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公开(公告)号：US09709458B1
公开(公告)日：2017-07-18
申请号：US14623007
申请日：2015-02-16
摘要： A hydrocarbon leak detection sensor having a hydrocarbon indicator paint applied to a surface exposed to a flow in which the presence of a hydrocarbon is detected. The sensor is located at a low point in a static drain line that is connected to a main fuel line of a liquid propellant rocket engine between a main fuel valve and a fuel injector of a combustion chamber. The sensor includes a housing with a flow inlet port and a flow outlet port with an optical device opposed to a removable plug that secures a target disk with a hydrocarbon indicator paint applied to an exposed surface. A light source is used to illuminate the hydrocarbon indicator that changes color from white to red in the presence of a hydrocarbon.
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公开(公告)号：US20160333737A1
公开(公告)日：2016-11-17
申请号：US14245199
申请日：2014-04-04
申请人： Timothy J Miller , Alex Pinera
发明人： Timothy J Miller , Alex Pinera
CPC分类号： F01D25/22 , F02B37/04 , F05D2220/40
摘要： A turbocharger for an internal combustion engine, the turbocharger being supported by hydrostatic bearings in both a radial and an axial direction by a compressed air supplied from a compressor of the turbocharger and boosted in pressure by a separate boost pump to a high enough pressure to support the rotor of the turbocharger.
摘要翻译： 一种用于内燃机的涡轮增压器，所述涡轮增压器通过由涡轮增压器的压缩机供应的压缩空气在径向和轴向方向上由静压轴承支撑，并通过单独的增压泵将压力提升到足够高的压力以支撑 涡轮增压器的转子。
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公开(公告)号：US10054005B1
公开(公告)日：2018-08-21
申请号：US14607846
申请日：2015-01-28
申请人： Alex Pinera , Timothy J Miller
发明人： Alex Pinera , Timothy J Miller
CPC分类号： F02B39/10 , F01D25/164 , F01D25/22 , F02B37/04 , F02B67/10 , F05D2220/40 , F05D2240/53 , F16C32/06 , Y02T10/144
摘要： A turbocharger for an internal combustion engine, the turbocharger being supported by hydrostatic bearings in both a radial and an axial direction by a compressed air supplied from a compressor of the turbocharger and boosted in pressure by a separate boost pump to a high enough pressure to support the rotor of the turbocharger. The turbocharger hydrostatic bearings are damped using wire mesh or dispersed friction dampers.
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公开(公告)号：US20170082070A1
公开(公告)日：2017-03-23
申请号：US15227031
申请日：2016-08-03
申请人： Timothy J. Miller , Alex Pinera , Stephen M. Brooks , John W. Appleby, JR. , Timothy G. Leonard
发明人： Timothy J. Miller , Alex Pinera , Stephen M. Brooks , John W. Appleby, JR. , Timothy G. Leonard
摘要： A turbopump for a liquid rocket engine in which an oxidizer is pumped, where the turbopump is formed with a single piece rotor within a single piece housing by a metal additive manufacturing process, and where surfaces exposed to the oxidizer is coated with enamel glass to provide a smooth surface over the rough printed surface and to provide burn resistance to the base metal from exposure to the oxidizer such as oxygen. A Mondaloy coating can be used below the enamel glass coating to add additional burn resistance to the base metal.
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公开(公告)号：US09540952B2
公开(公告)日：2017-01-10
申请号：US14245199
申请日：2014-04-04
申请人： Timothy J Miller , Alex Pinera
发明人： Timothy J Miller , Alex Pinera
CPC分类号： F01D25/22 , F02B37/04 , F05D2220/40
摘要： A turbocharger for an internal combustion engine, the turbocharger being supported by hydrostatic bearings in both a radial and an axial direction by a compressed air supplied from a compressor of the turbocharger and boosted in pressure by a separate boost pump to a high enough pressure to support the rotor of the turbocharger.
摘要翻译： 一种用于内燃机的涡轮增压器，所述涡轮增压器通过由涡轮增压器的压缩机供应的压缩空气在径向和轴向方向上由静压轴承支撑，并通过单独的增压泵将压力提升到足够高的压力以支撑 涡轮增压器的转子。
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公开(公告)号：US09200597B1
公开(公告)日：2015-12-01
申请号：US13572809
申请日：2012-08-13
申请人： Alex Pinera
发明人： Alex Pinera
摘要： An extendable nozzle for a rocket engine includes a chamber with a main combustion chamber and a throat and a main nozzle formed within a guide tube, where a nozzle extension slides over the guide tube from a stowed position to an extendable position. A locking O-ring secures the nozzle extension in a stowed position, and a locking split ring holds the nozzle extension in the extended position.
摘要翻译： 用于火箭发动机的可延伸喷嘴包括具有主燃烧室和喉部的腔室和形成在引导管内的主喷嘴，其中喷嘴延伸部从引导管从收起位置滑动到可延伸位置。 锁定O形环将喷嘴延伸部固定在收起位置，并且锁定开口环将喷嘴延伸部保持在延伸位置。
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公开(公告)号：US08220267B1
公开(公告)日：2012-07-17
申请号：US12571579
申请日：2009-10-01
申请人： Elizabeth V Stein , Alex Pinera
发明人： Elizabeth V Stein , Alex Pinera
IPC分类号： F02C7/24
CPC分类号： F02K9/46 , F02C7/24 , F02K9/563 , F05D2260/80
摘要： A Helmholtz resonator is used to detect a presence of a two-phase flow in a conduit. The resonator is sized so that a range of frequencies it is tuned for corresponds to a change in the speed of sound as the fluid changes from all liquid, to liquid plus vapor, and to all vapor. A band-pass filter is used to cancel out any external noise that would pollute the signal from the resonator. The resonator is used to monitor for a two-phase flow occurring within a feed line leading into a turbopump of a rocket engine.
摘要翻译： 亥姆霍兹共振器用于检测导管中两相流的存在。 谐振器的尺寸使得其调谐的频率范围对应于随着流体从所有液体，液体加蒸汽和全部蒸汽变化而产生的声速变化。 使用带通滤波器来抵消会污染来自谐振器的信号的任何外部噪声。 谐振器用于监测在通向火箭发动机的涡轮泵的进料管线内发生的两相流。
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公开(公告)号：US07445424B1
公开(公告)日：2008-11-04
申请号：US11409925
申请日：2006-04-22
申请人： Todd A. Ebert , Alex Pinera , Antonio Negron
发明人： Todd A. Ebert , Alex Pinera , Antonio Negron
IPC分类号： F01D11/04
CPC分类号： F01D11/001 , F01D5/081 , F05D2240/56 , F05D2260/14 , F05D2300/50212 , F16J15/3288
摘要： In a gas turbine engine having a rim cavity formed between a rotor disk and a stator, and a brush seal or other seal member providing an airflow seal between the stator and a side plate of the rotor disk, a thermally responsive valve device is located in the bypass passage of the stator to form a parallel air flow path with the brush seal. As the brush seal wears and the leakage airflow around the worn brush seal increases, the air flow temperature in the rim cavity would decrease. The thermally responsive valve device would detect the decreasing airflow temperature, and reduce the airflow passing through the bypass passage in order to prevent the temperature of the rim cavity from decreasing. The temperature responsive valve device makes use of a bimetallic valve member that regulates airflow based upon temperature.
摘要翻译： 在具有形成在转子盘和定子之间的边缘空腔的燃气涡轮发动机中，以及在定子和转子盘的侧板之间提供气流密封的刷密封件或其他密封构件，热响应阀装置位于 定子的旁路通道与刷密封件形成平行的空气流动路径。 当刷子密封件磨损并且磨损的刷密封件周围的泄漏气流增加时，轮辋腔中的空气流动温度将降低。 热响应阀装置将检测气流温度的降低，并且减少通过旁路通道的气流，以防止边缘腔的温度降低。 温度响应阀装置利用基于温度来调节气流的双金属阀构件。
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公开(公告)号：US08083469B1
公开(公告)日：2011-12-27
申请号：US12408016
申请日：2009-03-20
申请人： Alex Pinera
发明人： Alex Pinera
IPC分类号： F01D11/00
CPC分类号： F01D25/18 , F01D25/16 , F05D2260/20 , F05D2300/509 , Y02T50/671 , Y02T50/676 , Y10S384/907
摘要： A bearing lubrication system for a high temperature bearing, such as in a small gas turbine engine for a UAV, in which the bearing and lubricant requires a long shelf life, where the bearing includes a solid lubricant movable within a chamber formed within a housing and located adjacent to the bearing. The solid lubricant is biased by a spring toward the bearing and abuts against a runner that rotates along with the rotor shaft during engine operation. A cooling air passage opens into a space formed between the bearing and the solid lubricant to supply cooling air through the bearing. When the engine operates, heat is transferred through the runner to the solid lubricant to melt the lubricant. Rubbing of the runner against the biased solid lubricant will also melt the lubricant. The melting lubricant is carried by the cooling air through the bearing to provide both cooling and lubrication for the bearing.
摘要翻译： 一种用于高温轴承的轴承润滑系统，例如在用于UAV的小型燃气涡轮发动机中，其中轴承和润滑剂需要较长的保质期，其中轴承包括在形成于壳体内的室内可移动的固体润滑剂， 位于轴承附近。 固体润滑剂由弹簧朝向轴承偏置，并与发动机运转期间与转子轴一起转动的转轮抵接。 冷却空气通道通向轴承和固体润滑剂之间形成的空间，以通过轴承供应冷却空气。 当发动机运转时，热量通过流道传递到固体润滑剂以熔化润滑剂。 将润滑剂摩擦偏压的固体润滑剂也会使润滑剂熔化。 熔化润滑剂由冷却空气通过轴承承载，为轴承提供冷却和润滑。
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公开(公告)号：US07748959B1
公开(公告)日：2010-07-06
申请号：US11787559
申请日：2007-04-17
申请人： Alex Pinera , Todd A. Ebert
发明人： Alex Pinera , Todd A. Ebert
IPC分类号： F01D5/08
CPC分类号： F01D5/08 , F02K9/48 , F05D2250/621 , F05D2300/504
摘要： A turbine disc used in a turbo-pump that is exposed to a large thermal gradient across the sides of the rotor disc. The warm side of the turbine disc is covered by a cover plate that forms a sealed space between the turbine disc and the cover plate, and this space is evacuated or insulated to form a complete vacuum or as near as a complete vacuum as possible. The surfaces of the turbine disc and cover plate that form the vacuum space are also coated with a reflective coating such as with a highly polished surface of low emissivity in order to minimize the radiation heat loss through the vacuum space. The turbine disc can have a cover plate forming a vacuum space or insulated cavity on both sides of the turbine disc. Ribs are also used within the vacuum space as supports for the cover plate due to the difference in pressure from the ambient side and the vacuum.
摘要翻译： 在涡轮泵中使用的涡轮盘，其在转子盘的侧面上暴露于大的热梯度。 涡轮盘的温暖的一侧由盖板覆盖，该盖板在涡轮盘和盖板之间形成密封空间，并且该空间被抽空或绝缘以形成尽可能接近完全真空的完全真空。 形成真空空间的涡轮盘和盖板的表面也涂覆有诸如具有低发射率的高抛光表面的反射涂层，以便使通过真空空间的辐射热损失最小化。 涡轮盘可以具有在涡轮盘的两侧形成真空空间或绝缘腔的盖板。 由于与环境侧和真空的压力差，在真空空间内还使用肋作为盖板的支撑。
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