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公开(公告)号：US5642985A
公开(公告)日：1997-07-01
申请号：US559965
申请日：1995-11-17
CPC分类号： F01D5/16 , F01D5/141 , F04D21/00 , F04D29/324 , F04D29/384 , F04D29/386 , F05D2220/327 , F05D2240/302 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2250/713
摘要： A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowing through interblade passages (50) is subjected to a single coincident shock rather than the individual shocks. In one embodiment of the invention the forwardmost extremity of the airfoil defines an inner transition point (40) located at an inner transition radius r.sub.t -inner. The sweep angle of the airfoil is nondecreasing with increasing radius from the inner transition radius to an outer transition radius r.sub.t-outer, radially inward of the airfoil tip (26), and is nonincreasing with increasing radius between the outer transition radius and the airfoil tip.
摘要翻译： 公开了一种用于这种叶片级联的扫掠式涡轮机叶片。 叶片（12）具有独特地扫过的翼型件（22），使得有限径向范围的端壁冲击（64）和通道冲击（66）重合，并且流经叶片间通道（50）的工作介质（48） 以单一的同时震惊而不是个别的冲击。 在本发明的一个实施例中，翼型件的最前端限定位于内部过渡半径rt-内部的内部转变点（40）。 翼型的扫掠角度随着从内部过渡半径到外部过渡半径rt-半径的增加而减小，这在外部过渡半径（外部过渡半径）外部，在翼型端部（26）的径向内侧，并且随着外部过渡半径和翼型尖端之间的半径的增加而增加 。
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2.发明授权
公开(公告)号：US5397215A
公开(公告)日：1995-03-14
申请号：US076325
申请日：1993-06-14
申请人： David A. Spear , Bruce P. Biederman
发明人： David A. Spear , Bruce P. Biederman
CPC分类号： F01D5/143 , F01D5/145 , F01D9/02 , F04D29/321 , F04D29/526 , F04D29/681 , Y02T50/673 , Y10S415/914
摘要： A flow directing assembly 24, 24a for a rotary machine 10 is disclosed. Various construction details are developed to decrease aerodynamic losses and promote the ease of design. In one particular embodiment, a concave region 58 of an end wall is employed to create convex wall regions 54, 56 upstream and downstream of the concave region.
摘要翻译： 公开了一种用于旋转机器10的流动引导组件24,24a。 开发了各种结构细节，以减少空气动力学损失并提高设计的便利性。 在一个特定实施例中，端壁的凹入区域58用于在凹入区域的上游和下游产生凸壁区域54,56。
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公开(公告)号：USRE38040E1
公开(公告)日：2003-03-18
申请号：US09343736
申请日：1999-06-30
IPC分类号： F01D514
CPC分类号： F01D5/16 , F01D5/141 , F04D21/00 , F04D29/324 , F04D29/384 , F04D29/386 , F05D2220/327 , F05D2240/302 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2250/713
摘要： A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowing through interblade passages (50) is subjected to a single coincident shock rather than the individual shocks. In one embodiment of the invention the forwardmost extremity of the airfoil defines an inner transition point (40) located at an inner transition radius rt-inner. The sweep angle of the airfoil is nondecreasing with increasing radius from the inner transition radius to an outer transition radius rt-outer, radially inward of the airfoil tip (26), and is nonincreasing with increasing radius between the outer transition radius and the airfoil tip.
摘要翻译： 公开了一种用于这种叶片级联的扫掠式涡轮机叶片。 叶片（12）具有独特地扫过的翼型件（22），使得有限径向范围的端壁冲击（64）和通道冲击（66）重合，并且流经叶片间通道（50）的工作介质（48） 以单一的同时震惊而不是个别的冲击。 在本发明的一个实施例中，翼型件的最前端限定位于内部过渡半径rt-内部的内部转变点（40）。 翼型的扫掠角度随着从内部过渡半径到外部过渡半径rt-半径的增加而减小，这在外部过渡半径（外部过渡半径）外部，在翼型端部（26）的径向内侧，并且随着外部过渡半径和翼型尖端之间的半径的增加而增加 。
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公开(公告)号：US5460488A
公开(公告)日：1995-10-24
申请号：US259705
申请日：1994-06-14
申请人： David A. Spear , Bruce P. Biederman
发明人： David A. Spear , Bruce P. Biederman
CPC分类号： F01D5/22 , F04D21/00 , F04D29/681 , Y02T50/673
摘要： A compressor or fan blade (112) for a gas turbine engine includes a suction surface midspan shroud (122) which is cambered so that the shroud trailing edge (132) is substantially aligned with the direction of the air flow in the vicinity of the shroud trailing edge (132). The cambered portion originates at the chordwise location where a shock wave (60) attached to the leading edge of the neighboring blade crosses the shroud (136). The cambered portion gradually transitions to an uncambered profile at a circumferential location intermediate the suction surface (110) of the blade (112) and the pressure surface shroud of the neighboring blade.
摘要翻译： 用于燃气涡轮发动机的压缩机或风扇叶片（112）包括吸入表面中跨护罩（122），其被弯曲成使得护罩后缘（132）基本上与护罩附近的空气流的方向对齐 后缘（132）。 弧形部分起始于附接到相邻叶片的前缘的冲击波（60）穿过护罩（136）的弦向位置。 弧形部分在叶片（112）的吸力表面（110）和相邻叶片的压力表面护罩之间的圆周位置处逐渐转变为无弯曲轮廓。
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公开(公告)号：USRE45689E1
公开(公告)日：2015-09-29
申请号：US12785222
申请日：2010-05-21
CPC分类号： F01D5/16 , F01D5/141 , F04D21/00 , F04D29/324 , F04D29/384 , F04D29/386 , F05D2220/327 , F05D2240/302 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2250/713
摘要： A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowing through interblade passages (50) is subjected to a single coincident shock rather than the individual shocks. In one embodiment of the invention the forwardmost extremity of the airfoil defines an inner transition point (40) located at an inner transition radius rt-inner. The sweep angle of the airfoil is nondecreasing with increasing radius from the inner transition radius to an outer transition radius rt-outer, radially inward of the airfoil tip (26), and is nonincreasing with increasing radius between the outer transition radius and the airfoil tip.
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公开(公告)号：USRE43710E1
公开(公告)日：2012-10-02
申请号：US09874931
申请日：2001-06-05
IPC分类号： F01D5/14
CPC分类号： F01D5/16 , F01D5/141 , F04D21/00 , F04D29/324 , F04D29/384 , F04D29/386 , F05D2220/327 , F05D2240/302 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2250/713
摘要： A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowing through interblade passages (50) is subjected to a single coincident shock rather than the individual shocks. In one embodiment of the invention the forwardmost extremity of the airfoil defines an inner transition point (40) located at an inner transition radius rt-inner. The sweep angle of the airfoil is nondecreasing with increasing radius from the inner transition radius to an outer transition radius rt-outer, radially inward of the airfoil tip (26), and is nonincreasing with increasing radius between the outer transition radius and the airfoil tip.
摘要翻译： 公开了一种用于这种叶片级联的扫掠式涡轮机叶片。 叶片（12）具有独特地扫过的翼型件（22），使得有限径向范围的端壁冲击（64）和通道冲击（66）重合，并且流经叶片间通道（50）的工作介质（48） 以单一的同时震惊而不是个别的冲击。 在本发明的一个实施例中，翼型件的最前端限定位于内部过渡半径rt-内部的内部转变点（40）。 翼型的扫掠角度随着从内部过渡半径到外部过渡半径rt-半径的增加而减小，这在外部过渡半径（外部过渡半径）外部，在翼型端部（26）的径向内侧，并且随着外部过渡半径和翼型尖端之间的半径的增加而增加 。
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7.发明申请ORGANIC RANKINE CYCLE (ORC) LOAD FOLLOWING POWER GENERATION SYSTEM AND METHOD OF OPERATION 审中-公开有机发动机循环（ORC）发电系统及其运行方法公开(公告)号：US20120299311A1
公开(公告)日：2012-11-29
申请号：US13575685
申请日：2010-01-27
摘要： A system for producing power using an organic Rankine cycle (ORC) includes a turbine, a generator, an evaporator, an electric heater, an inverter system and an organic Rankine cycle (ORC) voltage regulator. The turbine is coupled to the generator for producing electric power. The evaporator is upstream of the turbine and the electric heater is upstream of the evaporator. The evaporator provides a vaporized organic fluid to the turbine. The electric heater heats the organic fluid prior to the evaporator. The inverter system is coupled to the generator. The inverter system transfers electric power from the generator to a load. The ORC voltage regulator is coupled to the inverter system and to the electric heater and it diverts excess electrical power from the inverter system to the electric heater.
摘要翻译： 使用有机朗肯循环（ORC）生产电力的系统包括涡轮机，发电机，蒸发器，电加热器，逆变器系统和有机朗肯循环（ORC）电压调节器。 涡轮联接到发电机以产生电力。 蒸发器位于涡轮机的上游，电加热器位于蒸发器的上游。 蒸发器向涡轮机提供蒸发的有机流体。 电加热器在蒸发器之前加热有机流体。 逆变器系统耦合到发电机。 逆变器系统将电力从发电机传递到负载。 ORC电压调节器耦合到逆变器系统和电加热器，并将多余的电力从逆变器系统转移到电加热器。
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公开(公告)号：US20110189001A1
公开(公告)日：2011-08-04
申请号：US12696536
申请日：2010-01-29
IPC分类号： F01D9/04
CPC分类号： F01D17/165 , F01D9/042 , F02C6/12 , F05D2210/43 , F05D2260/53
摘要： A variable nozzle system can comprise a gas inlet ring, an opposing gas outlet ring, an actuation ring, guides, and vanes circumferentially spaced about and disposed between the gas inlet ring and the gas outlet ring. The gas inlet ring, the gas outlet ring, and the vanes can form nozzles, the nozzles being variable by rotation of the vanes about a pivot axis. The plurality of guides can extend from the gas inlet ring, the gas outlet ring, or the actuation ring, and the vanes can be connected to the actuation ring, so that each vane can be rotated by rotation of the actuation ring and by sliding against a respective guide from the plurality of guides. The actuation ring can have a gear rack and can be rotated by rotatable engagement of the gear rack with a pinion attached to the end of a rotatable gear shaft.
摘要翻译： 可变喷嘴系统可以包括气体入口环，相对的气体出口环，致动环，引导件和沿周向间隔开并设置在气体入口环和气体出口环之间的叶片。 气体入口环，气体出口环和叶片可以形成喷嘴，喷嘴可通过围绕枢转轴线的叶片的旋转而变化。 多个引导件可以从气体入口环，气体出口环或致动环延伸，并且叶片可以连接到致动环，使得每个叶片可以通过致动环的旋转而旋转并且通过相对于 来自多个引导件的相应引导件。 致动环可以具有齿条并且可以通过齿条与安装在可旋转齿轮轴的端部上的小齿轮的可旋转接合来旋转。
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9.发明申请CASCADED ORGANIC RANKINE CYCLE (ORC) SYSTEM USING WASTE HEAT FROM A RECIPROCATING ENGINE 审中-公开使用来自再生发动机的废热的组合有机RANKINE CYCLE（ORC）系统公开(公告)号：US20100263380A1
公开(公告)日：2010-10-21
申请号：US12738028
申请日：2007-10-04
IPC分类号： F01K25/08
CPC分类号： F02G5/04 , F01K23/065 , F01K25/08 , F02G2262/00 , Y02E20/14 , Y02T10/166
摘要： A method and system for operating a cascaded organic Rankine cycle (ORC) system (100) utilizes two waste heat sources from a positive-displacement engine (106), resulting in increased efficiency of the engine (106) and the cascaded ORC system (100). A high temperature waste heat source from the positive-displacement engine (106) is used in a first ORC system (102) to vaporize a first working fluid (118). A low temperature waste heat source from the positive-displacement engine (106) is used in a second ORC system (104) to heat a second working fluid (130) to a temperature less than the vaporization temperature. The second working fluid (130) is then vaporized using heat from the first working fluid (118). In an exemplary embodiment, the positive-displacement engine (106) is a reciprocating engine. The high temperature waste heat source may be exhaust gas and the low temperature waste heat source may be jacket cooling water.
摘要翻译： 用于操作级联有机朗肯循环（ORC）系统（100）的方法和系统利用来自正排量发动机（106）的两个废热源，导致发动机（106）和级联ORC系统（100 ）。 来自正排量发动机（106）的高温废热源用于第一ORC系统（102）中以蒸发第一工作流体（118）。 来自正排量发动机（106）的低温余热源用于第二ORC系统（104）中，以将第二工作流体（130）加热到低于蒸发温度的温度。 然后使用来自第一工作流体（118）的热量使第二工作流体（130）蒸发。 在示例性实施例中，正排量发动机（106）是往复式发动机。 高温废热源可以是废气，低温废热源可以是夹套冷却水。
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公开(公告)号：US07146813B2
公开(公告)日：2006-12-12
申请号：US10293709
申请日：2002-11-13
申请人： Joost J. Brasz , Bruce P. Biederman
发明人： Joost J. Brasz , Bruce P. Biederman
IPC分类号： F01K25/08
CPC分类号： F01K25/08 , F01D15/10 , F04D25/06 , F04D29/444 , F05D2250/52
摘要： A machine designed as a centrifugal compressor is applied as an organic rankine cycle turbine by operating the machine in reverse. In order to accommodate the higher pressures when operating as a turbine, a suitable refrigerant is chosen such that the pressures and temperatures are maintained within established limits. Such an adaptation of existing, relatively inexpensive equipment to an application that may be otherwise uneconomical, allows for the convenient and economical use of energy that would be otherwise lost by waste heat to the atmosphere.
摘要翻译： 作为离心压缩机设计的机器通过相反地操作机器而被用作有机Rankine循环涡轮机。 为了在作为涡轮机运行时适应较高的压力，选择合适的制冷剂使得压力和温度保持在确定的限度内。 现有的，相对便宜的设备对可能以其他方式不经济的应用的这种适应允许方便和经济地使用否则将由废热损失到大气中的能量。
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