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公开(公告)号：US07581397B2
公开(公告)日：2009-09-01
申请号：US11213125
申请日：2005-08-26
CPC分类号： F04D29/441 , F04D29/701 , F05B2260/63
摘要： A diffuser particle separator may be integrated into a gas turbine engine to remove corrosive dust and salt particles from the engine's core air flow. The air flow may pass over a series of particle accumulator entrance orifices, trapping particles in a particle accumulator while allowing the air flow to continue unimpeded. Since dust deposits may become molten at high temperatures, removal of dust from the core and secondary airflow may be critical for long-life superalloy and ceramic components, particularly those with small diameter air-cooling holes and thermal barrier coatings.
摘要翻译： 扩散器颗粒分离器可以集成到燃气涡轮发动机中以从发动机的核心空气流中去除腐蚀性灰尘和盐颗粒。 空气流可以通过一系列颗粒蓄能器入口，将颗粒捕获在颗粒蓄积器中，同时允许气流继续畅通无阻。 由于灰尘沉积物可能在高温下变得熔融，因此从长期使用的超级合金和陶瓷部件，特别是具有小直径空气冷却孔和热障涂层的那些部件中，从芯部和二次气流中除去灰尘可能是至关重要的。
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公开(公告)号：US07717672B2
公开(公告)日：2010-05-18
申请号：US11512559
申请日：2006-08-29
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D9/065 , F04D29/444 , F04D29/624 , F04D29/644 , F05D2250/52 , Y02T50/671
摘要： A radial diffuser comprises a housing, a plurality of diffuser vanes, and a plurality of integral service vanes. The housing includes an air inlet and an air outlet, and defines a radial section extending radially outward from the air inlet, an axial section extending axially to the air outlet, and a transition including a bend and extending between the radial and axial sections. The diffuser vanes are coupled to the housing, and are disposed in, and define diffusion flow passages. The integral service vanes are coupled to the housing, extend around the bend, and define transition flow passages, each in fluid communication with at least one diffusion flow passage. At least some of the integral service vanes include a service passage extending therethrough and configured to allow a service conduit to extend therethrough without crossing either a diffusion flow passage or a transition flow passage.
摘要翻译： 径向扩散器包括壳体，多个扩散器叶片和多个整体服务叶片。 壳体包括空气入口和空气出口，并且限定从空气入口径向向外延伸的径向部分，轴向延伸到空气出口的轴向部分，以及包括弯曲并在径向部分和轴向部分之间延伸的过渡。 扩散器叶片联接到壳体，并且设置在并限定扩散流动通道。 整体服务叶片联接到壳体，围绕弯曲部延伸并且限定过渡流动通道，每个流体通道与至少一个扩散流动通道流体连通。 整体式服务叶片中的至少一些包括延伸穿过其中的服务通道并且构造成允许服务导管在其中延伸穿过而不穿过扩散流动通道或过渡流动通道。
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3.发明申请COMPRESSOR IMPELLERS, COMPRESSOR SECTIONS INCLUDING THE COMPRESSOR IMPELLERS, AND METHODS OF MANUFACTURING 有权压缩机叶轮，压缩机部分，包括压缩机叶轮，以及制造方法公开(公告)号：US20090056125A1
公开(公告)日：2009-03-05
申请号：US11848435
申请日：2007-08-31
申请人： William J. Howe , Harry L. Kington , James Neumann
发明人： William J. Howe , Harry L. Kington , James Neumann
IPC分类号： B21D53/78
CPC分类号： F04D27/0246 , F04D29/023 , F04D29/284 , F04D29/584 , F05D2230/21 , F05D2230/23 , F05D2230/25 , F05D2300/177 , Y10T29/49316
摘要： Compressor impellers, compressor sections, and methods of manufacturing compressor impellers and cooling the compressor impellers are provided. In an embodiment, and by way of example only, a compressor impeller includes a bore section and a rim section. The bore section comprises a first nickel-based alloy and includes an inner disk portion and a first plurality of blade portions extending therefrom. The rim section comprises a second nickel-based alloy and includes an outer disk portion and a second plurality of blade portions. The outer disk portion is bonded to the inner disk portion of the bore section, and the second plurality of blade portions is bonded to the first plurality of blade portions of the bore section
摘要翻译： 提供压缩机叶轮，压缩机部分以及制造压缩机叶轮并冷却压缩机叶轮的方法。 在一个实施例中，仅作为示例，压缩机叶轮包括孔部分和轮缘部分。 孔部分包括第一镍基合金，并且包括内盘部分和从其延伸的第一多个叶片部分。 边缘部分包括第二镍基合金，并且包括外部盘部分和第二多个刀片部分。 外圆盘部分接合到孔部分的内圆盘部分，并且第二多个叶片部分接合到孔部分的第一多个叶片部分
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4.发明授权Compressor impellers, compressor sections including the compressor impellers, and methods of manufacturing 有权压缩机叶轮，包括压缩机叶轮的压缩机部分和制造方法公开(公告)号：US08137075B2
公开(公告)日：2012-03-20
申请号：US11848435
申请日：2007-08-31
申请人： William J. Howe , Harry L. Kington , James Neumann
发明人： William J. Howe , Harry L. Kington , James Neumann
IPC分类号： F03B3/12
CPC分类号： F04D27/0246 , F04D29/023 , F04D29/284 , F04D29/584 , F05D2230/21 , F05D2230/23 , F05D2230/25 , F05D2300/177 , Y10T29/49316
摘要： Compressor impellers, compressor sections, and methods of manufacturing compressor impellers and cooling the compressor impellers are provided. In an embodiment, and by way of example only, a compressor impeller includes a bore section and a rim section. The bore section comprises a first nickel-based alloy and includes an inner disk portion and a first plurality of blade portions extending therefrom. The rim section comprises a second nickel-based alloy and includes an outer disk portion and a second plurality of blade portions. The outer disk portion is bonded to the inner disk portion of the bore section, and the second plurality of blade portions is bonded to the first plurality of blade portions of the bore section.
摘要翻译： 提供压缩机叶轮，压缩机部分以及制造压缩机叶轮并冷却压缩机叶轮的方法。 在一个实施例中，仅作为示例，压缩机叶轮包括孔部分和轮缘部分。 孔部分包括第一镍基合金，并且包括内盘部分和从其延伸的第一多个叶片部分。 边缘部分包括第二镍基合金，并且包括外部盘部分和第二多个刀片部分。 外圆盘部分接合到孔部分的内圆盘部分，并且第二多个叶片部分结合到孔部分的第一多个叶片部分。
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公开(公告)号：US5628193A
公开(公告)日：1997-05-13
申请号：US307961
申请日：1994-09-16
申请人： Harry L. Kington , Craig W. Irwin
发明人： Harry L. Kington , Craig W. Irwin
CPC分类号： F01D9/023
摘要： A transition assembly for directing the gas flow from a combustor to an axial turbine includes a transition liner having a shroud disposed about its outer surface and abutting thereto at a plurality of points to defining a plurality of cooling air passages therebetween. The downstream end of the assembly is circumscribed by the first stage stator and extends axially to just upstream of the first stage turbine rotor. At this end a plurality of circumferentially spaced struts are mounted between the liner and the shroud to define a plurality of axially facing nozzles which are angled to impart a pre-swirl to the cooling air exiting therefrom.
摘要翻译： 用于将气流从燃烧器引导到轴向涡轮机的过渡组件包括过渡衬套，其具有围绕其外表面设置的护罩，并且在多个点处与其邻接以在其间限定多个冷却空气通道。 组件的下游端由第一级定子外接，并且轴向延伸到刚好在第一级涡轮转子的上游。 在该端部处，多个周向间隔开的支柱安装在衬套和护罩之间以限定多个轴向面对的喷嘴，该喷嘴成角度以对从其离开的冷却空气进行预旋转。
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公开(公告)号：US5183270A
公开(公告)日：1993-02-02
申请号：US760419
申请日：1991-09-16
IPC分类号： F16J15/34
CPC分类号： F16J15/3452
摘要： A composite seal rotor is provided for sealing between the rotating components of a gas turbine engine held together by the compressive force of a lockup assembly and a housing circumscribing the rotating components and having carbon face seals mounted thereto. The seal rotor is comprised of a metal base portion disposed between two of said rotating components for transmitting said compressive force therethrough, and a ceramic surface for sealingly engaging said carbon face seal.
摘要翻译： 提供了一种复合密封转子，用于通过锁定组件的压缩力和外壳旋转部件并具有安装在其上的碳表面密封件的壳体来密封保持在一起的燃气涡轮发动机的旋转部件之间。 密封转子包括设置在两个用于传递所述压缩力的旋转部件之间的金属基部，以及用于密封地接合所述碳面密封件的陶瓷表面。
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公开(公告)号：US5061154A
公开(公告)日：1991-10-29
申请号：US448776
申请日：1989-12-11
申请人： Harry L. Kington
发明人： Harry L. Kington
CPC分类号： F01D5/048 , F01D5/28 , F05D2220/50 , Y02T50/672 , Y02T50/673 , Y10T29/49316
摘要： A radial inflow rotor for a gas turbine engine has a dual structure for improving the low cycle fatigue life of the saddle region. The interior core or hub of the rotor is a high strength polycrystalline alloy while a series of outer blade segments is individually cast as single crystals and bonded so that their low modulus (100) crystallographic axis is aligned substantially tangential to the rotor's circumference at the saddle.
摘要翻译： 用于燃气涡轮发动机的径向流入转子具有用于改善鞍形区域的低循环疲劳寿命的双重结构。 转子的内芯或轮毂是高强度多晶合金，而一系列外刀片段单独铸造为单晶并结合，使得它们的低模量（100）结晶轴基本上与转子在鞍座处的圆周相切地对齐 。
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公开(公告)号：US5664413A
公开(公告)日：1997-09-09
申请号：US412641
申请日：1995-03-29
摘要： A gas turbine engine having a compressor rotor and turbine rotor in back-to-back relation and annular groove therebetween. A nonrotating seal is disposed in the groove. A dual pilot ring is disposed at the radial inner end of the groove. The dual pilot ring includes an inner annular ring and an outer annular ring radially spaced apart to define a clearance gap. The inner ring is mounted to radially facing piloting surfaces on both the compressor and turbine rotors and maintains concentricity between the two rotors as they grow at different thermal rates. The outer annular ring transfers axial loads between the rotors.
摘要翻译： 一种具有压缩机转子和背对背关系的涡轮转子和其间的环形槽的燃气涡轮发动机。 非旋转密封件设置在凹槽中。 双引导环设置在凹槽的径向内端。 双引导环包括内环形环和径向间隔开的外环形环，以限定间隙。 内圈安装在压缩机和涡轮转子上的径向面向的引导表面上，并且当它们以不同的热速率生长时，保持两个转子之间的同心度。 外环形圈转动转子之间的轴向载荷。
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公开(公告)号：US5290143A
公开(公告)日：1994-03-01
申请号：US970198
申请日：1992-11-02
CPC分类号： F01D9/044 , Y10S415/915
摘要： A bicast vane and shroud rings is provided in which thermal stresses are minimized. The vane has a flange portion along its inner and outer edge. These flange portions extend from the mid-chord of the vane part way towards the leading and trailing edges and follow the camber of the vane. Each of the flange portions has a width greater than that of the vane so has to form an overhang or lip about which conventional shroud rings are cast. As the flange portions approach the leading and trailing edges their width decreases and the overhang blends into the inner and outer edge to form rounded tops and bottoms at the leading and trailing edge. These rounded tops and bottoms reduce stress concentrations in the shroud rings and increase shroud material near these edges. Additionally, a stress relieving member is provided that embraces the top and bottom edges of the thin trailing edge, and inhibits the melting of the trailing edge during bicasting.
摘要翻译： 提供了一种双向叶片和护罩环，其中热应力最小化。 叶片沿其内边缘和外边缘具有凸缘部分。 这些凸缘部分从叶片的中间部分方向延伸到前缘和后缘并跟随叶片的弯度。 每个凸缘部分的宽度大于叶片的宽度，因此必须形成一个伸出或者唇缘，围绕这些突出部分或唇缘铸造常规的护罩环。 当凸缘部分接近前缘和后缘时，它们的宽度减小，并且突出部分共混到内边缘和外边缘中，以在前缘和后缘形成圆顶和底部。 这些圆形顶部和底部减少了护罩环中的应力集中，并增加了这些边缘附近的护罩材料。 另外，提供了一种应力消除构件，其包围薄后缘的顶部和底部边缘，并且在双打时抑制后缘的熔化。
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公开(公告)号：US20100078259A1
公开(公告)日：2010-04-01
申请号：US12242138
申请日：2008-09-30
CPC分类号： B29C70/088 , B29C53/562 , B29C65/4835 , B29C65/5042 , B29C65/5092 , B29C65/56 , B29C65/562 , B29C65/601 , B29C66/1122 , B29C66/1142 , B29C66/1222 , B29C66/1226 , B29C66/43 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/723 , B29C66/72321 , B29C66/7254 , B29C66/73161 , B29C66/83411 , B29D23/001 , B29K2305/00 , B29L2009/003 , B29L2023/00 , B29L2023/22 , B32B1/00 , B32B1/08 , B32B3/08 , B32B3/12 , B32B3/266 , B32B3/30 , B32B5/022 , B32B5/024 , B32B5/18 , B32B5/24 , B32B5/245 , B32B7/02 , B32B7/08 , B32B7/12 , B32B15/046 , B32B15/14 , B32B15/18 , B32B15/20 , B32B27/06 , B32B27/40 , B32B37/00 , B32B37/12 , B32B2250/42 , B32B2260/021 , B32B2260/046 , B32B2262/0269 , B32B2262/10 , B32B2262/101 , B32B2262/106 , B32B2307/102 , B32B2307/306 , B32B2307/554 , B32B2307/712 , B32B2439/00 , B32B2597/00 , B32B2605/00 , B32B2605/18 , F16L9/147 , F16L9/165 , B29K2307/04 , B29K2309/08 , B29K2063/00 , B29K2309/14
摘要： Methods of forming flowbodies and flowbodies are provided. In an embodiment, by way of example only, a method includes providing a first sheet of a first material comprising a metal, providing a second sheet of a second material comprising a composite, attaching a portion of the first sheet to a first position on a preform, securing a portion of the second sheet to a second position on the preform, and winding the first sheet and the second sheet around the preform to form the first flowbody, the first flowbody including a laminate comprising alternating layers of the first sheet and the second sheet.
摘要翻译： 提供了形成流动体和流动体的方法。 在一个实施例中，仅作为示例，一种方法包括提供包括金属的第一材料的第一片材，提供包括复合材料的第二材料的第二片材，将第一片材的一部分附着到第一片材上 将所述第二片材的一部分固定到所述预制件上的第二位置，以及将所述第一片材和所述第二片材缠绕在所述预成型件周围以形成所述第一流动体，所述第一流动体包括层压体，所述层压体包括所述第一片材和 第二张。
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