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公开(公告)号：US20160313212A1
公开(公告)日：2016-10-27
申请号：US15200125
申请日：2016-07-01
IPC分类号： G01M15/14 , F01D25/28 , F01D21/00 , G01M9/04 , G01M17/007
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 full-sized aircraft or full-sized gas turbine engine in a wind tunnel and includes the steps of securing a full-sized aircraft or engine in a wind tunnel for testing; filling an underground storage reservoir with compressed air; passing pre-treated compressed air from the underground storage reservoir through the wind tunnel for testing of the full-sized aircraft or engine; connecting an outlet of the wind tunnel to an ejector; and, passing compressed air from the underground storage reservoir through the ejector to decrease the exit pressure at the wind tunnel during testing of the full-sized aircraft or engine. The step of pre-treating compressed air from the underground storage reservoir includes preheating the compressed air; and, passing the higher temperature compressed air into the wind tunnel.
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2.发明申请Process for testing a compressor or a combustor of a gas turbine engine using a large compressed air storage reservoir 审中-公开使用大压缩空气储存容器测试燃气轮机的压缩机或燃烧器的方法公开(公告)号：US20160305436A1
公开(公告)日：2016-10-20
申请号：US15198440
申请日：2016-06-30
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 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.
摘要翻译： 一种用于测试燃气涡轮发动机的压缩机的方法，其中大容积的压缩空气储存在诸如地下储存室的至少10,000立方米的大型储存器中，来自储存容器的压缩空气通过空气涡轮机 驱动压缩机以产生高压和高温压缩空气，并且其中压缩空气可以排放到燃烧器中并在燃气涡轮发动机的模拟条件下用燃料测试燃烧器。
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公开(公告)号：US20170097284A1
公开(公告)日：2017-04-06
申请号：US15200102
申请日：2016-07-01
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 turbine of a gas turbine engine at high altitudes, 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 heat exchanger to preheat the compressed air to a temperature that would normally be discharged from a compressor, the preheated compressed air is burned with a fuel in the combustor, and additional compressed air from the reservoir is passed through an injector located downstream from the turbine to produce a decreased pressure such that a low atmospheric condition at the turbine exit is simulated.
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公开(公告)号：US20170097283A1
公开(公告)日：2017-04-06
申请号：US15200057
申请日：2016-07-01
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 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 heat exchanger to preheat the compressed air to a temperature that would normally be discharged from a compressor, the preheated compressed air is burned with a fuel in the combustor, and additional compressed air from the reservoir is passed through an injector located downstream from the combustor to produce a decreased pressure such that a low atmospheric condition at the combustor exit is simulated.
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5.发明申请Process for testing a compressor or a combustor of a gas turbine engine using a large compressed air storage reservoir 有权使用大压缩空气储存容器测试燃气轮机的压缩机或燃烧器的方法公开(公告)号：US20160069777A1
公开(公告)日：2016-03-10
申请号：US14934219
申请日：2015-11-06
IPC分类号： G01M15/14 , G01M9/02 , G01M17/007 , F02C3/04
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.
摘要翻译： 一种用于测试燃气涡轮发动机的燃烧器或压缩机的方法，其中大容积的压缩空气存储在诸如地下储存室的至少10,000立方米的大容器中，来自储存容器的压缩空气通过 空气涡轮机以驱动压缩机以产生高压和高温的压缩空气，并且其中压缩空气可以在燃气涡轮发动机的模拟条件下被排放到燃烧器中并用燃料燃烧以测试燃烧器。
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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：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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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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9.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：US20160195018A1
公开(公告)日：2016-07-07
申请号：US14512070
申请日：2014-10-10
申请人： Joseph D. Brostmeyer
发明人： Joseph D. Brostmeyer
IPC分类号： F02C7/18
CPC分类号： F02C7/18 , F01D5/082 , F05D2220/3215 , F05D2260/20
摘要： A turbine of a gas turbine engine with a rotor and a stator forming a rim cavity, where the rotor includes a turbine rotor blade with a cooling air channel opening into the rim cavity, and a centrifugal impeller rotatably connected to the rotor in which the centrifugal impeller discharges pressurized cooling air into the rim cavity to improve the rim cavity seal and to supply pressurized cooling air to the rotor blade cooling air channel.
摘要翻译： 具有转子和定子的燃气涡轮发动机的涡轮机形成轮辋腔，其中所述转子包括具有通向所述轮辋腔的冷却空气通道的涡轮机转子叶片，以及可旋转地连接到所述转子的离心式叶轮，其中所述离心机 叶轮将加压的冷却空气排放到轮辋腔中，以改善轮辋腔密封并将加压的冷却空气供应到转子叶片冷却空气通道。
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