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公开(公告)号：US20180010476A1
公开(公告)日：2018-01-11
申请号：US14854119
申请日：2015-09-15
CPC分类号： F01D15/10 , F01D1/04 , F02C3/04 , F02C3/10 , F02C9/20 , F02C9/22 , F02K3/06 , F05D2220/32 , F05D2220/3213 , F05D2220/3215 , F05D2220/76 , F05D2230/80
摘要： An apparatus and a process for converting a twin spool aero gas turbine engine to an industrial gas turbine engine, where the fan of the aero engine is removed and replaced with an electric generator, a power turbine is added that drives a low pressure compressor that is removed from the aero engine, variable guide vanes are positioned between the high pressure turbine and the power turbine, and a low pressure compressed air line is connected between the outlet of the low pressure compressor and an inlet to the high pressure compressor, where a hot gas flow produced in the combustor first flows through the high pressure turbine, then through the low pressure turbine, and then through the power turbine.
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公开(公告)号：US09410869B2
公开(公告)日：2016-08-09
申请号：US14934219
申请日：2015-11-06
IPC分类号： G01M15/14 , G01M9/02 , G01M17/007 , F02C6/16
CPC分类号： H04B1/1646 , B65D19/16 , F01D5/02 , F01D17/02 , F01D21/003 , F01D25/285 , F02C6/16 , F04D27/001 , F04D29/321 , F05B2220/302 , F05B2260/83 , F05D2220/323 , F05D2260/83 , F23R2900/00019 , G01M9/02 , G01M9/04 , G01M15/14 , G01M17/007 , Y02E60/15
摘要： A process for testing a combustor or a compressor of a gas turbine engine, where a large volume of compressed air is stored in a large reservoir of at least 10,000 m3 such as an underground storage cavern, compressed air from the storage reservoir is passed through an air turbine to drive a compressor to produce high pressure and temperature compressed air, and where the compressed air can be discharged into a combustor and burned with a fuel for testing of the combustor under simulated conditions of a real gas turbine engine.
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3.发明授权Apparatus and process for testing an industrial gas turbine engine and components thereof 有权用于测试工业燃气涡轮发动机及其部件的装置和方法公开(公告)号：US09200983B2
公开(公告)日：2015-12-01
申请号：US14008308
申请日：2012-03-15
申请人： Joseph D. Brostmeyer
发明人： Joseph D. Brostmeyer
IPC分类号： G01M15/14
CPC分类号： G01M15/14
摘要： A system and a process for testing a gas turbine engine or component thereof, especially for a large aero gas turbine engine, and for a process for testing a large industrial gas turbine engine that requires large flow capacity and pressure ratios. The system and process may include the use of a large compressed air storage reservoir to provide compressed air to the testing system. Further, the system and process may also include the use of a pre-heating system, which may include a heater and a heat exchange device, to warm the compressed air from the compressed air storage reservoir to a temperature suitable to simulate normal operating conditions of the gas turbine engine or component thereof.
摘要翻译： 一种用于测试燃气涡轮发动机或其部件，特别是用于大型航空燃气涡轮发动机的系统和过程，以及用于测试需要大流量和压力比的大型工业燃气涡轮发动机的方法。 系统和过程可以包括使用大的压缩空气存储容器来向测试系统提供压缩空气。 此外，系统和过程还可以包括使用预热系统，其可以包括加热器和热交换装置，以将压缩空气从压缩空气存储容器加热至适于模拟正常操作条件的温度 燃气涡轮发动机或其部件。
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公开(公告)号：US07893556B1
公开(公告)日：2011-02-22
申请号：US12780967
申请日：2010-05-17
IPC分类号： F03D3/04
CPC分类号： F03D3/005 , F03D13/25 , F05B2220/7066 , F05B2220/7068 , F05B2240/212 , F05B2240/301 , F05B2240/61 , F05B2240/93 , F05B2240/95 , F05B2260/85 , F05B2260/90 , Y02E10/727 , Y02E10/74
摘要： A bearingless floating wind turbine has a tall narrow main support structure with a center of buoyancy located well above the center of gravity to provide stability to the wind turbine while supported for rotation in a body of water, a vertical axis turbine blade extends from the main support structure and rotates together under a wind, and a non-rotating shaft extends through the main support structure with a vertical axis direct drive generator connected between the main support structure and the non-rotating shaft to produce electricity when the main support structure rotates. An anchor line connected to the non-rotating shaft prevents the floating wind turbine from drifting in a body of water.
摘要翻译： 无轴承浮动风力涡轮机具有高的窄的主要支撑结构，其浮力中心位于重心之上，以便在风力涡轮机同时被支撑以在水体中旋转时提供稳定性，垂直轴线涡轮机叶片从主体 支撑结构并在风中一起旋转，并且非旋转轴通过连接在主支撑结构和非旋转轴之间的垂直轴直接驱动发生器延伸通过主支撑结构，以在主支撑结构旋转时产生电力。 连接到非旋转轴的锚线防止浮动风力涡轮机在水体中漂移。
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公开(公告)号：US20170342854A1
公开(公告)日：2017-11-30
申请号：US15137248
申请日：2016-04-25
CPC分类号： F01D17/16 , F01D15/10 , F01D17/162 , F01K23/106 , F02C3/04 , F02C3/13 , F02C6/04 , F02C6/18 , F02C9/20 , F02C9/22 , F04D29/403 , F05D2220/32 , F05D2220/76 , F05D2240/128 , F05D2270/023 , F05D2270/053 , F05D2270/061 , H02P9/04 , Y02E20/16
摘要： A large frame heavy duty industrial gas turbine engine that can produce twice the power as a conventional single spool industrial engine, and can operate at full power during a hot day. The industrial engine includes a high spool that directly drives an electric generator at a synchronous speed of the electric power grid, a low spool with a low pressure turbine that drives a low pressure compressor from the exhaust gas from the high pressure turbine, where the low pressure compressor supplies compressed air to the high pressure compressor. Variable inlet guide vane assemblies are used in the low pressure turbine and the low pressure compressor so that the high spool can operate at full power even during a hot day. The low spool is designed to operate at a higher speed than at the normal temperature conditions so that a high mass flow can be produced for the high spool during the hot day conditions.
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公开(公告)号：US09353687B1
公开(公告)日：2016-05-31
申请号：US14450944
申请日：2014-08-04
CPC分类号： F02C7/16 , F01D5/185 , F01D9/065 , F01D25/12 , F05B2260/205 , F05D2260/207 , F05D2260/232 , F05D2300/1606 , F05D2300/1612 , Y02T50/672 , Y02T50/676
摘要： A gas turbine engine with a closed-loop liquid metal cooling fluid system for cooling stator vanes within the turbine, in which the stator vanes are made of a metallic material that will not react with the liquid metal cooling fluid. The stator vane may be made from a typical metal material such as ferrous metal alloys, nickel alloys or cobalt (Co) alloys, and an insert or liner made of molybdenum or tantalum may be placed inside to protect the outer vane material from reacting with a liquid metal such as bismuth, lead (Pb), indium, or alloy mixtures of thereof. In the case where the liquid coolant is bismuth, the liquid bismuth must be purged from the cooling system before the fluid cools and solidifies so the solidified bismuth does not expand and break the vanes.
摘要翻译： 一种具有用于冷却涡轮内的定子叶片的闭环液态金属冷却流体系统的燃气涡轮发动机，其中定子叶片由不会与液态金属冷却流体反应的金属材料制成。 定子叶片可以由诸如黑色金属合金，镍合金或钴（Co）合金的典型金属材料制成，并且可以将由钼或钽制成的插入件或衬垫放置在内部以保护外部叶片材料不与 液态金属如铋，铅（Pb），铟或其合金混合物。 在液体冷却剂为铋的情况下，液体铋在流体冷却并凝固之前必须从冷却系统中清除，因此凝固的铋不膨胀并破坏叶片。
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公开(公告)号：US08770913B1
公开(公告)日：2014-07-08
申请号：US12817440
申请日：2010-06-17
IPC分类号： F04D27/02
CPC分类号： F04D29/053 , F01D17/02 , F01D21/00 , F02C9/00 , F04D19/002 , F04D27/001 , F05D2260/80 , F05D2270/804
摘要： An apparatus and a process for measuring rotor creep values for a monolithic rotor of an industrial gas turbine engine in order to determine when creep growth of the rotor has exceeded an allowable limit. One or more critical locations of the rotor are measured for real-time radius, and a CPU having rotor creep deflection model is used to compare the real-time data and determine if the rotor creep is within safe and allowable limits. If the creep is determined to exceed allowable values, then an alarm in initiated or engine shutdown occurs.
摘要翻译： 用于测量工业燃气涡轮发动机的单片转子的转子蠕变值的装置和方法，以便确定转子的蠕变生长是否已经超过允许极限。 测量转子的一个或多个关键位置用于实时半径，并且使用具有转子蠕变偏转模型的CPU来比较实时数据并确定转子蠕变是否在安全和允许的极限内。 如果蠕变确定超过允许值，则发生启动或发动机关闭时发生报警。
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公开(公告)号：US08721265B1
公开(公告)日：2014-05-13
申请号：US13946003
申请日：2013-07-19
申请人： Joseph D Brostmeyer , John E Ryznic
发明人： Joseph D Brostmeyer , John E Ryznic
CPC分类号： F04D29/584 , F01D5/187 , F02C6/08 , F02C7/18 , F02C7/224 , F04D19/02 , F04D29/324 , F04D29/542 , F05D2220/3219 , F05D2260/205 , Y02T50/676
摘要： A high compression ratio compressor having multiple stages of airfoils to produce the high pressure rations, where the last stage airfoils are cooled by passing cooling air through the airfoils without discharging film cooling air. A portion of the compressed air from the discharge of the compressor is bled off and passed through a heat exchanger to preheat a fuel and to cool the compressed air. The cooled compressed air is then passed through the last stage airfoil of the compressor to provide cooling. The cooling air is then reintroduced back into the compressor at an earlier stage or passed through an airfoil in the turbine to provide cooling.
摘要翻译： 具有多级翼型件以产生高压口径的高压缩比压缩机，其中通过使冷却空气通过翼型件而不排放膜冷却空气来冷却最后级翼型件。 来自压缩机排出的压缩空气的一部分被排出并通过热交换器以预热燃料并冷却压缩空气。 冷却的压缩空气然后通过压缩机的最后一级翼型件以提供冷却。 然后冷却空气在较早的阶段被重新引入压缩机，或者通过涡轮机中的翼型以提供冷却。
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9.发明授权Process for re-designing a distressed component used under thermal and structural loading 有权重新设计在热和结构加载下使用的不良部件的过程公开(公告)号：US08505181B1
公开(公告)日：2013-08-13
申请号：US13478005
申请日：2012-05-22
IPC分类号： B23Q17/00
CPC分类号： F01D5/005 , F01D5/141 , F01D21/003 , F05D2270/708 , F05D2270/71 , F05D2270/8041 , Y10T29/49758 , Y10T29/49764 , Y10T29/49771
摘要： A process for redesigning a distressed component in which the distressed component is under thermal and structural loads, for improving the life of the component. The process includes obtaining the operating conditions of the machine in which the distressed component is used, finding the boundary conditions under which the distressed component operates, producing a 3-dimensional model of the distressed component with such detail that the distress levels are accurately represented on the model, subjecting the model to a series of technical analysis to predict a life for the component, reiterating the technical analysis until the levels of distress on the model accurately represent the distress that appears on the actual component, and then predicting a remaining life of the component based on the analysis, or redesigning the model and reanalyzing the model until a maximum life for the component has been found.
摘要翻译： 一种重新设计遇险部件的过程，其中受损部件处于热和结构负载下，以改善部件的使用寿命。 该过程包括获得其中使用受损部件的机器的操作条件，找到遇险部件在其下运行的边界条件，产生不良部件的3维模型，其中具有如下细节：遇险水平被准确地表示在 模型，对模型进行一系列技术分析以预测组件的生命，重申技术分析，直到模型的困扰程度准确地表示出现在实际组件上的痛苦，然后预测剩余寿命 基于分析的组件，或重新设计模型并重新分析模型，直到找到组件的最大寿命。
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公开(公告)号：US08250851B1
公开(公告)日：2012-08-28
申请号：US13050828
申请日：2011-03-17
申请人： Joseph D. Brostmeyer
发明人： Joseph D. Brostmeyer
IPC分类号： F02C3/00
CPC分类号： F01D9/023 , F05B2260/3011 , F05D2240/12 , F05D2300/607
摘要： A transition duct used in a gas turbine engine to direct the hot gas flow from the combustor into the turbine section of the gas turbine engine. The transition duct includes a plurality of guide vane integral with the duct. The transition duct includes a circular shaped inlet end for connection to a can combustor and a rectangular and arched shaped outlet end for connection to a first stage turbine section. the guide vanes extend within the flow path between inner and outer projections each having a curved opening in the shape of the airfoil each airfoil includes inner and outer airfoil ends with retainer slots formed between the airfoil ends and the duct projections that form shear pin retainer slots. Shear pin retainers are secured within the slots to secure the guide vanes to the duct in a thermally uncoupled manner to reduce thermal stresses. The guide vanes can be made from a single crystal material for higher gas flow temperatures.
摘要翻译： 一种用于燃气涡轮发动机的过渡管道，用于将来自燃烧器的热气流引导到燃气涡轮发动机的涡轮部分。 过渡管道包括与导管一体的多个导向叶片。 过渡管道包括用于连接到罐式燃烧器的圆形入口端和用于连接到第一级涡轮机部分的矩形和拱形出口端。 导向叶片在内部和外部突出部之间的流动路径内延伸，每个翼部具有翼型形状的弯曲开口，每个翼型件包括形成有翼型端部和管道突起之间的保持槽的内部和外部翼型端部，形成剪切销保持器狭槽 。 剪切销保持器固定在槽内以将导叶以热脱开的方式固定到管道上以减少热应力。 引导叶片可以由单晶材料制成，用于更高的气体流动温度。
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