• 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:
    The present invention provides a seal (100) for use between adjacent turbine components (110, 120) and with a cooling flow. The seal (100) includes an impactor plate (220), a base plate (240), and one or more spacer elements (260) therebetween. The cooling flow provides cooling through the impactor plate (220).
    公开号:CH711138A2
    申请号:CH00673/16
    申请日:2016-05-25
    公开日:2016-11-30
    发明作者:Earl Dyson Thomas；John Morgan Victor；Nandkumar Sarawate Neelesh；Benjamin Helmer David
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    TECHNICAL AREA
    The present application and the resulting patent generally relate to gas turbines and, more particularly, to gas turbines which use strip seals and the like with leakage flow therethrough to achieve improved heat transfer by impact.
    BACKGROUND TO THE INVENTION
    Generally described, turbomachines, such as gas turbines and the like, include a main gas flow path extending therethrough. Gas leakage, either from the gas flow path or into the gas flow path, can reduce overall efficiency, increase fuel costs and possibly increase emission levels. Secondary flows may be used within the gas turbine to cool the various components heated via the gas flow path. In particular, cooling air may be removed from the later stages of the compressor to be used in cooling the heated gas flow path components and flushing gaps in cavities between adjacent components. For example, conventional designs may include metallic washers placed in slots between shell segments to minimize any leakage flow therethrough. However, these gas flow paths may be exposed to very high heat fluxes and / or other operating parameters that can lead to high oxidation, creep, and consequent damage or failure.
    As firing temperatures increase, gas flow path temperatures may exceed the material limits of conventional gaskets to cause excessive leakage, loss of efficiency and overall reduced component life. Thus, there is a need for improved turbine seals and associated seal cooling techniques. Such improved turbine gaskets and techniques can thus handle the higher firing temperatures without sacrificing efficiency or life.
    BRIEF DESCRIPTION OF THE INVENTION
    The present application and the resulting patent thus provide a seal for use between adjacent turbine components and with a cooling flow. The gasket may include an impactor plate, a base plate, and one or more spacer elements therebetween. The cooling flow provides for cooling through the impact pad.
    In the aforementioned gasket, the impact pad may have one or more baffles in it.
    Additionally or as an alternative, the base plate may have one or more base plate openings therein.
    Further additionally or as a further alternative, the base plate may include one or more base plate outlet slots.
    Still further, the one or more base plate outlet slots may have an exit opening within a cavity.
    In the gasket of any kind mentioned above, the base plate may have a solid construction.
    In some embodiments of any of the aforementioned gaskets, the one or more spacer elements may include a first spacer positioned at a first end of the gasket and a second spacer positioned at a second end of the gasket.
    Additionally or as an alternative, the one or more spacer elements may comprise a spring element.
    Further additionally or as a further alternative, the one or more spacer elements may have a "C" like shape.
    Still further additionally or as yet another alternative, the one or more spacer elements may comprise a material having a different coefficient of thermal expansion than the impactor plate and / or the baseplate.
    In some embodiments of any of the aforementioned gaskets, the one or more spacer elements may include one or more spacer openings.
    In some embodiments of any of the aforementioned gaskets, the one or more spacer elements may comprise a solid element.
    In some embodiments of any of the aforementioned gaskets, the base plate and the one or more spacer elements may comprise a solid element.
    [0017] In any of the above-mentioned seals, the impactor plate, the base plate, and / or the one or more spacer elements may comprise all or part of a spring material.
    The present application and the resulting patent further provide a method for cooling a gasket positioned between turbine components. The method may include the steps of supplying cooling air flow to the gasket, urging the cooling air flow through one or more baffles in the gasket, crimping the gasket, and forcing the cooling air flow out of the gasket.
    The present application and the resulting patent further provide a turbine including a strip seal between adjacent components. The strip seal may include an impactor plate having one or more impact openings therein, a base plate, a first spacer on a first side of the strip seal, and a second spacer on a second side of the strip seal. A cooling flow achieves cooling through the impact openings of the roughing plate.
    In the aforementioned turbine, the base plate of the strip seal may have one or more base plate openings, one or more base plate exit slots, or a solid construction.
    Additionally or as an alternative, the one or more spacer elements of the strip seal may comprise a spring element or a material with a different coefficient of thermal expansion than the impact pad and / or the base plate.
    In any of the aforementioned turbines, the base plate and the one or more spacer elements of the strip seal may comprise a solid element.
    In some embodiments of the turbine of any of the above-mentioned types, the impactor plate, the base plate, and / or the one or more spacer elements of the strip seal may comprise a spring material in whole or in part.
    These and other features and improvements of the present application and the resulting patent will become apparent to one of ordinary skill in the art upon review of the following detailed description, taken in conjunction with the several drawings and the appended claims.
    BRIEF DESCRIPTION OF THE DRAWINGS
    [0025]<Tb> FIG. 1 <SEP> is a schematic diagram of a gas turbine illustrating a compressor, a combustor, a turbine, and a load.<Tb> FIG. Figure 2 shows a side view of a turbine illustrating a number of components positioned along a hot gas path.<Tb> FIG. Figure 3 shows a side cross-sectional view of a strip seal positioned between adjacent turbine components.<Tb> FIG. Figure 4 shows a side sectional view of a chilled strip seal as may be described herein.<Tb> FIG. FIG. 5 shows a top plan view of a base plate of the impact-cooled strip seal of FIG. 4. FIG.<Tb> FIG. FIG. 6 shows a side sectional view of an alternative embodiment of a bumped strip seal as may be described herein. FIG.<Tb> FIG. FIG. 7 shows a top plan view of a baseplate for use in the pulse-cooled strip seal of FIG. 7. FIG.<Tb> FIG. Figure 8 shows a side sectional view of an alternative embodiment of a bumped strip seal as may be described herein.<Tb> FIG. Figure 9 shows a side sectional view of an alternative embodiment of a chilled strip seal as may be described herein.<Tb> FIG. Fig. 10 shows a side sectional view of an alternative embodiment of a bumped strip seal as may be described herein.<Tb> FIG. Figure 11 shows a side sectional view of an alternative embodiment of a chilled strip seal as described herein.<Tb> FIG. Figure 12 shows a side sectional view of an alternative embodiment of a chilled strip seal as may be described herein.
    DETAILED DESCRIPTION
    Referring now to the drawings, wherein like reference numerals designate like elements throughout the several views, FIG. 1 is a schematic view of a gas turbine engine 10 as may be used herein. The gas turbine 10 may include a compressor 15. The compressor 15 compresses an incoming airflow 20. The compressor 15 delivers the compressed airflow 20 to a combustor 25. The combustor 25 mixes the compressed airflow 20 with a pressurized fuel flow 30 and ignites the mixture to produce a combustion gas flow 35. Although only a single combustor 25 is illustrated, the gas turbine engine 10 may include any number of combustors 25. The combustion gas flow 35 is in turn supplied to a turbine 40. The combustion gas flow 35 drives the turbine 40 so as to perform mechanical work. The mechanical work done in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50, such as an electric generator and the like. Other types of applications include aviation and the like.
    The gas turbine 10 may use natural gas, liquid fuels, various types of synthesis gas, and / or other types of fuels and mixtures of these. The gas turbine engine 10 may be any of a number of different gas turbines, such as those offered by General Electric Company of Schenectady, New York, including, but not limited to, those of a 7 or 9 series of heavy duty gas turbines, and the like be. The gas turbine 10 may have various configurations and may use various types of components. Other types of gas turbines may be used herein. Also, a plurality of gas turbines, other turbine types, and other types of power generation devices may be used together herein.
    FIG. 2 shows a portion of the turbine 40. Generally described, the turbine 40 may include a first stage vane 55, a first stage rotor 60, and a first stage shell ring 62 of a first turbine stage 65. Further, a second stage vane 70 of a second turbine stage 75 is illustrated. Any number of stages can be used herein. The vanes 55, 70 may be positioned on a nozzle 80. Any number of vanes 70 and nozzles 80 may be circumferentially disposed about an axis 85. Between each two adjacent shrouds 62, adjacent nozzles 80 and / or other turbine components, a strip seal 90 may be positioned to prevent the leakage of cooling airflows 20 from or through the compressor 15 therethrough. As described above, the strip seals 90 may have many different configurations. Other types of sealing mechanisms and techniques may be used.
    FIG. 3 shows an example of the strip seal 90 positioned between adjacent turbine components, a first component 91 and a second component 92. The turbine components 91, 92 may be adjacent turbine components, such as stator components and the like. The turbine components 91, 92 may define a sealing slot 94 therebetween. The strip seal 90 may be a seal made of a solid material, although other types of seals, such as layered seals, may be used. Any number of strip seals 90 may be used herein. The seals 90 prevent leakage of high pressure cooling air flow 97 into a lower pressure hot gas path 98. The seal 90, as illustrated herein, is for exemplary purposes only. Many other seal configurations can be used.
    Figures 4 and 5 show an example of a strip seal 100 as may be described herein. As described above, the strip seal 100 may be positioned between two adjacent gas turbine components, such as a first gas turbine component 110 and a second gas turbine component 120. In particular, the strip seal 100 may be positioned between two adjacent slot end surfaces of the first and second gas turbine components 110, 120 to prevent leakage of the cooling flow 97 into the hot gas path 98. The first and second gas turbine components 110, 120 may be shroud components, nozzles, or other types of gas turbine components. The first gas turbine component 110 may include a first sealing slot 130 disposed on a first slot end surface 140. The second gas turbine component 120 may include a second sealing slot 150 disposed on a second slot end surface 160. The strip seal 100 may be positioned in the first seal slot 130 and the second seal slot 150 to form a seal between the first slot end surface 140 and the second slot end surface 160. The strip seal 100 can thus completely or partially obstruct a slot face gap 170. The strip seal 100 may include a top 180, a bottom 190, a first end 200, and an opposite end 210. (The terms "bottom," "ground," "top," "side," "end," "first," "second," and the like are used for purposes of relative orientation only and not as an absolute position.) The strip seal 100 may be made of any suitable temperature resistant material.
    The strip seal 100 may include an impactor plate 220. The impactor plate 220 may include a number of baffles 230 therein. Although two (2) baffles 230 are illustrated, any number of baffles 230 may be used in any suitable size, shape, or configuration herein. The baffles 230 and their positioning may be configured to optimize heat transfer relative to the flow rate of the cooling flow 97. In addition, the seal 100 may also be optimized in terms of gradients, temperature, lifetime, and other types of parameters.
    The strip seal 100 may include a base plate 240. The base plate 240 may be of any suitable size, shape or configuration. The base plate 240 may include a number of base plate openings 250 therein. Although a single (1) base plate opening 250 is illustrated, any number of base plate openings 250 in any suitable size, shape or configuration may be used herein. The base plate openings 250 can increase the volume of the cooling flow 97 through the strip seal 100 so as to enhance the overall cooling. Alternatively, as illustrated below, the base plate 240 may also be a solid structure without any of the openings 250 therein.
    Between the impactor plate 220 and the base plate 240, one or more spacer elements 260 may be positioned. In this example, a first spacer 270 and a second spacer 280 may be used herein. Any number of spacers 260 in any suitable size, shape or configuration herein may be used. The spacers 260 may be positioned at the first end 200 and the second end 210 to provide the strip seal 100 in combination with the baller plate 220 and the base plate 240 in a box-like shape. Other positions and orientations may be used herein. The spacers 270, 280 may prevent or limit the loss of the cooling flow 97 from the ends 200, 210 of the strip seal 100.
    The spacers 260 may be a spring element 290 and the like. In particular, the spring elements 290 may be a flat spring and the like. Various types of spring materials can be used herein. Spacers 260 may have a substantially "C" -like shape, a "U" -like shape, a leaf spring shape, and other types of suitable shapes. The spring elements 290 can increase the contact force between the turbine components 110, 120 and the strip seal 100. This increased contact may increase the volume of the cooling flow 97 passing through the baffles 230 and may also reduce the total leakage flow therethrough. Alternatively, the spacer element 260 may be made of a different material compared to the impactor plate 220 and the base plate 240 to divide the plates 220, 240 apart as a result of a difference in the overall coefficient of thermal expansion. Other components and other configurations may be used herein.
    In use, the cooling flow 97 can be forced through the baffle openings 230 of the roughing plate 220. The baffles 230 may drive the cooling flow 97 to a number of discrete jets impacting the base plate 240 so as to provide enhanced cooling. The strip seal 100 may be combined with other types of seal cooling technologies and techniques to enable operation at very high temperatures. The strip seal 100 may thus result in lower maintenance costs and improved overall efficiency as operating temperatures exceed the material limits of conventional coats, such as metallic sheaths, ceramic matrix composite sheaths, and the like. The strip seal 100 thus utilizes all of the leakage flow therethrough to improve component life with minimal fluid losses.
    Figures 6 and 7 show an alternative embodiment of a strip seal 300 which may be described herein. The strip seal 300 may be substantially similar to the strip seal 100 described above, and may include the impactor plate 220, the base plate 240, and a pair of spacers 260. Instead of the base plate 240 containing the base plate openings 250, the base plate 240 herein may include a number of base plate outlet slots 310. The base plate outlet slots 310 may include a relatively narrow exit opening 320 within a substantially concave cavity 330. The base plate outlet slots 310 may be of any suitable size, shape or configuration. Any number of base plate outlet slots 310 may be used herein. Combinations of base plate openings 250 and base plate outlet slots 310 may also be used herein. Other components and other configurations may be used herein.
    FIG. 8 shows another embodiment of a strip seal 340 as may be described herein. The strip seal 340 may be substantially similar to the strip seal 100 described above and may include the impactor plate 220, the spacers 260 and the base plate 240. In this example, the base plate 240 may not include the base plate openings 250. Instead, the base plate 240 may be solid, and one or more of the spacers 260 may include one or more spacer openings 350 positioned therein. Any number of spacer openings 350 in any suitable size, shape or configuration herein may be used. The cooling flow 97 can thus escape via the spacer openings 350. In particular, the cooling flow 97 can enter via the spacer element openings 350 into the sealing slots 130, 150 and subsequently escape into the slot face gap. The strip seal 340 may be of any suitable size, shape or configuration. Other components and other configurations may be used herein.
    FIG. 9 shows another alternative embodiment of a strip seal 360 as may be described herein. The strip seal 360 may be substantially similar to the above-described strip seal 100 and may include the impactor plate 220, the base plate 240, and the spacers 260. In this example, the base plate 240 may not include the base plate opening 250. Rather, the base plate 240 may be solid. Likewise, the spacers 260 may not include spacer openings 350. Rather, the spacers 260 may be solid. In view of this, the strip seal 360 does not include any outlet openings at all. Rather, the entire cooling flow 97 can escape via a leakage flow. The strip seal 360 may be of any suitable size, shape or configuration. Other components and other configurations may be used herein.
    Fig. 10 shows another embodiment of a strip seal 370 as may be described herein. The strip seal 370 may be similar to the above-described strip seal 100 and may include the impactor plate 220, the base plate 240, and the spacers 260. The impactor plate 220 may include the baffle openings 230, and the base plate 240 may include one or more base plate openings 250. However, the spacers 260 may not be made from the spring element 290. Rather, the spacers 260 may each be a solid element 380. As described above, the solid members 380 can separate the plates 220, 240 from each other due to a different thermal expansion coefficient and the like. Various types of materials for different rates of thermal expansion can be used herein. The strip seal 170 may be of any suitable size, shape or configuration. Other components and other configurations may be used herein.
    Fig. 11 shows another embodiment of a strip seal 390 as may be described herein. The strip seal 390 may be substantially similar to the above-described strip seal 100 and may include the impactor plate 220, the base plate 240, and the spacers 260. The impactor plate 220 may include one or more impact openings 230, and the base plate 240 may include one or more base plate openings 250. In this example, the spacers 260 as well as the impactor plate 220 and the base plate 240 may be a spring clip 400 and the like. In view of this, all or part of the strip seal 390 may be made of a spring-like material. Various types of spring materials can be used herein. The strip seal 390 may be of any suitable size, shape or configuration. Other components and other configurations may be used herein.
    Fig. 12 shows another embodiment of a strip seal 410 as may be described herein. The strip seal 410 may be substantially similar to the above-described strip seal 100 and may include the impactor plate 220, the base plate 240, and the spacers 260. The impactor plate 220 may include one or more impact openings 230, and the base plate 240 may include one or more base plate openings 250. In this example, the spacers 260 may be substantially solid walls 420. The substantially solid walls 420 may be less resilient than, for example, the spring members 290 and the like. The substantially solid walls 420 may be any suitable size, shape or configuration. The strip seal 410 may instead include one or more spring members 290 positioned on top of the baller plate 220. The substantially solid walls 420 thus provide for a substantially constant distance between the impactor plate 220 and the base plate 240, while the spring elements 290 exert a high pressure on the impactor plate 220. This higher pressure may allow a wide spacing of the baffles 230 to achieve substantially uniform cooling of the base plate 240. The strip seal 410 may be of any suitable size, shape or configuration. Other components and other configurations may be used herein.
    The strip seals described herein thus enable a substantially uniform cooling flow rate to achieve improved cooling and extended overall seal life. In addition, the strip seals described herein can provide improved cooling with reduced secondary flows, higher overall machine efficiency, and reduced thermal output. Various configurations of strip seals may be used herein together. Other types of sealing technologies and techniques may be used herein. The strip seals can be original equipment parts or part of a retrofit measure.
    It should be apparent that the foregoing is merely specific embodiments of the present application and the resulting patent. Various changes and modifications may be made by those skilled in the art without departing from the broader spirit and scope of the invention as defined by the following claims and their equivalents.
    The present application provides a seal 100 for use between adjacent turbine components 110, 120 and with a cooling flow 97. The seal 100 may include an impactor plate 220, a base plate 240, and one or more spacers 260 therebetween. The cooling flow 97 provides cooling through the impactor plate 220.
    LIST OF REFERENCE NUMBERS
    [0045]<Tb> 10 <September> Gas Turbine<Tb> 15 <September> compressor<Tb> 20 <September> Air<Tb> 25 <September> combustion chamber<Tb> 30 <September> Fuel<Tb> 35 <September> combustion gases<Tb> 40 <September> Turbine<Tb> 45 <September> wave<Tb> 50 <September> Last<tb> 55 <SEP> First stage vane<tb> 60 <SEP> First Stage Blade<tb> 62 <SEP> First stage shroud<tb> 65 <SEP> First turbine stage<tb> 70 <SEP> second stage vane<tb> 75 <SEP> Second turbine stage<Tb> 80 <September> distributor<Tb> 85 <September> axis<Tb> 90 <September> Streifendichtun<tb> 91 <SEP> First component<tb> 92 <SEP> Second component<Tb> 94 <September> seal slot<Tb> 97 <September> KühIströmung<Tb> 98 <September> hot gas path<Tb> 100 <September> Streifendichtun<tb> 110 <SEP> First gas turbine component<tb> 120 <SEP> Second Gas Turbine Component<tb> 130 <SEP> First Sealing Slot<tb> 140 <SEP> First slot face<tb> 150 <SEP> Second Sealing Slot<tb> 160 <SEP> Second slot face<Tb> 170 <September> slot surface gap<Tb> 180 <September> top<Tb> 190 <September> bottom<tb> 200 <SEP> First End<tb> 210 <SEP> Second End<Tb> 220 <September> Impact top plate<Tb> 230 <September> impingement holes<Tb> 240 <September> baseplate<Tb> 250 <September> base plate openings<Tb> 260 <September> spacers<tb> 270 <SEP> First spacer element<tb> 280 <SEP> Second spacer<Tb> 290 <September> spring element<Tb> 300 <September> strip seal<Tb> 310 <September> Grundplattenauslassschlitze<Tb> 320 <September> outlet opening<tb> 330 <SEP> concave cavity<Tb> 340 <September> Streifendichtun<Tb> 350 <September> spacer openings<Tb> 360 <September> strip seal<Tb> 370 <September> strip seal<tb> 380 <SEP> Massive element<Tb> 390 <September> strip seal<Tb> 400 <September> spring clip<Tb> 410 <September> strip seal<tb> 420 <SEP> Solid walls
    权利要求:
    Claims (10)
    [1]
    A seal (100) for use between adjacent turbine components (110, 120) and having a cooling flow (97), comprising:an impactor plate (220);a base plate (240); andone or more spacer elements (260) therebetween;wherein the cooling flow (97) achieves cooling through the roughing plate (220).
    [2]
    The seal (100) of claim 1, wherein the impactor plate (220) has one or more impact openings (230) therein; and orwherein the base plate (240) has one or more base plate openings (250) therein; and orwherein the base plate (240) has a solid construction.
    [3]
    The seal (100) of claim 1 or 2, wherein the base plate (240) has one or more base plate outlet slots (310); wherein the one or more base plate outlet slots (310) preferably include an exit opening (320) within a cavity (330).
    [4]
    The seal (100) of any one of the preceding claims, wherein the one or more spacer elements (260) include a first spacer (270) positioned at a first end (200) of the seal (100) and a second spacer (10). 280) positioned at a second end (210) of the seal (100).
    [5]
    5. A seal (100) according to any one of the preceding claims, wherein the one or more spacer elements (260) comprise a spring element (290); and / or wherein the one or more spacer elements (260) have a "C" like shape.
    [6]
    The seal (100) of any of the preceding claims, wherein the one or more spacer elements (260) comprise a material having a different coefficient of thermal expansion than the impactor plate (220) and / or the base plate (240); and / or wherein the one or more spacer elements (260) comprise one or more spacer openings (350).
    [7]
    The seal (100) of any one of the preceding claims, wherein the one or more spacer elements (260) comprise a solid element (380); or wherein the baseplate (240) and the one or more spacer elements (260) comprise a solid element.
    [8]
    8. Seal according to one of the preceding claims, wherein the impact pad (220), the base plate (240) and / or the one or more spacer elements (260) have a spring material (400) wholly or partly.
    [9]
    9. A method of cooling a gasket (100) positioned between turbine components (110, 120), comprising:Supplying a cooling air flow (97) to the seal (100);Urging the cooling air flow (97) through one or more baffles (230) in the seal (100);Impingement cooling of the gasket (100); andUrging the cooling air flow (97) out of the seal (100).
    [10]
    10. A turbine including a strip seal (100) between adjacent components (110, 120), the strip seal (100) comprising:a baffle plate (220) having one or more baffles (230) therein;a base plate (240);a first spacer (270) on a first side of the strip seal (100); anda second spacer (280) on a second side of the strip seal (100);wherein a cooling flow (97) achieves cooling through the baffles (230) of the baffle plate (220).
    类似技术:
    公开号 | 公开日 | 专利标题
    CH711138A2|2016-11-30|Impact-cooled strip seal.
    DE60210684T2|2007-05-16|Seal of a turbine shroud ring
    DE102012100521A1|2012-07-26|Arrangement for preventing fluid flow
    DE102015101156A1|2015-07-30|High chord blade, two partial span damper elements and curved dovetail
    DE102010060280A1|2011-05-12|Airfoil heat shield
    DE102015100874A1|2015-07-30|Sealing device for providing a seal in a turbomachine
    EP2300686B1|2013-08-07|Gas turbine comprising a guide vane
    DE102008002890A1|2008-12-24|Alternately cooled turbine stator
    DE102011000299A1|2011-12-15|heat shield
    DE112008003522T5|2010-10-21|The turbine nozzle
    DE2555049A1|1976-06-16|COOLED TURBINE BLADE
    EP1848904B1|2009-01-14|Sealing element for use in turbomachinery
    CH707899A2|2014-10-15|Turbo engine cooling structure.
    EP1934523B1|2014-10-29|Combustion chamber and gas turbine plant
    EP2084368A1|2009-08-05|Turbine blade
    DE102011052937A1|2012-03-15|Turbine blade platform cooling systems
    WO2004090423A1|2004-10-21|Heat shield element
    DE4100554A1|1991-08-14|DEVICE FOR GASKET SEALING BETWEEN NEXT SEGMENTS OF TURBINE GUIDE BLADES AND SHEET RINGS
    DE102008055573A1|2009-07-02|The turbine nozzle
    DE102010037858A1|2011-04-14|Radial sealing pin
    DE102005046731A1|2006-11-02|Heat shield arrangement
    EP2236759A1|2010-10-06|Rotor blade system
    DE102014115476A1|2015-04-30|Hot gas path component with impact and foot cooling
    DE102014211590A1|2015-12-17|Gas turbine generator cooling
    WO2004023042A1|2004-03-18|Gas turbine combustion chamber
    同族专利:
    公开号 | 公开日
    CN106194277A|2016-12-07|
    DE102016108804A1|2016-12-01|
    JP6890930B2|2021-06-18|
    JP2016223444A|2016-12-28|
    CN106194277B|2020-09-22|
    US20160348535A1|2016-12-01|
    US9869201B2|2018-01-16|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4752184A|1986-05-12|1988-06-21|The United States Of America As Represented By The Secretary Of The Air Force|Self-locking outer air seal with full backside cooling|
    US5048288A|1988-12-20|1991-09-17|United Technologies Corporation|Combined turbine stator cooling and turbine tip clearance control|
    US5092735A|1990-07-02|1992-03-03|The United States Of America As Represented By The Secretary Of The Air Force|Blade outer air seal cooling system|
    US5823741A|1996-09-25|1998-10-20|General Electric Co.|Cooling joint connection for abutting segments in a gas turbine engine|
    EP1130218A1|2000-03-02|2001-09-05|Siemens Aktiengesellschaft|Turbine with sealings for the stator platforms|
    US6340285B1|2000-06-08|2002-01-22|General Electric Company|End rail cooling for combined high and low pressure turbine shroud|
    GB0108398D0|2001-04-04|2001-05-23|Siemens Ag|Seal element for sealing a gap and combustion turbine having a seal element|
    US6412270B1|2001-09-12|2002-07-02|General Electric Company|Apparatus and methods for flowing a cooling or purge medium in a turbine downstream of a turbine seal|
    US7217081B2|2004-10-15|2007-05-15|Siemens Power Generation, Inc.|Cooling system for a seal for turbine vane shrouds|
    US20070009349A1|2005-07-11|2007-01-11|General Electric Company|Impingement box for gas turbine shroud|
    GB0703827D0|2007-02-28|2007-04-11|Rolls Royce Plc|Rotor seal segment|
    US8439629B2|2007-03-01|2013-05-14|United Technologies Corporation|Blade outer air seal|
    US8303247B2|2007-09-06|2012-11-06|United Technologies Corporation|Blade outer air seal|
    US8684680B2|2009-08-27|2014-04-01|Pratt & Whitney Canada Corp.|Sealing and cooling at the joint between shroud segments|
    EP2378071A1|2010-04-16|2011-10-19|Siemens Aktiengesellschaft|Turbine assembly having cooling arrangement and method of cooling|
    US8678754B2|2011-01-24|2014-03-25|General Electric Company|Assembly for preventing fluid flow|
    US20130028713A1|2011-07-25|2013-01-31|General Electric Company|Seal for turbomachine segments|
    US20130108420A1|2011-10-26|2013-05-02|General Electric Company|Layered spline seal assembly for gas turbines|
    US20140091531A1|2012-10-03|2014-04-03|General Electric Company|Spline seal with cooling pathways|
    WO2015009392A2|2013-07-19|2015-01-22|General Electric Comapny|Turbine nozzle with impingement baffle|GB201603556D0|2016-03-01|2016-04-13|Rolls Royce Plc|An intercomponent seal for a gas turbine engine|
    US10436041B2|2017-04-07|2019-10-08|General Electric Company|Shroud assembly for turbine systems|
    US10934873B2|2018-11-07|2021-03-02|General Electric Company|Sealing system for turbine shroud segments|
    US11111794B2|2019-02-05|2021-09-07|United Technologies Corporation|Feather seals with leakage metering|
    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 |
    2019-09-13| AZW| Rejection (application)|
    优先权:
    申请号 | 申请日 | 专利标题
    US14/725,004|US9869201B2|2015-05-29|2015-05-29|Impingement cooled spline seal|
    [返回顶部]