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1. 发明授权

US09765623B2 Methods for modifying cooling holes with recess-shaped modifications 有权
公开(公告)号：US09765623B2
公开(公告)日：2017-09-19
申请号：US13948240
申请日：2013-07-23
申请人： General Electric Company
发明人： Srikanth Chandrudu Kottilingam , Yan Cui , Brian Lee Tollison , David Edward Schick , Jonathan Matthew Lomas , Gareth William David Lewis
IPC分类号： F01D5/00 , B23P6/00 , F01D5/18
CPC分类号： F01D5/005 , B23P6/005 , B23P2700/06 , F01D5/182 , F01D5/186 , F01D5/187 , F01D5/20 , F05D2230/22 , F05D2230/236 , F05D2230/80 , F05D2240/307 , Y02T50/671 , Y02T50/676 , Y10T29/49318 , Y10T29/49737 , Y10T29/49902
摘要： A Method for modifying a plurality of cooling holes of a turbine component includes disposing a recess-shaped modification in a recess of the component comprising a plurality of cooling hole outlets, wherein the recess-shaped modification is formed to substantially fill the recess and comprising a plurality of modified cooling holes passing there through. The method further includes aligning the plurality of modified cooling holes of the recess-shaped modification with the plurality of cooling hole outlets of the component, inserting at least one alignment pin into at least one of aligned pair of holes and hole outlets, bonding the recess-shaped modification disposed in the recess to the component, and removing the at least one alignment pin after bonding, wherein the plurality of modified cooling holes of the recess-shaped modification is fluidly connected with the plurality of cooling holes of the component.

2. 发明申请

US20160053618A1 COMPONENTS WITH COOLING CHANNELS AND METHODS OF MANUFACTURE 审中-公开
标题翻译：具有冷却通道的组件和制造方法
公开(公告)号：US20160053618A1
公开(公告)日：2016-02-25
申请号：US14929273
申请日：2015-10-31
申请人： General Electric Company
发明人： Ronald Scott Bunker , Scott Andrew Weaver , Don Mark Lipkin , John Brian McDermott
IPC分类号： F01D5/18 , F01D9/04 , F01D25/12 , F01D5/22 , F01D25/28 , F01D5/28 , F01D25/30
CPC分类号： F01D5/187 , B23P15/04 , B23P2700/13 , F01D5/182 , F01D5/186 , F01D5/225 , F01D5/288 , F01D9/041 , F01D25/12 , F01D25/28 , F01D25/30 , F05D2220/32 , F05D2230/90 , F05D2260/202 , F05D2260/203 , F05D2260/204 , F05D2300/611 , Y10T29/4932 , Y10T29/49341 , Y10T29/49982 , Y10T428/13 , Y10T428/24314 , Y10T428/24322 , Y10T428/24521 , Y10T428/24562 , Y10T428/24612 , Y10T428/24636
摘要： A manufacturing method includes forming one or more grooves in a component that comprises a substrate with an outer surface. The substrate has at least one interior space. Each groove extends at least partially along the substrate and has a base and a top. The manufacturing method further includes applying a structural coating on at least a portion of the substrate and processing at least a portion of the surface of the structural coating so as to plastically deform the structural coating at least in the vicinity of the top of a respective groove, such that a gap across the top of the groove is reduced. A component is also disclosed and includes a structural coating disposed on at least a portion of a substrate, where the surface of the structural coating is faceted in the vicinity of the respective groove.
摘要翻译：一种制造方法包括在包括具有外表面的基板的部件中形成一个或多个凹槽。衬底具有至少一个内部空间。每个凹槽至少部分地沿着基底延伸并且具有基部和顶部。该制造方法还包括在至少一部分基底上施加结构涂层并且处理结构涂层的表面的至少一部分，以至少在相应凹槽的顶部附近使结构涂层塑性变形使得横跨槽的顶部的间隙减小。还公开了一种组件，并且包括设置在基底的至少一部分上的结构涂层，其中结构涂层的表面在相应凹槽附近被刻面。

3. 发明授权

US07665956B2 Wall cooling arrangement 有权
标题翻译：墙体冷却装置
公开(公告)号：US07665956B2
公开(公告)日：2010-02-23
申请号：US11580893
申请日：2006-10-16
申请人： Mark T Mitchell , Peter Ireland , Vikram Mittal
发明人： Mark T Mitchell , Peter Ireland , Vikram Mittal
IPC分类号： F01D5/14
CPC分类号： F01D5/182 , B33Y80/00 , F01D5/186 , F05D2250/21 , F05D2260/203 , F23R2900/03041 , F23R2900/03042 , F28F2210/02
摘要： A wall cooling arrangement comprising on one side of a wall a multiplicity of cooling fluid inlet apertures and on the opposite of the wall a multiplicity of cooling fluid exit apertures, and in the body of the wall linking said inlet and exit apertures a network of multiply branched cooling passages. Flow of cooling fluid through a network is controlled by a throat positioned either at or close to the inlet to the passage network or at a location part way through the network, in which case there may be a plurality of inlet apertures feeding through a single throat to a plurality of outlet apertures.
摘要翻译：壁冷却装置包括在壁的一侧上具有多个冷却流体入口孔，并且在壁的相对侧上包括多个冷却流体出口孔，并且在连接所述入口孔和出口孔的壁的主体中，分支冷却通道。通过网络的冷却流体的流动由位于通道网络的入口处或靠近通道网络的入口的喉部或通过网络的部分位置的喉部控制，在这种情况下，可以有多个入口孔通过单个喉部到多个出口孔。

4. 发明授权

US06551061B2 Process for forming micro cooling channels inside a thermal barrier coating system without masking material 失效
公开(公告)号：US06551061B2
公开(公告)日：2003-04-22
申请号：US09818311
申请日：2001-03-27
申请人： Ramgopal Darolia , Ching-Pang Lee , Robert Edward Schafrik
发明人： Ramgopal Darolia , Ching-Pang Lee , Robert Edward Schafrik
IPC分类号： F01D518
CPC分类号： F01D5/288 , F01D5/182 , F01D5/187 , F05D2230/12 , Y02T50/67 , Y02T50/676 , Y10T29/49316
摘要： The present invention provides a process for forming active convection cooling micro channels within or adjacent to a bond coat layer applied to a turbine high pressure turbine airfoil. When placed adjacent or within a porous TBC, the micro channels additionally provide transpiration cooling through the porous TBC. The micro channels communicate directly with at least one cooling circuit contained within the airfoil from which they receive cooling air, thereby providing direct and efficient cooling for the bond coat layer. Because the substrate includes an actively cooled flow path surface region that can reduce the cooling requirement for the substrate, the engine can run at a higher firing temperature without the need for additional cooling air, achieving a better, more efficient engine performance. In one embodiment, a metallic bond coat is applied to an airfoil. The bond coat is grooved such that the grooves are structured, with at least one structured micro groove communicating with at least one cooling fluid supply contained within the airfoil. A TBC layer is applied over the structured grooves, resulting in the formation of hollow micro channels for the transport of the cooling fluid due to self-shadowing. In different embodiments, the location of the structured grooves, hence, the resulting micro channels are placed within the airfoil substrate at the substrate/bond coat interface or within the TBC layer.

5. 发明授权

US06499950B2 Cooling circuit for a gas turbine bucket and tip shroud 有权
标题翻译：燃气轮机铲斗和喷嘴罩的冷却回路
公开(公告)号：US06499950B2
公开(公告)日：2002-12-31
申请号：US09852673
申请日：2001-05-11
申请人： Fred Thomas Willett , Gary Michael Itzel , Dimitrios Stathopoulos , Larry Wayne Plemmons , Doyle C. Lewis
发明人： Fred Thomas Willett , Gary Michael Itzel , Dimitrios Stathopoulos , Larry Wayne Plemmons , Doyle C. Lewis
IPC分类号： F01D518
CPC分类号： F01D5/225 , F01D5/182 , F01D25/12
摘要： An open cooling circuit for a gas turbine bucket wherein the bucket has an airfoil portion, and a tip shroud, the cooling circuit including a plurality of radial cooling holes extending through the airfoil portion and communicating with an enlarged internal area within the tip shroud before exiting the tip shroud such that a cooling medium used to cool the airfoil portion is subsequently used to cool the tip shroud.
摘要翻译：一种用于燃气轮机桶的敞开冷却回路，其中所述铲斗具有翼型部分和尖端护罩，所述冷却回路包括多个径向冷却孔，所述多个径向冷却孔延伸穿过所述翼型部分并且在出口之前与所述末端护罩内的扩大的内部区域连通尖端护罩使得用于冷却翼型件部分的冷却介质随后用于冷却尖端护罩。

6. 发明授权

US06375425B1 Transpiration cooling in thermal barrier coating 失效
标题翻译：隔热涂层中的蒸腾冷却
公开(公告)号：US06375425B1
公开(公告)日：2002-04-23
申请号：US09707027
申请日：2000-11-06
申请人： Ching-Pang Lee , Robert Edward Schafrik , Ramgopal Darolia
发明人： Ching-Pang Lee , Robert Edward Schafrik , Ramgopal Darolia
IPC分类号： F04D2958
CPC分类号： F01D5/288 , C23C28/00 , F01D5/182 , Y02T50/67 , Y02T50/676 , Y10T29/49341
摘要： A method for transpiration cooling of the flow path surface region of an engine component used in a gas turbine engine by channeling a substrate to provide cooling channels through the substrate having a diameter of about 0.005″ to about 0.02″ to allow passage of cooling fluid from a cooling fluid source through the cooling channels. A bond coat of about 0.0005″ to about 0.005″ in thickness is applied to the substrate such that the bond coat partially fills the cooling channels. A porous TBC of at least about 0.003″ to about 0.01″ thick is applied over the bond coat, such that the TBC completely fills the cooling channels. Cooling fluid from a cooling fluid source is passed through the cooling channels and porous TBC. Because the channel exit is filled with TBC, the cooling fluid is transmitted through the porous passageways of the TBC. The porous passageways provide a plurality of tortuous routes to the TBC surface. The present invention further comprises both the cooled flow path surface region formed by the foregoing methods and the turbine component having a porous TBC cooling system connected to a cooling fluid source for cooling the component.
摘要翻译：一种用于蒸汽冷却燃气涡轮发动机中使用的发动机部件的流路表面区域的方法，其通过引导基板以提供通过直径为大约0.005“至大约0.02”的基板的冷却通道，以允许冷却冷却流体源通过冷却通道的流体。将厚度为约0.0005“至约0.005”的粘合涂层施加到基底上，使得粘结涂层部分地填充冷却通道。至少约0.003“至约0.01”厚的多孔TBC施加在粘合涂层上，使得TBC完全填充冷却通道。来自冷却流体源的冷却流体通过冷却通道和多孔TBC。由于通道出口填充有TBC，冷却液通过TBC的多孔通道传播。多孔通道为TBC表面提供了多条曲折的路线。本发明还包括通过上述方法形成的冷却流路表面区域和具有连接到用于冷却部件的冷却流体源的多孔TBC冷却系统的涡轮机部件。

7. 发明申请

US20020028133A1 Vane assembly 有权
标题翻译：叶片装配
公开(公告)号：US20020028133A1
公开(公告)日：2002-03-07
申请号：US09925502
申请日：2001-08-10
发明人： Rez Manzoori , Michael J. L. Percival , Graham M. Upton
IPC分类号： F01D009/06
CPC分类号： F01D5/186 , F01D5/182
摘要： A vane assembly 40 for use within a gas turbine engine has a main vane portion 42 with an internal cavity 44. A cavity insert 46 is located within the cavity 44, close to the wall 48 to define transpiration cooling paths. Cooling air leaves the insert 46 through apertures directed at the wall 48, to produce impingement cooling. The transpiration cooling paths are extended back to the trailing edge 66 by means of a fairing 54. The use of a fairing in addition to the insert allows more complicated cavity shapes to be filled.
摘要翻译：在燃气涡轮发动机内使用的叶片组件40具有带有内腔44的主叶片部分42.腔体插入件46位于空腔44内，靠近壁48以限定蒸发冷却路径。冷却空气通过指向壁48的孔离开插入件46，以产生冲击冷却。蒸腾冷却路径通过整流罩54延伸回到后缘66.除了插入件之外使用整流罩允许填充更复杂的空腔形状。

8. 发明授权

US4653983A Cross-flow film cooling passages 失效
标题翻译：横流膜冷却通道
公开(公告)号：US4653983A
公开(公告)日：1987-03-31
申请号：US812099
申请日：1985-12-23
申请人： James W. Vehr
发明人： James W. Vehr
IPC分类号： B23H9/10 , F01D5/18
CPC分类号： B23H9/10 , F01D5/182 , F01D5/186 , Y02T50/676
摘要： Film coolant passages through the wall of a hollow airfoil for a gas turbine engine are oriented to direct coolant fluid therefrom at a substantial acute angle to the downstream direction and at a shallow angle to the surface of the airfoil. Each passage includes a metering portion at its inlet end and a four sided diffusing portion at its outlet end. The diffusing portion includes a pair of adjoining surfaces which are both parallel to a central axis of the passage, and another pair of adjoining surfaces which diverge from the central axis, the diverging pair of surfaces being located on the downstream side of the passage. With this configuration the coolant completely fills the diffusing section and exits as a wide film of coolant within the boundary layer downstream of the passage outlet.
摘要翻译：通过用于燃气涡轮发动机的中空翼型件的壁的薄膜冷却剂通道被定向成将冷却剂流体以与下游方向成大体锐角并以与叶片表面成浅角度的方式引导。每个通道在其入口端处包括计量部分和在其出口端处的四边扩散部分。漫射部分包括一对平行于通道的中心轴线的邻接表面以及从中心轴线分叉的另一对相邻表面，发散对表面位于通道的下游侧。利用这种结构，冷却剂完全填满扩散部分，并在通道出口下游的边界层内以宽的冷却剂膜的形式离开。

9. 发明授权

US4314794A Transpiration cooled blade for a gas turbine engine 失效
标题翻译：用于燃气涡轮发动机的蒸腾冷却叶片
公开(公告)号：US4314794A
公开(公告)日：1982-02-09
申请号：US88245
申请日：1979-10-25
申请人： Abe N. Holden, deceased , by Joyce A. Holden, executrix
发明人： Abe N. Holden, deceased , by Joyce A. Holden, executrix
IPC分类号： F01D5/18
CPC分类号： F01D5/182
摘要： A transpiration cooled blade for a gas turbine engine is assembled from a plurality of individual airfoil-shaped hollow ceramic washers stacked upon a ceramic platform which in turn is seated on a metal root portion. The airfoil portion so formed is enclosed by a metal cap covering the outermost washer. A metal tie tube is welded to the cap and extends radially inwardly through the hollow airfoil portion and through aligned apertures in the platform and root portion to terminate in a threaded end disposed in a cavity within the root portion housing a tension nut for engagement thereby. The tie tube is hollow and provides flow communication for a coolant fluid directed through the root portion and into the hollow airfoil through apertures in the tube. The ceramic washers are made porous to the coolant fluid to cool the blade via transpiration cooling.
摘要翻译：用于燃气涡轮发动机的蒸发冷却叶片由堆叠在陶瓷平台上的多个单独的翼型中空陶瓷垫圈组装，陶瓷平台又位于金属根部上。如此形成的翼型部由覆盖最外侧垫圈的金属盖封闭。金属连接管被焊接到盖并且径向向内延伸穿过中空翼型部分并且通过平台和根部中的对准的孔并终止于设置在根部内的空腔中的螺纹端，该螺纹端容纳用于接合的拉紧螺母。连接管是中空的，并且提供通过根部分引导的冷却剂流体和通过管中的孔的中空翼型件的流动连通。陶瓷垫圈对冷却剂流体制成多孔，以通过蒸发冷却来冷却刀片。

10. 发明授权

US4118146A Coolable wall 失效
标题翻译：可冷却墙
公开(公告)号：US4118146A
公开(公告)日：1978-10-03
申请号：US713739
申请日：1976-08-11
申请人： James Albert Dierberger
发明人： James Albert Dierberger
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F01D5/182 , F05D2260/201 , F05D2260/203 , Y02T50/673 , Y02T50/676
摘要： A coolable wall element which is adapted for combined impingement and transpiration cooling in environments where the pressure differential across the wall element differs substantially with physical position along the wall is disclosed. Techniques varying the proportion of impingement to transpiration cooling along the wall are developed. The wall element is shown in one embodiment as forming a portion of the wall of an air-foil adapted for use in the turbine section of a gas turbine engine.
摘要翻译：公开了一种可冷却的壁元件，其适用于在跨过壁元件的压差基本上与沿着壁的物理位置大不相同的环境中的组合冲击和蒸发冷却。开发了将冲击比例沿着墙壁蒸发冷却的技术。在一个实施例中，壁元件被示出为形成适于在燃气涡轮发动机的涡轮部分中使用的空气箔的壁的一部分。

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