1|2010-02-01|2012-03-29|United States Government As Represented By The Secretary Of The Army|Method of improving the thermo-mechanical properties of fiber-reinforced silicon carbide matrix composites|
    US8905709B2|2010-09-30|2014-12-09|General Electric Company|Low-ductility open channel turbine shroud|US20170276000A1|2016-03-24|2017-09-28|General Electric Company|Apparatus and method for forming apparatus|
    US10519790B2|2017-06-15|2019-12-31|General Electric Company|Turbine shroud assembly|
    US10711637B2|2017-06-15|2020-07-14|General Electric Company|Turbine component assembly|
    EP3792456A4|2018-05-11|2021-12-15|Kawasaki Jukogyo Kabushiki Kaisha|Shroud assembly for gas turbine|
    US11097384B2|2019-01-23|2021-08-24|General Electric Company|Mechanical ceramic matrix compositerepair|
    US11248482B2|2019-07-19|2022-02-15|Raytheon Technologies Corporation|CMC BOAS arrangement|
    US11073037B2|2019-07-19|2021-07-27|Raytheon Technologies Corporation|CMC BOAS arrangement|
    US11105214B2|2019-07-19|2021-08-31|Raytheon Technologies Corporation|CMC BOAS arrangement|
    US11073038B2|2019-07-19|2021-07-27|Raytheon Technologies Corporation|CMC BOAS arrangement|
    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2019-05-31| NV| New agent|Representative=s name: FREIGUTPARTNERS IP LAW FIRM DR. ROLF DITTMANN, CH |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/292,985|US20150345308A1|2014-06-02|2014-06-02|Turbine component|
    [返回顶部]