• 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 turbomachine (2) includes a turbine section (4) containing a turbine inlet (12). A transition piece (10) includes a transition piece inlet (30) and a transition piece outlet (31). A ceramic matrix composite (CMC) bridge member (54, 55) connects the transition piece outlet (31) to the turbine inlet (12).
    公开号:CH703864B1
    申请号:CH01548/11
    申请日:2011-09-16
    公开日:2016-01-15
    发明作者:Jeffrey John Butkiewicz；Andres Jose Garcia-Crespo；Stanley Frank Simpson
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Background to the invention
    The subject matter disclosed herein relates to a turbo-machine having a ceramic matrix composite bridge connecting a transition piece to a turbine section of a turbomachine.
    Generally, gas turbine engines burn a fuel / air mixture that releases heat energy to form a high temperature gas stream. The high temperature gas stream is directed to a turbine section via a hot gas path. The turbine section converts the heat energy from the high temperature gas stream into mechanical energy that rotates a turbine shaft. The turbine section may be used in a variety of applications, such as providing power to a pump or an electric generator.
    Many gas turbine engines include an annular combustor in which combustion gases are generated which form the high temperature gas stream. Other turbomachines use multiple combustors arranged in an annular array. In such a turbomachine, the hot gas path includes a transition piece connecting a group of combustion chambers to a first stage of the turbine section. The combustion gases generated in the combustor group are delivered through the transition piece to the turbine section.
    The transition piece / turbine section interface is usually exposed to high temperatures and thus requires cooling to extend component life.
    Object of the present invention is, therefore, the transition piece / turbine section interface to design so that it withstands without adverse effects and without the need for a cooling air flow higher temperatures.
    Brief description of the invention
    The invention relates to a turbomachine having a turbine section with a turbine inlet and a transition piece with a transition piece inlet and a transition piece outlet. A ceramic matrix composite (CMC) bridge element connects the transition piece outlet to the turbine inlet.
    Further advantageous embodiments of the invention will become apparent from the following description taken in conjunction with the drawings.
    Brief description of the drawings
    The accompanying drawings show:<Tb> FIG. 1 <SEP> is a partial cross-sectional view of a turbomachine including a ceramic matrix composite (CMC) bridge that includes first and second CMC bridge members that seal a junction between a transition piece and a turbine section according to an exemplary embodiment;<Tb> FIG. Fig. 2 <SEP> is a bottom right perspective view of the first CMC bridge element of Fig. 1;<Tb> FIG. 3 <SEP> is a cross-sectional side view of a CMC bridge element according to another exemplary embodiment;<Tb> FIG. 4 <SEP> is a cross-sectional side view of a CMC bridge element according to yet another exemplary embodiment; and<Tb> FIG. 5 <SEP> is a cross-sectional side view of a CMC bridge element according to yet another exemplary embodiment.
    The detailed description explains embodiments of the invention together with advantages and features by way of example with reference to the drawings.
    Detailed description of the invention
    The terms "axial" and "axial" as used in this application refer to directions and orientations that are substantially parallel to a central longitudinal axis of a turbomachine. The terms "radial" and "radial" as used in this application refer to directions and orientations that are substantially perpendicular to the central longitudinal axis of the turbomachine. The terms "upstream" and "downstream" as used in this application refer to directions and orientations relative to an axial flow direction with respect to the central longitudinal axis of the turbomachine.
    Referring to FIG. 1, a turbomachine 2 includes a turbine section 4 which is fluidly connected to a combustor (not shown) via a transition piece 10. The turbine section 4 includes a turbine section inlet 12 defined by an end wall 14. A first stage 16 of the turbine section 4 is located downstream of the turbine section inlet 12. The first stage 16 includes a plurality of vanes 17, only one of which is shown in FIG. 1, which directs combustion gases 18 to a plurality of first stage buckets 19, only one of which is shown in FIG. The combustion gases 18 flow axially into a transition piece inlet 30, pass through the transition piece 10, and enter the turbine section inlet 12 out of a transition piece outlet 31. At this point, the combustion gases 18 pass the vanes 17 before acting on the blades 19. The blades 19 convert thermal and kinetic energy from the combustion gases 18 into mechanical rotational energy used to rotate a shaft (not shown). In addition to the combustion gases 18, compressor discharge air 37 from a compressor section (not shown) enters an impeller clearance section 40 of the turbine section 4.
    According to an exemplary embodiment, the turbomachine 2 includes a ceramic matrix composite (CMC) bridge 47 connecting the transition piece outlet 31 to the turbine section inlet 12. According to the exemplary embodiment, the CMC bridge 47 is formed of silicon carbide-silicon carbide (SiC-SiC) composites, oxide-oxide composites, and / or silicon nitride composites. Of course, it should be understood that various other CMC materials can be used. The CMC bridge 47 includes a first CMC bridge element 54 disposed at an outer junction between the transition piece outlet 31 and the turbine section inlet 12, and a second CMC bridge element 55 located at an inner junction is disposed between the transition piece outlet 31 and the turbine section inlet 12. The first CMC bridge member 54 includes a main body 56 having an outer surface 57 and an inner surface 58. Likewise, the second CMC bridge member 55 includes a main body 59 having an outer surface 60 and an inner surface 61.
    The first CMC bridge element 54 includes a flow guide 64 which is disposed on the inner surface 58. The flow guide 64 directs combustion gases 18 away from the end wall 14. Similarly, the second CMC bridge member 55 includes a flow guide 66 disposed on the inner surface 61. The flow guide 66 directs combustion gases 18 away from the end wall 14 and / or interferes with crossflow vortex generation. In this arrangement, the end wall 14 is protected against damage that may result from exposure to combustion gases 18. In particular, combustion gases entering an inlet section 68 of the CMC bridge element 54 flow past the flow guide 64. The flow guide 64 directs the combustion gases 18 through an outlet portion 69 of the CMC bridge member 54 on a path that extends at an angle away from the end wall 14. Combustion gases entering an inlet section 71 of the CMC bridge member 55 similarly flow over the flow guide 66. The flow guide 66 directs the combustion gases 18 through an outlet section 72 of the CMC bridge member 55 on a path which is at an angle from the end wall 14 away.
    As best illustrated in FIG. 2, the first bridge member 54 includes a first portion 76 defining a first flange 77. The first section 76 leads to a second section 79, which is aligned substantially perpendicular to the first section 76. A third section 82 extends from the second section 79 and extends substantially parallel to the first section 76. A fourth section 85, which is substantially parallel to the second section 79, extends from the third section 82. A fifth portion 88, which is substantially parallel to the first and third portions 76 and 82, extends from the fourth portion 85. The third, fourth and fifth sections 82, 85 and 88, in combination with one another, form a second flange 89 connecting the first CMC bridge element 54 to the turbine section 4. In addition, the bridge member 54 includes first and second fasteners 90 and 91 formed in the second flange 89. Mechanical fasteners, one of which is indicated at 96 in FIG. 1, pass through the fasteners 90, 91 and the turbine section 4 to connect the first CMC bridge member 54 to the turbine section 4. The second flange 89 further includes a plurality of mounting members 98 and 99 that are aligned with pins (not shown) to position the first CMC bridge member 54 on the turbine section 4. Finally, the turbomachine 2 is illustrated as including first and second resilient seals 104 and 106 configured to communicate combustion gases at exit at the interface between the transition piece outlet 31 and the associated one inlet section 68 and 71 of the first and second, respectively CMC bridge element 54 and 55 to prevent.
    Reference is now made to Fig. 3, wherein like reference characters designate corresponding parts throughout the several views to describe a CMC bridge element 116 constructed in accordance with another exemplary embodiment. As will become more fully apparent below, the CMC bridge member 116 is secured to the turbine section 4 via a retaining ring 118 disposed on the turbine section inlet 12. The CMC bridge member 116 includes a main body 123 that includes an outer surface 130 and an inner surface 131 that defines an inlet portion 134 and an outlet portion 135. The CMC bridge member 116 includes a first flange 140 disposed on the inlet portion 134 and a second flange 143 disposed on the outlet portion 135. A fastener 147 extends substantially perpendicularly from the outer surface 130. The fastener 147 includes a dovetailed portion 149 which cooperates with a corresponding (not separately designated) structure on the retaining ring 118 to secure the CMC bridge member 116 to the turbomachine 2. As further illustrated in FIG. 3, a first resilient seal 154 extends between the inlet section 134 and the transition piece outlet 31, and a second resilient seal 157 extends between the outlet section 135 and the turbine section inlet 112 to prevent compressor exit air from entering the combustion chamber to flow around and enter the turbine inlet 12.
    Referring now to Figure 4, like reference characters represent corresponding parts throughout the several views to describe a CMC bridge member 167 constructed in accordance with another exemplary embodiment. The CMC bridge member 167 includes a main body 170 that includes an outer surface 172 and an inner surface 173 that defines an inlet portion 176 and an outlet portion 177. The CMC bridge member 167 includes a first flange 180 disposed on the inlet portion 176. The first flange 180 is secured to the transition piece outlet 31 via a mechanical fastener 181. The CMC bridge member 167 further includes a second flange 183 disposed on the outlet portion 177. In the illustrated exemplary embodiment, the transition piece 10 includes an air passage 185 disposed at the transition piece outlet 31. The air channel 185 conducts a cooling fluid, e.g. Compressor outlet air, on the first flange 180 to reduce temperatures of the CMC bridge element 167. As further illustrated in FIG. 4, an elastic seal 187 extends between the outlet portion 177 and the turbine portion inlet 12 to prevent compressor discharge air from flowing around the combustion chamber and entering the turbine inlet 12.
    Referring now to Figure 5, like reference characters represent corresponding parts throughout the several views to describe a CMC bridge member 197 constructed in accordance with yet another exemplary embodiment. The CMC bridge member 197 includes a main body 200 that includes an outer surface 204 and an inner surface 205 that defines an inlet portion 209 and an outlet portion 210. The CMC bridge member 167 includes a first flange 214 disposed on the inlet portion 209 and a second flange 217 disposed on the outlet portion 210. The second flange 217 is secured to the turbine section inlet 12 via a fastener 220. The fastener 220 includes a slide connector (not illustrated) that engages an associated structure on the turbine section 4. The CMC bridge member 197 further includes an elastic seal 224 extending between the inlet portion 209 and the transition piece outlet 31 to prevent compressor discharge air from flowing around the combustion chamber and entering the turbine inlet 12.
    At this point, it should be understood that the CMC bridge elements according to the exemplary embodiments provide a seal between the transition piece / turbine section boundary to limit and / or prevent compressor exit air from entering the turbine inlet , The transition piece / turbine section interface is usually exposed to high temperatures and thus requires cooling to extend component life. In contrast, the present invention provides a bridge made of CMC materials that are capable of withstanding high temperatures without compromising. By using the CMC bridge elements according to the exemplary embodiments, the need for cooling air flow at the transition piece / turbine section interface is significantly reduced, thereby improving turbomachinery efficiency. The reduced cooling flow provides additional flow that can be used to extract work from the turbine.
    While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments.
    LIST OF REFERENCE NUMBERS
    [0020]<Tb> 2 <September> turbomachinery<Tb> 4 <September> turbine section<Tb> 6 <September> combustion chamber<Tb> 10 <September> transition piece<Tb> 12 <September> turbine section inlet<Tb> 14 <September> end wall<tb> 16 <SEP> First Stage (4)<tb> 17 <SEP> First stage vane<Tb> 18 <September> combustion gases<tb> 19 <SEP> First Stage Blade (Downstream)<tb> 21 <SEP> wave (not illustrated)<Tb> 30 <September> transition piece inlet<Tb> 31 <September> Übergangsstückauslass<tb> 37 <SEP> Compressor outlet air (axial flow)<Tb> 40 <September> impeller clearance section<Tb> 47 <September> Bridge<Tb> 48 <September> CMC<tb> 54 <SEP> First bridge element<tb> 55 <SEP> Second bridge element<tb> 56, 59, 123, 170, 200 <SEP> main body<tb> 57, 60, 130, 172, 204 <SEP> Outer surface (54)<tb> 58, 61, 131, 173, 205 <SEP> Inner surface (54)<tb> 64, 66 <SEP> Flow Management, Guiding Device (55)<tb> 68, 71, 134, 176, 209 <SEP> inlet section (54)<tb> 69, 72, 135, 177, 210 <SEP> Outlet Section (55)<tb> 76 <SEP> First section<tb> 77, 140, 180, 214 <SEP> First flange<tb> 79 <SEP> Second Section<tb> 82 <SEP> Third Section<tb> 85 <SEP> Fourth Section<tb> 88 <SEP> Fifth Section<tb> 89, 143, 183, 217 <SEP> Second flange<tb> 90, 91, 147, 220 <SEP> Fastener<tb> 96 <SEP> Mechanical fastener<tb> 98, 99 <SEP> Mounting element<tb> 104, 106, 187, 224 <SEP> Elastic Seal (54)<tb> 116, 167, 197 <SEP> CMC Bridge Element<Tb> 118 <September> retaining ring<tb> 149 <SEP> Dovetailed section<tb> 154 <SEP> First elastic seal<tb> 157 <SEP> Second elastic seal<tb> 181 <SEP> Mechanical fastener<Tb> 185 <September> air duct
    权利要求:
    Claims (10)
    [1]
    1. Turbomachine (2), comprising:a turbine section (4) containing a turbine inlet (12);a transition piece (10) including a transition piece inlet (30) and a transition piece outlet (31); andat least one ceramic matrix composite bridge member (116, 167, 197) interconnecting the transition piece outlet (31) and the turbine inlet (12).
    [2]
    The turbomachine (2) of claim 1, wherein the ceramic matrix composite bridge member (116, 167, 197) has an outer surface (57, 60, 130, 172, 204) and an inner surface (58, 61, 131, 173, 205 In operation, the combustion gas (18) flowing from the transition piece (10) into the turbine section (4) faces and faces, the inner surface (58, 61, 131, 173, 205) comprising a flow guide (64, 66 ) adapted to direct combustion gases (18) into the turbine inlet (12).
    [3]
    The turbomachine (2) of claim 2, wherein the flow directing means (64, 66) is arranged and arranged to direct combustion gases (18) from a portion of an end wall (14) of the turbine inlet (12).
    [4]
    The turbomachine (2) of claim 1, wherein said at least one ceramic matrix composite bridge member (116, 167, 197) comprises a main body (56, 59, 123, 170, 200) having an inlet portion (68, 71, 134 , 176, 209) operatively connected to the transition piece (10) and an outlet portion (69, 72, 135, 177, 210) operatively connected to the turbine portion (4).
    [5]
    The turbomachine (2) of claim 4, wherein the at least one ceramic matrix composite bridge member (116, 167, 197) includes a first flange (77, 140, 180, 214) attached to the inlet portion (68, 71, 134, 176, 209) and a second flange (89, 143, 183, 217) disposed on the outlet portion (69, 72, 135, 177, 210).
    [6]
    A turbomachine (2) according to claim 5, wherein either the first flange (180, 214) is attached to the combustion chamber (6) or the second flange (183, 217) is attached to the turbine section (4).
    [7]
    7. A turbomachine (2) according to claim 6, further comprising a sealing member (187, 224) disposed between the second flange (183) and the turbine section (4), provided that the first flange (180) on the combustion chamber (6 ), or disposed between the first flange (214) and the transition piece (10), as long as the second flange (217) is fixed to the turbine section (4).
    [8]
    The turbomachine (2) of claim 5 wherein the at least one ceramic matrix composite bridge member (116, 167, 197) includes a fastener (147) disposed between the first (140) and second flanges (143) of the main body (123) projects radially outwards.
    [9]
    The turbomachine (2) of claim 8, further comprising: a retaining ring (118) operatively connected to the turbine section (4), the at least one bridge element (116) being secured to the retaining ring (118) via the fastener (147) ) is secured.
    [10]
    The turbomachine (2) of claim 9, further comprising two seal members, a first seal member (154) disposed between the first flange (140) and the combustion chamber (6), and a second seal member (157) interposed between the second flange (143) and the turbine section (4) is arranged.
    类似技术:
    公开号 | 公开日 | 专利标题
    CH703864B1|2016-01-15|Turbo machine with a bridge made of ceramic matrix composite |
    US10301960B2|2019-05-28|Shroud assembly for gas turbine engine
    EP1736635B1|2012-05-02|Air transfer system between compressor and turbine of a gas turbine engine
    DE102010017362A1|2010-12-16|Mechanical connection for a gas turbine engine
    DE102008002932B4|2021-06-24|Clamp plate seal
    DE4447507A1|1998-01-29|Annular seal
    US10233775B2|2019-03-19|Engine component for a gas turbine engine
    DE2261443A1|1973-07-05|TURBINE ARRANGEMENT WITH TWO-CURRENT COOLING FOR GAS TURBINE ENGINES
    EP3064706A1|2016-09-07|Guide blade assembly for a flow engine with axial flow
    EP2696037A1|2014-02-12|Sealing of the flow channel of a fluid flow engine
    US10815789B2|2020-10-27|Impingement holes for a turbine engine component
    DE102015102396A1|2015-08-20|Turbine blade and method for balancing a tip shroud of a turbine blade and gas turbine
    EP2084368A1|2009-08-05|Turbine blade
    DE112011104298B4|2021-01-21|Gas turbine engine with secondary air circuit
    CH709047A2|2015-06-30|Turbine blade and method for cooling a turbine blade of a gas turbine.
    US20160319680A1|2016-11-03|Blade/disk dovetail backcut for blade/disk stress reduction for a second stage of a turbomachine
    EP0806547A1|1997-11-12|Axial turbine for turbochargers
    US20170356298A1|2017-12-14|Stator vane
    EP1731715A1|2006-12-13|Transition between a combustion chamber and a turbine
    EP3029269A1|2016-06-08|Turbine rotor blade, corresponding rotor and turbomachine
    DE112017002151T5|2019-01-10|COMPRESSOR DIFFUSER AND GAS TURBINE
    US20140033733A1|2014-02-06|Flow discharge device
    US20160341053A1|2016-11-24|Turbomachine diffuser including flow mixing lobes and method
    CH710372A2|2016-05-13|Turbo machine with a sealing element for variable flushing flow between a transition piece and a Turbinenabschnit.
    WO2015000830A2|2015-01-08|Rotor for a turbine
    同族专利:
    公开号 | 公开日
    JP2012067745A|2012-04-05|
    JP5548661B2|2014-07-16|
    CN102418602A|2012-04-18|
    US8347636B2|2013-01-08|
    CH703864A2|2012-03-30|
    US20120073304A1|2012-03-29|
    CN102418602B|2016-01-06|
    DE102011053534A1|2012-03-29|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5265412A|1992-07-28|1993-11-30|General Electric Company|Self-accommodating brush seal for gas turbine combustor|
    US5687572A|1992-11-02|1997-11-18|Alliedsignal Inc.|Thin wall combustor with backside impingement cooling|
    US5657998A|1994-09-19|1997-08-19|General Electric Company|Gas-path leakage seal for a gas turbine|
    IN187185B|1995-04-25|2002-02-23|Siemens Ag|
    JP2000502039A|1995-12-15|2000-02-22|ウエスチングハウス・エレクトリック・コーポレイション|Oxide-based ceramic composites, devices, methods and components for high temperature environments|
    WO1997047784A1|1996-06-13|1997-12-18|Siemens Aktiengesellschaft|Article with a protective coating system comprising an improved anchoring layer and its manufacture|
    JP2000517397A|1996-09-04|2000-12-26|シーメンスアクチエンゲゼルシヤフト|Turbine blades exposed to hot gas flow|
    US6835465B2|1996-12-10|2004-12-28|Siemens Westinghouse Power Corporation|Thermal barrier layer and process for producing the same|
    JP2002502462A|1997-05-28|2002-01-22|シーメンスアクチエンゲゼルシヤフト|Gradient material of metal and ceramic, product thereof, and method of manufacturing gradient material of metal and ceramic|
    DE59802578D1|1997-11-03|2002-01-31|Siemens Ag|PRODUCT DESIGNED FOR HOT GAS APPLICATION AND METHOD FOR PRODUCING A COATING FOR THIS PRODUCT|
    US6111599A|1998-01-14|2000-08-29|Westinghouse Savannah River Company|Apparatus for observing a hostile environment|
    DE69908990T2|1998-01-29|2004-05-19|Coi Ceramics, Inc., San Diego|Process for the production of sized coated ceramic fibers|
    US6013592A|1998-03-27|2000-01-11|Siemens Westinghouse Power Corporation|High temperature insulation for ceramic matrix composites|
    US6733907B2|1998-03-27|2004-05-11|Siemens Westinghouse Power Corporation|Hybrid ceramic material composed of insulating and structural ceramic layers|
    US6197424B1|1998-03-27|2001-03-06|Siemens Westinghouse Power Corporation|Use of high temperature insulation for ceramic matrix composites in gas turbines|
    US6676783B1|1998-03-27|2004-01-13|Siemens Westinghouse Power Corporation|High temperature insulation for ceramic matrix composites|
    US7563504B2|1998-03-27|2009-07-21|Siemens Energy, Inc.|Utilization of discontinuous fibers for improving properties of high temperature insulation of ceramic matrix composites|
    US7179524B2|1998-03-27|2007-02-20|Siemens Power Generation, Inc.|Insulated ceramic matrix composite and method of manufacturing|
    US6743393B1|1998-06-17|2004-06-01|Coi Ceramics, Inc.|Method for producing ceramic matrix composites|
    US6106959A|1998-08-11|2000-08-22|Siemens Westinghouse Power Corporation|Multilayer thermal barrier coating systems|
    DE59904234D1|1998-09-21|2003-03-13|Siemens Ag|METHOD FOR INTERIOR WORKING A HOLLOW COMPONENT|
    JP2002528643A|1998-10-22|2002-09-03|シーメンスアクチエンゲゼルシヤフト|Product with heat insulation layer and method of making heat insulation layer|
    US6350713B1|1998-11-24|2002-02-26|Dow Corning Corporation|Ceramic matrix composites|
    US6933060B2|1999-02-05|2005-08-23|Siemens Westinghouse Power Corporation|Thermal barrier coating resistant to sintering|
    US6235370B1|1999-03-03|2001-05-22|Siemens Westinghouse Power Corporation|High temperature erosion resistant, abradable thermal barrier composite coating|
    JP4031590B2|1999-03-08|2008-01-09|三菱重工業株式会社|Combustor transition structure and gas turbine using the structure|
    US6060174A|1999-05-26|2000-05-09|Siemens Westinghouse Power Corporation|Bond coats for turbine components and method of applying the same|
    US6296945B1|1999-09-10|2001-10-02|Siemens Westinghouse Power Corporation|In-situ formation of multiphase electron beam physical vapor deposited barrier coatings for turbine components|
    US6294260B1|1999-09-10|2001-09-25|Siemens Westinghouse Power Corporation|In-situ formation of multiphase air plasma sprayed barrier coatings for turbine components|
    US6641907B1|1999-12-20|2003-11-04|Siemens Westinghouse Power Corporation|High temperature erosion resistant coating and material containing compacted hollow geometric shapes|
    US20080101683A1|1999-12-22|2008-05-01|Siemens Power Generation, Inc.|System and method of evaluating uncoated turbine engine components|
    EP1126221A1|2000-02-17|2001-08-22|Siemens Aktiengesellschaft|Padded refactory tile as liner for a gas turbine combustor|
    US6977060B1|2000-03-28|2005-12-20|Siemens Westinghouse Power Corporation|Method for making a high temperature erosion resistant coating and material containing compacted hollow geometric shapes|
    US6384365B1|2000-04-14|2002-05-07|Siemens Westinghouse Power Corporation|Repair and fabrication of combustion turbine components by spark plasma sintering|
    US6528190B1|2000-08-02|2003-03-04|Siemens Westinghouse Power Corporation|Fiber coating compounds for reinforced ceramic matrix composites|
    US6258467B1|2000-08-17|2001-07-10|Siemens Westinghouse Power Corporation|Thermal barrier coating having high phase stability|
    US6670046B1|2000-08-31|2003-12-30|Siemens Westinghouse Power Corporation|Thermal barrier coating system for turbine components|
    US6514046B1|2000-09-29|2003-02-04|Siemens Westinghouse Power Corporation|Ceramic composite vane with metallic substructure|
    US6512379B2|2001-02-05|2003-01-28|Siemens Westinghouse Power Corporation|Condition monitoring of turbine blades and vanes in service|
    US6939603B2|2001-03-22|2005-09-06|Siemens Westinghouse Power Corporation|Thermal barrier coating having subsurface inclusions for improved thermal shock resistance|
    GB0108398D0|2001-04-04|2001-05-23|Siemens Ag|Seal element for sealing a gap and combustion turbine having a seal element|
    US20020197465A1|2001-04-24|2002-12-26|Butner Steven Carl|Damage tolerant CMC using sol-gel martix slurry|
    US6719853B2|2001-04-27|2004-04-13|Siemens Aktiengesellschaft|Method for restoring the microstructure of a textured article and for refurbishing a gas turbine blade or vane|
    US6617013B2|2001-05-10|2003-09-09|Siemens Westinghouse Power Corporation|Ceramic matrix composite having improved interlaminar strength|
    US6846574B2|2001-05-16|2005-01-25|Siemens Westinghouse Power Corporation|Honeycomb structure thermal barrier coating|
    US6703137B2|2001-08-02|2004-03-09|Siemens Westinghouse Power Corporation|Segmented thermal barrier coating and method of manufacturing the same|
    US6602053B2|2001-08-02|2003-08-05|Siemens Westinghouse Power Corporation|Cooling structure and method of manufacturing the same|
    US7080513B2|2001-08-04|2006-07-25|Siemens Aktiengesellschaft|Seal element for sealing a gap and combustion turbine having a seal element|
    US7001679B2|2001-08-09|2006-02-21|Siemens Westinghouse Power Corporation|Protective overlayer for ceramics|
    US6746755B2|2001-09-24|2004-06-08|Siemens Westinghouse Power Corporation|Ceramic matrix composite structure having integral cooling passages and method of manufacture|
    US7541005B2|2001-09-26|2009-06-02|Siemens Energy Inc.|Catalytic thermal barrier coatings|
    US6884384B2|2001-09-27|2005-04-26|Siemens Westinghouse Power Corporation|Method for making a high temperature erosion resistant material containing compacted hollow geometric shapes|
    US7017415B2|2001-09-27|2006-03-28|Siemens Westinghouse Power Corporation|Apparatus for sensing pressure fluctuations in a hostile environment|
    US6827312B2|2001-11-27|2004-12-07|Coi Ceramics, Inc.|Method and system of thermal protection|
    US6930066B2|2001-12-06|2005-08-16|Siemens Westinghouse Power Corporation|Highly defective oxides as sinter resistant thermal barrier coating|
    US6528178B1|2001-12-17|2003-03-04|Siemens Westinghouse Power Corporation|High temperature resistant article with improved protective coating bonding and method of manufacturing same|
    DE60105830T2|2001-12-21|2006-03-09|Siemens Ag|Method for removing a metal layer of a layer system|
    EP1329592A1|2002-01-18|2003-07-23|Siemens Aktiengesellschaft|Turbine with at least four stages and utilisation of a turbine blade with reduced mass|
    US6902360B2|2002-02-08|2005-06-07|General Electric Company|Method of cutting a hole in a composite material workpiece|
    EP1352989A1|2002-04-10|2003-10-15|Siemens Aktiengesellschaft|Object having a masking layer|
    US6677064B1|2002-05-29|2004-01-13|Siemens Westinghouse Power Corporation|In-situ formation of multiphase deposited thermal barrier coatings|
    US6709230B2|2002-05-31|2004-03-23|Siemens Westinghouse Power Corporation|Ceramic matrix composite gas turbine vane|
    US6648597B1|2002-05-31|2003-11-18|Siemens Westinghouse Power Corporation|Ceramic matrix composite turbine vane|
    US6929852B2|2002-08-08|2005-08-16|Siemens Westinghouse Power Corporation|Protective overlayer for ceramics|
    EP1532433A2|2002-08-28|2005-05-25|Wayne State University|System forinfrared imaging by inducing acoustic chaos|
    US7291407B2|2002-09-06|2007-11-06|Siemens Power Generation, Inc.|Ceramic material having ceramic matrix composite backing and method of manufacturing|
    US6758653B2|2002-09-09|2004-07-06|Siemens Westinghouse Power Corporation|Ceramic matrix composite component for a gas turbine engine|
    US9068464B2|2002-09-17|2015-06-30|Siemens Energy, Inc.|Method of joining ceramic parts and articles so formed|
    US7093359B2|2002-09-17|2006-08-22|Siemens Westinghouse Power Corporation|Composite structure formed by CMC-on-insulation process|
    US7582359B2|2002-09-23|2009-09-01|Siemens Energy, Inc.|Apparatus and method of monitoring operating parameters of a gas turbine|
    US6838157B2|2002-09-23|2005-01-04|Siemens Westinghouse Power Corporation|Method and apparatus for instrumenting a gas turbine component having a barrier coating|
    US7572524B2|2002-09-23|2009-08-11|Siemens Energy, Inc.|Method of instrumenting a component|
    US8004423B2|2004-06-21|2011-08-23|Siemens Energy, Inc.|Instrumented component for use in an operating environment|
    US20050198967A1|2002-09-23|2005-09-15|Siemens Westinghouse Power Corp.|Smart component for use in an operating environment|
    US7270890B2|2002-09-23|2007-09-18|Siemens Power Generation, Inc.|Wear monitoring system with embedded conductors|
    US7618712B2|2002-09-23|2009-11-17|Siemens Energy, Inc.|Apparatus and method of detecting wear in an abradable coating system|
    EP1422054A1|2002-11-21|2004-05-26|Siemens Aktiengesellschaft|Layered structure for use in gas turbines|
    US6860108B2|2003-01-22|2005-03-01|Mitsubishi Heavy Industries, Ltd.|Gas turbine tail tube seal and gas turbine using the same|
    US6767659B1|2003-02-27|2004-07-27|Siemens Westinghouse Power Corporation|Backside radiative cooled ceramic matrix composite component|
    US7413798B2|2003-04-04|2008-08-19|Siemens Power Generation, Inc.|Thermal barrier coating having nano scale features|
    US7198860B2|2003-04-25|2007-04-03|Siemens Power Generation, Inc.|Ceramic tile insulation for gas turbine component|
    US7311790B2|2003-04-25|2007-12-25|Siemens Power Generation, Inc.|Hybrid structure using ceramic tiles and method of manufacture|
    US6984277B2|2003-07-31|2006-01-10|Siemens Westinghouse Power Corporation|Bond enhancement for thermally insulated ceramic matrix composite materials|
    US7067181B2|2003-08-05|2006-06-27|Siemens Power Generation, Inc.|Insulating ceramic based on partially filled shapes|
    US7108925B2|2003-09-22|2006-09-19|Siemens Power Generation, Inc.|High temperature insulation utilizing zirconia-hafnia|
    DE50306521D1|2003-10-02|2007-03-29|Siemens Ag|Layer system and method for producing a layer system|
    EP1522375A1|2003-10-06|2005-04-13|Siemens Aktiengesellschaft|Method for producing a multilayered system|
    WO2007025842A1|2005-08-30|2007-03-08|Siemens Aktiengesellschaft|The invention relates to a turbine or vane, in particular for use in a combustion turbine|
    EP1528343A1|2003-10-27|2005-05-04|Siemens Aktiengesellschaft|Refractory tile with reinforcing members embedded therein, as liner for gas turbine combustion chamber|
    EP1533113A1|2003-11-14|2005-05-25|Siemens Aktiengesellschaft|High temperature layered system for heat dissipation and method for making it|
    EP1559499A1|2004-01-27|2005-08-03|Siemens Aktiengesellschaft|Method of repairing a turbine component|
    US7351364B2|2004-01-29|2008-04-01|Siemens Power Generation, Inc.|Method of manufacturing a hybrid structure|
    US7509735B2|2004-04-22|2009-03-31|Siemens Energy, Inc.|In-frame repairing system of gas turbine components|
    US7066717B2|2004-04-22|2006-06-27|Siemens Power Generation, Inc.|Ceramic matrix composite airfoil trailing edge arrangement|
    US7334330B2|2004-04-28|2008-02-26|Siemens Power Generation, Inc.|Thermally insulating layer incorporating a distinguishing agent and method for inspecting the same|
    DE102004045934B4|2004-09-22|2008-01-31|Siemens Ag|sensor device|
    JP2006097518A|2004-09-29|2006-04-13|Mitsubishi Heavy Ind Ltd|Connecting structure of combustor transition pipe of gas turbine with gas path|
    EP1645653A1|2004-10-07|2006-04-12|Siemens Aktiengesellschaft|Coating system|
    EP1645652A1|2004-10-07|2006-04-12|Siemens Aktiengesellschaft|Process for the manufacture of a layer system|
    US7237389B2|2004-11-18|2007-07-03|Siemens Power Generation, Inc.|Attachment system for ceramic combustor liner|
    US7247003B2|2004-12-02|2007-07-24|Siemens Power Generation, Inc.|Stacked lamellate assembly|
    US7255535B2|2004-12-02|2007-08-14|Albrecht Harry A|Cooling systems for stacked laminate CMC vane|
    US7153096B2|2004-12-02|2006-12-26|Siemens Power Generation, Inc.|Stacked laminate CMC turbine vane|
    US7402347B2|2004-12-02|2008-07-22|Siemens Power Generation, Inc.|In-situ formed thermal barrier coating for a ceramic component|
    US7198458B2|2004-12-02|2007-04-03|Siemens Power Generation, Inc.|Fail safe cooling system for turbine vanes|
    US7247002B2|2004-12-02|2007-07-24|Siemens Power Generation, Inc.|Lamellate CMC structure with interlock to metallic support structure|
    US7527469B2|2004-12-10|2009-05-05|Siemens Energy, Inc.|Transition-to-turbine seal apparatus and kit for transition/turbine junction of a gas turbine engine|
    US7123031B2|2004-12-20|2006-10-17|Siemens Power Generation, Inc.|System for on-line assessment of the condition of thermal coating on a turbine vane|
    US7435058B2|2005-01-18|2008-10-14|Siemens Power Generation, Inc.|Ceramic matrix composite vane with chordwise stiffener|
    US7258530B2|2005-01-21|2007-08-21|Siemens Power Generation, Inc.|CMC component and method of fabrication|
    US7217088B2|2005-02-02|2007-05-15|Siemens Power Generation, Inc.|Cooling fluid preheating system for an airfoil in a turbine engine|
    US7326030B2|2005-02-02|2008-02-05|Siemens Power Generation, Inc.|Support system for a composite airfoil in a turbine engine|
    US7341428B2|2005-02-02|2008-03-11|Siemens Power Generation, Inc.|Turbine blade for monitoring torsional blade vibration|
    US7387758B2|2005-02-16|2008-06-17|Siemens Power Generation, Inc.|Tabbed ceramic article for improved interlaminar strength|
    ES2305920T3|2005-02-18|2008-11-01|Siemens Aktiengesellschaft|MCRALX ALLOY, MCRALX ALLOY PROTECTIVE COAT, AND PROCEDURE FOR OBTAINING IT.|
    US7176681B2|2005-03-08|2007-02-13|Siemens Power Generation, Inc.|Inspection of composite components using magnetic resonance imaging|
    US7300621B2|2005-03-16|2007-11-27|Siemens Power Generation, Inc.|Method of making a ceramic matrix composite utilizing partially stabilized fibers|
    US7230205B2|2005-03-29|2007-06-12|Siemens Power Generation, Inc.|Compressor airfoil surface wetting and icing detection system|
    EP1707653B1|2005-04-01|2010-06-16|Siemens Aktiengesellschaft|Coating system|
    US7452182B2|2005-04-07|2008-11-18|Siemens Energy, Inc.|Multi-piece turbine vane assembly|
    US7316539B2|2005-04-07|2008-01-08|Siemens Power Generation, Inc.|Vane assembly with metal trailing edge segment|
    US7393183B2|2005-06-17|2008-07-01|Siemens Power Generation, Inc.|Trailing edge attachment for composite airfoil|
    US7494317B2|2005-06-23|2009-02-24|Siemens Energy, Inc.|Ring seal attachment system|
    US7721547B2|2005-06-27|2010-05-25|Siemens Energy, Inc.|Combustion transition duct providing stage 1 tangential turning for turbine engines|
    EP1739356A1|2005-07-01|2007-01-03|Siemens Aktiengesellschaft|Moulding composition for making a refractory lining|
    US7745022B2|2005-07-22|2010-06-29|Siemens Energy, Inc.|CMC with multiple matrix phases separated by diffusion barrier|
    US7550107B2|2005-07-25|2009-06-23|Siemens Energy, Inc.|Method of forming CMC component|
    US7563071B2|2005-08-04|2009-07-21|Siemens Energy, Inc.|Pin-loaded mounting apparatus for a refractory component in a combustion turbine engine|
    US7785076B2|2005-08-30|2010-08-31|Siemens Energy, Inc.|Refractory component with ceramic matrix composite skeleton|
    US7632012B2|2005-09-01|2009-12-15|Siemens Energy, Inc.|Method of measuring in situ differential emissivity and temperature|
    US7278820B2|2005-10-04|2007-10-09|Siemens Power Generation, Inc.|Ring seal system with reduced cooling requirements|
    US20070075455A1|2005-10-04|2007-04-05|Siemens Power Generation, Inc.|Method of sealing a free edge of a composite material|
    JP2007120340A|2005-10-26|2007-05-17|Mitsubishi Heavy Ind Ltd|Combustor tail pipe seal structure of gas turbine|
    AT469110T|2005-11-21|2010-06-15|Siemens Ag|METHOD FOR PRODUCING A BURNED FORM OF A FIRE-RESISTANT CLOTHING|
    US7481621B2|2005-12-22|2009-01-27|Siemens Energy, Inc.|Airfoil with heating source|
    US7371043B2|2006-01-12|2008-05-13|Siemens Power Generation, Inc.|CMC turbine shroud ring segment and fabrication method|
    US7700202B2|2006-02-16|2010-04-20|Alliant Techsystems Inc.|Precursor formulation of a silicon carbide material|
    US7604456B2|2006-04-11|2009-10-20|Siemens Energy, Inc.|Vane shroud through-flow platform cover|
    US7534086B2|2006-05-05|2009-05-19|Siemens Energy, Inc.|Multi-layer ring seal|
    US7762766B2|2006-07-06|2010-07-27|Siemens Energy, Inc.|Cantilevered framework support for turbine vane|
    US20080025838A1|2006-07-25|2008-01-31|Siemens Power Generation, Inc.|Ring seal for a turbine engine|
    US7488157B2|2006-07-27|2009-02-10|Siemens Energy, Inc.|Turbine vane with removable platform inserts|
    US7600978B2|2006-07-27|2009-10-13|Siemens Energy, Inc.|Hollow CMC airfoil with internal stitch|
    US7784264B2|2006-08-03|2010-08-31|Siemens Energy, Inc.|Slidable spring-loaded transition-to-turbine seal apparatus and heat-shielding system, comprising the seal, at transition/turbine junction of a gas turbine engine|
    US7631499B2|2006-08-03|2009-12-15|Siemens Energy, Inc.|Axially staged combustion system for a gas turbine engine|
    EP1903184B1|2006-09-21|2019-05-01|Siemens Energy, Inc.|Combustion turbine subsystem with twisted transition duct|
    US7950234B2|2006-10-13|2011-05-31|Siemens Energy, Inc.|Ceramic matrix composite turbine engine components with unitary stiffening frame|
    US7686577B2|2006-11-02|2010-03-30|Siemens Energy, Inc.|Stacked laminate fiber wrapped segment|
    US20080274336A1|2006-12-01|2008-11-06|Siemens Power Generation, Inc.|High temperature insulation with enhanced abradability|
    US7722317B2|2007-01-25|2010-05-25|Siemens Energy, Inc.|CMC to metal attachment mechanism|
    US7798769B2|2007-02-15|2010-09-21|Siemens Energy, Inc.|Flexible, high-temperature ceramic seal element|
    US7871244B2|2007-02-15|2011-01-18|Siemens Energy, Inc.|Ring seal for a turbine engine|
    US20080199661A1|2007-02-15|2008-08-21|Siemens Power Generation, Inc.|Thermally insulated CMC structure with internal cooling|
    US20080206542A1|2007-02-22|2008-08-28|Siemens Power Generation, Inc.|Ceramic matrix composite abradable via reduction of surface area|
    US20080207075A1|2007-02-22|2008-08-28|Siemens Power Generation, Inc.|Optimized fabric lay-up for improved ceramic matrix composites|
    US7887300B2|2007-02-27|2011-02-15|Siemens Energy, Inc.|CMC airfoil with thin trailing edge|
    US7819625B2|2007-05-07|2010-10-26|Siemens Energy, Inc.|Abradable CMC stacked laminate ring segment for a gas turbine|
    US9297269B2|2007-05-07|2016-03-29|Siemens Energy, Inc.|Patterned reduction of surface area for abradability|
    US7824152B2|2007-05-09|2010-11-02|Siemens Energy, Inc.|Multivane segment mounting arrangement for a gas turbine|
    US7648605B2|2007-05-17|2010-01-19|Siemens Energy, Inc.|Process for applying a thermal barrier coating to a ceramic matrix composite|
    US8061977B2|2007-07-03|2011-11-22|Siemens Energy, Inc.|Ceramic matrix composite attachment apparatus and method|
    US20090014926A1|2007-07-09|2009-01-15|Siemens Power Generation, Inc.|Method of constructing a hollow fiber reinforced structure|
    US7908867B2|2007-09-14|2011-03-22|Siemens Energy, Inc.|Wavy CMC wall hybrid ceramic apparatus|
    US8128350B2|2007-09-21|2012-03-06|Siemens Energy, Inc.|Stacked lamellae ceramic gas turbine ring segment component|
    US8974891B2|2007-10-26|2015-03-10|Coi Ceramics, Inc.|Thermal protection systems comprising flexible regions of inter-bonded lamina of ceramic matrix composite material and methods of forming the same|
    JP2009167905A|2008-01-16|2009-07-30|Mitsubishi Heavy Ind Ltd|Gas turbine combustor outlet seal structure|
    FR2929690B1|2008-04-03|2012-08-17|Snecma Propulsion Solide|COMBUSTION CHAMBER SECTORIZED IN CMC FOR GAS TURBINE|
    FR2929689B1|2008-04-03|2013-04-12|Snecma Propulsion Solide|GAS TURBINE COMBUSTION CHAMBER WITH SECTORIZED INTERNAL AND EXTERNAL WALLS|
    US8162598B2|2008-09-25|2012-04-24|Siemens Energy, Inc.|Gas turbine sealing apparatus|CN104246373B|2011-10-24|2016-06-08|阿尔斯通技术有限公司|Combustion gas turbine|
    FR2989426B1|2012-04-11|2014-03-28|Snecma|TURBOMACHINE, SUCH AS A TURBOJET OR AIRCRAFT TURBOPROPULSER|
    US10633985B2|2012-06-25|2020-04-28|General Electric Company|System having blade segment with curved mounting geometry|
    US10436445B2|2013-03-18|2019-10-08|General Electric Company|Assembly for controlling clearance between a liner and stationary nozzle within a gas turbine|
    US20160131045A1|2014-11-12|2016-05-12|Siemens Energy, Inc.|Emissions control system for a gas turbine engine|
    US10077669B2|2014-11-26|2018-09-18|United Technologies Corporation|Non-metallic engine case inlet compression seal for a gas turbine engine|
    US10030541B2|2015-07-01|2018-07-24|Rolls-Royce North American Technologies Inc.|Turbine shroud with clamped flange attachment|
    US10577951B2|2016-11-30|2020-03-03|Rolls-Royce North American Technologies Inc.|Gas turbine engine with dovetail connection having contoured root|
    US11187105B2|2017-02-09|2021-11-30|General Electric Company|Apparatus with thermal break|
    US10837299B2|2017-03-07|2020-11-17|General Electric Company|System and method for transition piece seal|
    CN107143385B|2017-06-26|2019-02-15|中国科学院工程热物理研究所|A kind of gas turbine guider leading edge installation side structure and the gas turbine with it|
    US10648407B2|2018-09-05|2020-05-12|United Technologies Corporation|CMC boas cooling air flow guide|
    FR3107725A1|2020-02-27|2021-09-03|Safran Aircraft Engines|Assembly for an aircraft turbomachine stator, with reinforced sealing between an outer shell and a bladed stator ring surrounded by this shell|
    US11174754B1|2020-08-26|2021-11-16|Solar Turbines Incorporated|Thermal bridge for connecting sections with a large temperature differential under high-pressure conditions|
    CN112460630A|2020-10-27|2021-03-09|中国船舶重工集团公司第七0三研究所|Sealing assembly between gap planes of high-temperature zone of gas turbine|
    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2018-04-30| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US12/889,860|US8347636B2|2010-09-24|2010-09-24|Turbomachine including a ceramic matrix compositebridge|
    [返回顶部]