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公开(公告)号：US20140230400A1
公开(公告)日：2014-08-21
申请号：US13767928
申请日：2013-02-15
IPC分类号： F02C7/00
CPC分类号： F02C7/08 , F01D5/08 , F01D11/24 , F01D25/10 , F05D2260/20 , F05D2260/85
摘要： A gas turbine engine including a compressor section, a combustor section, and a turbine section operating to produce a power output during a first mode of operation. A heat retention and distribution system is provided to the engine wherein the heat retention system operates in a second mode of operation, following a shutdown of the engine, to maintain an elevated temperature in components of each of the compressor section, the combustor section and the turbine section in order to effect (1) a reduction in an effective cyclic life consumption of the components and extend a maintenance interval associated with the effective cyclic life consumption, and (2) clearances by maintaining a higher vane carrier temperature with time during a non-power producing mode and more uniform temperature of most stationary components in the circumferential orientation.
摘要翻译： 一种燃气涡轮发动机，包括压缩机部分，燃烧器部分和在第一操作模式期间产生功率输出的涡轮部分。 发动机提供保温分配系统，其中在发动机关闭之后，保温系统在第二操作模式下操作，以在压缩机部分，燃烧器部分和 涡轮机部分，以实现（1）减少部件的有效循环寿命消耗并延长与有效循环寿命消耗相关联的维护间隔，以及（2）通过在非涡轮机非零时保持较高的叶片载体温度随时间而增加间隙 大多数固定部件在圆周方向上的功率生产模式和更均匀的温度。
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公开(公告)号：US20120034081A1
公开(公告)日：2012-02-09
申请号：US12852720
申请日：2010-08-09
CPC分类号： F01D5/147 , F01D5/3007 , F02C7/04 , F04D29/324 , F04D29/34 , F04D29/584 , F05D2260/20 , F05D2270/114
摘要： A compressor blade root heating system for a turbine engine is disclosed. The compressor blade root heating system may be formed from one or more induction heaters formed from one or more induction coils positioned in close proximity to a root of a compressor blade. In one embodiment, the induction heater may be coupled to a static casing component positioned immediately upstream of a first row of compressor blades on a rotor assembly such that the induction heater is stationary during turbine engine operation. The induction heater causes eddy current formation, which heats the row one compressor blades. This heating increases the fracture toughness of the material forming the rotor and compressor blades, thereby increasing the mechanical life cycle.
摘要翻译： 公开了一种用于涡轮发动机的压缩机叶片根加热系统。 压缩机叶片根部加热系统可以由一个或多个感应加热器形成，该感应加热器由位于压缩机叶片的根部附近的一个或多个感应线圈形成。 在一个实施例中，感应加热器可以耦合到位于转子组件上的第一排压缩机叶片的紧邻上游的静态壳体部件，使得感应加热器在涡轮发动机运转期间是静止的。 感应加热器引起涡流形成，这加热了一排压缩机叶片。 这种加热增加了形成转子和压缩机叶片的材料的断裂韧性，从而增加了机械寿命周期。
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公开(公告)号：US08573932B2
公开(公告)日：2013-11-05
申请号：US12852720
申请日：2010-08-09
IPC分类号： F01D25/10
CPC分类号： F01D5/147 , F01D5/3007 , F02C7/04 , F04D29/324 , F04D29/34 , F04D29/584 , F05D2260/20 , F05D2270/114
摘要： The compressor blade root heating system may be formed from one or more induction heaters formed from one or more induction coils positioned in close proximity to a root of a compressor blade. In one embodiment, the induction heater may be coupled to a static casing component positioned immediately upstream of a first row of compressor blades on a rotor assembly such that the induction heater is stationary during turbine engine operation. The induction heater causes eddy current formation, which heats the row one compressor blades. This heating increases the fracture toughness of the material forming the rotor and compressor blades, thereby increasing the mechanical life cycle.
摘要翻译： 压缩机叶片根部加热系统可以由一个或多个感应加热器形成，该感应加热器由位于压缩机叶片的根部附近的一个或多个感应线圈形成。 在一个实施例中，感应加热器可以耦合到位于转子组件上的第一排压缩机叶片的紧邻上游的静态壳体部件，使得感应加热器在涡轮发动机运转期间是静止的。 感应加热器引起涡流形成，这加热了一排压缩机叶片。 这种加热增加了形成转子和压缩机叶片的材料的断裂韧性，从而增加了机械寿命周期。
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4.发明授权Method and apparatus to tune rotor's torsional natural frequency by geometry of rotor winding slot 失效通过转子绕组槽的几何形状来调节转子扭转固有频率的方法和装置公开(公告)号：US06833640B2
公开(公告)日：2004-12-21
申请号：US09731501
申请日：2000-12-07
IPC分类号： H02K704
CPC分类号： H02K1/26
摘要： A method and apparatus for tuning the torsional natural frequency of a rotor is disclosed. At least one tuning slot is formed within the winding slots defined by radially projecting winding teeth. The tuning slot extends radially inward from the bottom of the winding slot a distance to tune the rotor to a desired torsional natural frequency. This tuning slot can be positioned preferably at the quadrature axis.
摘要翻译： 公开了一种用于调谐转子的扭转固有频率的方法和装置。 在由径向突出的绕线齿限定的绕组槽内形成至少一个调音槽。 调音槽从卷绕槽的底部径向向内延伸一定距离，以将转子调谐到所需的扭转固有频率。 该调谐槽优选地位于正交轴上。
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5.发明申请MID-SECTION OF A CAN-ANNULAR GAS TURBINE ENGINE WITH AN IMPROVED ROTATION OF AIR FLOW FROM THE COMPRESSOR TO THE TURBINE 有权CAN-ANNULAR气体涡轮发动机的中间部分，从压缩机到涡轮机的空气流改进公开(公告)号：US20130219853A1
公开(公告)日：2013-08-29
申请号：US13408287
申请日：2012-02-29
IPC分类号： F02G1/00
摘要： A midframe portion (313) of a gas turbine engine (310) is presented and includes a compressor section with a last stage blade to orient an air flow (311) at a first angle (372). The midframe portion (313) further includes a turbine section with a first stage blade to receive the air flow (311) oriented at a second angle (374). The midframe portion (313) further includes a manifold (314) to directly couple the air flow (311) from the compressor section to a combustor head (318) upstream of the turbine section. The combustor head (318) introduces an offset angle in the air flow (311) from the first angle (372) to the second angle (374) to discharge the air flow (311) from the combustor head (318) at the second angle (374). While introducing the offset angle, the combustor head (318) at least maintains or augments the first angle (372).
摘要翻译： 呈现燃气涡轮发动机（310）的中架部分（313）并且包括具有最后级叶片的压缩机部分，以使空气流（311）以第一角度（372）定向。 中间部分（313）还包括具有第一级叶片的涡轮机部分，以接收以第二角度（374）定向的空气流（311）。 中间部分（313）还包括歧管（314），用于将空气流（311）从压缩机部分直接耦合到涡轮部分上游的燃烧器头部（318）。 燃烧器头部（318）将空气流（311）中的偏移角从第一角度（372）引入第二角度（374），以使空气流（311）以第二角度从燃烧器头部（318）排出 （374）。 在引入偏移角的同时，燃烧器头（318）至少保持或增加第一角度（372）。
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公开(公告)号：US07165889B2
公开(公告)日：2007-01-23
申请号：US11044792
申请日：2005-01-27
IPC分类号： F16C17/02
CPC分类号： F16C32/0659 , F16C17/02 , F16C32/0685 , F16C39/04 , F16C2300/14 , F16C2360/00
摘要： An oil lift pocket for a bearing surface having a plurality of channels in communication with a supply port. The plurality of channels may be formed in a substantially bow shaped configuration. Each channel may extend from a supply port and terminate at an end and away from the supply port. The oil lift pocket greatly reduces friction in slow turning operations and reduces babbitt delamination, dead zones, and nonuniform support and lift as well.
摘要翻译： 一种用于支承表面的提油口，其具有与供给口连通的多个通道。 多个通道可以形成为大致弓形的构型。 每个通道可以从供应端口延伸并终止并且远离供应端口。 提油口袋大大降低了慢转动作业中的摩擦力，并减少了巴氏合金分层，死区和不均匀的支撑和提升。
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7.发明授权Shrunk on industrial coupling without keys for industrial system and associated methods 有权用于工业联接的工业系统和相关方法的密钥公开(公告)号：US06688802B2
公开(公告)日：2004-02-10
申请号：US09950497
申请日：2001-09-10
IPC分类号： F16B2114
CPC分类号： F16D1/076 , F16B2200/506
摘要： An industrial coupling (30) and associated methods are provided which are adapted to be positioned to connect a first shaft (21) of a portion (12) of an industrial system (10) to a second shaft (23) of a portion (11) of an industrial system (10) so that an industrial member (25) having an opening formed therein and having a preselected opening diameter can be readily positioned over the coupling (30). The industrial coupling (30) preferably has a first coupler portion (31) mounted to and integrally formed with the first shaft (21) and having a first diameter less than the preselected opening diameter of the industrial member (25) so that the industrial member (25) can readily be positioned over the first coupler portion (31) and onto the first shaft (21). The industrial coupler (30) preferably also has a second coupler portion (36) adapted to be mounted on the first coupler portion (31) and having a second diameter greater than the preselected opening diameter of the industrial member (25) when mounted on the first coupler portion (31) so that the industrial member (25) after being positioned onto the first shaft (21) cannot be readily positioned over the coupling (30).
摘要翻译： 提供了一种工业联接器（30）和相关联的方法，其适于定位成将工业系统（10）的部分（12）的第一轴（21）连接到部分（11）的第二轴（23） ），使得具有形成在其中并且具有预选开口直径的开口的工业构件（25）可以容易地定位在联接器（30）上方。 工业联接器（30）优选地具有安装到第一轴（21）并且与第一轴（21）一体形成并且具有小于工业构件（25）的预选开口直径的第一直径的第一联接器部分（31），使得工业构件 （25）可以容易地定位在第一联接器部分（31）上并且位于第一轴（21）上。 工业耦合器（30）优选地还具有适于安装在第一耦合器部分（31）上并具有大于工件（25）的预选开口直径的第二直径的第二耦合器部分（36） 第一联接器部分（31），使得在定位到第一轴（21）上之后的工业构件（25）不能容易地定位在联接器（30）上方。
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8.发明授权Mid-section of a can-annular gas turbine engine with an improved rotation of air flow from the compressor to the turbine 有权具有改进的从压缩机到涡轮机的空气流的旋转的罐环式燃气涡轮发动机的中部公开(公告)号：US09291063B2
公开(公告)日：2016-03-22
申请号：US13408287
申请日：2012-02-29
摘要： A midframe portion (313) of a gas turbine engine (310) is presented and includes a compressor section with a last stage blade to orient an air flow (311) at a first angle (372). The midframe portion (313) further includes a turbine section with a first stage blade to receive the air flow (311) oriented at a second angle (374). The midframe portion (313) further includes a manifold (314) to directly couple the air flow (311) from the compressor section to a combustor head (318) upstream of the turbine section. The combustor head (318) introduces an offset angle in the air flow (311) from the first angle (372) to the second angle (374) to discharge the air flow (311) from the combustor head (318) at the second angle (374). While introducing the offset angle, the combustor head (318) at least maintains or augments the first angle (372).
摘要翻译： 呈现燃气涡轮发动机（310）的中架部分（313）并且包括具有最后级叶片的压缩机部分，以使空气流（311）以第一角度（372）定向。 中间部分（313）还包括具有第一级叶片的涡轮机部分，以接收以第二角度（374）定向的空气流（311）。 中间部分（313）还包括歧管（314），用于将空气流（311）从压缩机部分直接耦合到涡轮部分上游的燃烧器头部（318）。 燃烧器头部（318）将空气流（311）中的偏移角从第一角度（372）引入第二角度（374），以使空气流（311）以第二角度从燃烧器头部（318）排出 （374）。 在引入偏移角的同时，燃烧器头（318）至少保持或增加第一角度（372）。
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公开(公告)号：US08893512B2
公开(公告)日：2014-11-25
申请号：US13280474
申请日：2011-10-25
摘要： A compressor bleed cooling fluid feed system for a turbine engine for directing cooling fluids from a compressor to a turbine airfoil cooling system to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. The compressor bleed cooling fluid feed system may enable cooling fluids to be exhausted from a compressor exhaust plenum through a downstream compressor bleed collection chamber and into the turbine airfoil cooling system. As such, the suction created in the compressor exhaust plenum mitigates boundary layer growth along the inner surface while providing flow of cooling fluids to the turbine airfoils.
摘要翻译： 公开了一种用于涡轮发动机的压缩机排放冷却流体进料系统，用于将冷却流体从压缩机引导到涡轮机翼型冷却系统，以将冷却流体供应到转子组件的一个或多个翼型件。 压缩机排放冷却流体供给系统可以使得冷却流体能够通过下游压缩机排气收集室从压缩机排气室排出并进入涡轮机翼型冷却系统。 因此，在压缩机排气增压室中产生的抽吸减轻了沿着内表面的边界层生长，同时将冷却流体流向涡轮机翼型件。
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公开(公告)号：US20130098062A1
公开(公告)日：2013-04-25
申请号：US13280474
申请日：2011-10-25
摘要： A compressor bleed cooling fluid feed system for a turbine engine for directing cooling fluids from a compressor to a turbine airfoil cooling system to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. The compressor bleed cooling fluid feed system may enable cooling fluids to be exhausted from a compressor exhaust plenum through a downstream compressor bleed collection chamber and into the turbine airfoil cooling system. As such, the suction created in the compressor exhaust plenum mitigates boundary layer growth along the inner surface while providing flow of cooling fluids to the turbine airfoils.
摘要翻译： 公开了一种用于涡轮发动机的压缩机排放冷却流体进料系统，用于将冷却流体从压缩机引导到涡轮机翼型冷却系统，以将冷却流体供应到转子组件的一个或多个翼型件。 压缩机排放冷却流体供给系统可以使得冷却流体能够通过下游压缩机排气收集室从压缩机排气室排出并进入涡轮机翼型冷却系统。 因此，在压缩机排气增压室中产生的抽吸减轻了沿着内表面的边界层生长，同时将冷却流体流向涡轮机翼型件。
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