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1. 发明授权

US08421263B2 Floating vertical axis wind turbine 有权
标题翻译：浮动垂直轴风力发电机
公开(公告)号：US08421263B2
公开(公告)日：2013-04-16
申请号：US12913023
申请日：2010-10-27
申请人： Jack W. Wilson, Jr. , John E. Ryznic , Joseph D. Brostmeyer
发明人： Jack W. Wilson, Jr. , John E. Ryznic , Joseph D. Brostmeyer
IPC分类号： F03D9/00
CPC分类号： F03D3/061 , F03D13/25 , F03D80/70 , F05B2240/93 , F05B2250/86 , Y02E10/727 , Y02E10/74 , Y10T29/49229 , Y10T29/49826
摘要： A large floating vertical axis wind turbine with a floating inner cylinder having rotor blades that rotate together as an assembly, and a floating outer cylinder with a central opening in which the floating inner cylinder rotates for support against tipping. Outriggers with floating devices on the ends extend out from the floating outer cylinder for additional stability. The floating inner cylinder is partially supported by a top bearing on the outer cylinder to carry some of the load from the rotor blades.
摘要翻译：具有浮动内筒的大浮动垂直轴风力涡轮机，其具有作为组件一起旋转的转子叶片，以及具有中心开口的浮动外筒，浮动内筒旋转以支撑以防止倾翻。具有浮动装置的外伸支架从浮动外筒延伸出来以获得额外的稳定性。浮动内筒由外筒上的顶部轴承部分支撑，以承载来自转子叶片的一些载荷。

2. 发明申请

US20170298826A1 Industrial gas turbine engine with turbine airfoil cooling 审中-公开
公开(公告)号：US20170298826A1
公开(公告)日：2017-10-19
申请号：US15131426
申请日：2016-04-18
申请人： John E. Ryznic , Russell B. Jones , Joseph D. Brostmeyer , Justin T. Cejka
发明人： John E. Ryznic , Russell B. Jones , Joseph D. Brostmeyer , Justin T. Cejka
IPC分类号： F02C7/18 , F01P1/06 , F01D5/18 , F01D15/10 , H02K7/18 , F02C3/04
CPC分类号： F02C7/18 , F01D5/18 , F01D15/10 , F01P1/06 , F02C3/04 , F02C6/02 , F05D2230/80 , H02K7/1823 , Y02E20/16
摘要： A process for retrofitting an electric power plant that uses two 60 Hertz large frame heavy duty industrial gas turbine engines to drive electric generators and produce electricity, where each of the two industrial engines can produce up to 350 MW of output power. The process replaces the two 350 MW industrial engines with one twin spool industrial gas turbine engine that is capable of producing at least 700 MW of output power. Thus, two prior art industrial engines can be replaced with one industrial engine that can produce power equal to the two prior art industrial engines.

3. 发明申请

US20170241336A1 Process for retrofitting an industrial gas turbine engine for increased power and efficiency 审中-公开
公开(公告)号：US20170241336A1
公开(公告)日：2017-08-24
申请号：US15157269
申请日：2016-05-17
申请人： Russell B. Jones , Joseph D. Brostmeyer , Justin T. Cejka , John E. Ryznic
发明人： Russell B. Jones , Joseph D. Brostmeyer , Justin T. Cejka , John E. Ryznic
IPC分类号： F02C3/13 , F01D17/14 , F02C9/22 , F01D15/10 , F02C7/18 , F02C9/18
CPC分类号： F02C3/13 , F01D15/10 , F01D17/14 , F02C3/00 , F02C6/00 , F02C7/18 , F02C9/18 , F02C9/22 , F05D2220/32 , F05D2220/76 , F05D2230/80 , F05D2240/35 , F05D2260/202 , F05D2260/211
摘要： A process for retrofitting an industrial gas turbine engine of a power plant where an old industrial engine with a high spool has a new low spool with a low pressure turbine that drives a low pressure compressor using exhaust gas from the high pressure turbine, and where the new low pressure compressor delivers compressed air through a new compressed air line to the high pressure compressor through a new inlet added to the high pressure compressor. The old electric generator is replaced with a new generator having around twice the electrical power production. One or more stages of vanes and blades are removed from the high pressure compressor to optimally match a pressure ratio split. Closed loop cooling of one or more new stages of vanes and blades in the high pressure turbine is added and the spent cooling air is discharged into the combustor.

4. 发明授权

US08858161B1 Multiple staged compressor with last stage airfoil cooling 有权
标题翻译：多级压缩机，最后阶段翼型冷却
公开(公告)号：US08858161B1
公开(公告)日：2014-10-14
申请号：US14246166
申请日：2014-04-07
申请人： John E. Ryznic , James P. Downs , Joseph D. Brostmeyer
发明人： John E. Ryznic , James P. Downs , Joseph D. Brostmeyer
IPC分类号： F01D5/14 , F03B11/00 , F03D11/00 , F04D29/36 , F01D25/12 , F01D15/10
CPC分类号： F01D25/12 , F02C7/143 , F02C7/16 , F02C7/185 , F04D19/02 , F04D29/324 , F04D29/542 , F04D29/584 , F05D2220/3216 , F05D2220/3219 , F05D2260/213 , Y02T50/676
摘要： An industrial gas turbine engine in which a compressor includes later stage airfoils that are cooled using a coolant from an external closed loop cooling circuit or from a heat recovery steam generator. Cooling air compressed by a compressor external to the IGT engine can be used for cooling of the main compressor airfoils with a heat exchanger to preheat a fuel used in the combustor. Or, water and steam from a heat recover steam generator can be used to cool the compressor airfoils in which steam can be bled off from the steam generator for cooling and then reintroduced into the HRSG at a downstream stage. Steam is used to cool the rotor blades while water is used to cool the stator vanes.
摘要翻译：一种工业燃气涡轮发动机，其中压缩机包括使用来自外部闭环冷却回路或来自热回收蒸汽发生器的冷却剂冷却的后级翼型件。由IGT发动机外部的压缩机压缩的冷却空气可用于利用热交换器对主压缩机翼型件进行冷却，以预热燃烧器中使用的燃料。或者，来自热回收蒸汽发生器的水和蒸汽可以用于冷却压缩机翼型，其中蒸汽可以从蒸汽发生器排出以进行冷却，然后在下游阶段再次引入HRSG。蒸汽用于冷却转子叶片，同时使用水来冷却定子叶片。

5. 发明申请

US20170342854A1 Twin spool industrial gas turbine engine with variable inlet guide vanes 审中-公开
公开(公告)号：US20170342854A1
公开(公告)日：2017-11-30
申请号：US15137248
申请日：2016-04-25
申请人： Barry J. Brown , Joseph D. Brostmeyer , Justin T. Cejka , Russell B. Jones
发明人： Barry J. Brown , Joseph D. Brostmeyer , Justin T. Cejka , Russell B. Jones
IPC分类号： F01D17/16 , F02C3/04 , F01D15/10 , F04D29/40 , H02P9/04 , F01K23/10 , F02C6/18
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.

6. 发明授权

US08250851B1 Transition duct with integral guide vanes 有权
标题翻译：具有整体导叶的过渡管
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。

7. 发明申请

US20180010476A1 Apparatus and process for converting an aero gas turbine engine into an industrial gas turbine engine for electric power production 审中-公开
公开(公告)号：US20180010476A1
公开(公告)日：2018-01-11
申请号：US14854119
申请日：2015-09-15
申请人： Joseph D. Brostmeyer , Russell B. Jones
发明人： Joseph D. Brostmeyer , Russell B. Jones
IPC分类号： F01D15/10 , F01D1/04 , F02C3/10 , F02C3/04 , F02C9/22
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.

8. 发明授权

US09200983B2 Apparatus and process for testing an industrial gas turbine engine and components thereof 有权
标题翻译：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。

9. 发明申请

US20160313212A1 Process for testing a compressor or a combustor of a gas turbine engine using a large compressed air storage reservoir 有权
公开(公告)号：US20160313212A1
公开(公告)日：2016-10-27
申请号：US15200125
申请日：2016-07-01
申请人： Joseph D. Brostmeyer , Robert L. Memmen
发明人： Joseph D. Brostmeyer , Robert L. Memmen
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.

10. 发明申请

US20160195018A1 Turbine last stage rotor blade with forced driven cooling air 审中-公开
标题翻译：涡轮机末级转子叶片带强制驱动冷却空气
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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