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1. 发明授权

US08566000B2 System and method for controlling a single-spool turboshaft engine 有权
标题翻译：用于控制单轴涡轮轴发动机的系统和方法
公开(公告)号：US08566000B2
公开(公告)日：2013-10-22
申请号：US13032792
申请日：2011-02-23
申请人： Ray D. Lickfold , Gregg Williams , Robert S. Thompson, Jr.
发明人： Ray D. Lickfold , Gregg Williams , Robert S. Thompson, Jr.
IPC分类号： F02C9/00 , F02C6/00 , F02G3/00 , F02K1/16 , F02K1/18 , F02K3/00 , G06F19/00 , G06G7/70 , F01B25/00 , F01D17/00 , F01D19/00 , F01D21/00 , F04D15/00 , F04D27/00
CPC分类号： F02C9/32 , B64D27/10 , B64D31/06 , B64D2033/0293 , F02C9/28 , F02C9/44 , F05D2220/32 , F05D2270/07 , F05D2270/304
摘要： A controller receives a power-level command representative of a level of power to be transmitted by a single-spool turboshaft engine to a controllable load. A torque command determined responsive to a measure of inlet pressure, from a control schedule responsive to the power-level command, is representative of a level of torque to be transmitted by an element to drive the controllable load. Under some operating conditions, a rotational speed command provides for at least nearly minimizing a measure of associated fuel consumption when the transmitted torque is regulated to the level corresponding to the torque command by controlling one of the controllable load and a fuel flow to the engine, and the other of the controllable load and the fuel flow to the engine is controlled so as to regulate an associated rotational speed to a level corresponding to the rotational speed command.
摘要翻译：控制器接收代表要由单线轴涡轮轴发动机传递到可控负载的功率水平的功率级指令。响应于功率级命令的控制调度响应于入口压力的测量而确定的扭矩指令代表由元件传递以驱动可控负载的转矩水平。在一些操作条件下，转速指令通过控制可控制的负载和向发动机的燃料流中的一个传递转矩被调节到与转矩指令相对应的水平，提供至少几乎最小化相关燃料消耗的量度，并且控制负载和发动机的燃料流中的另一个被控制成将相关联的转速调整到与转速指令相对应的水平。

2. 发明授权

US08459038B1 Two-spool turboshaft engine control system and method 有权
标题翻译：双轴涡轮轴发动机控制系统及方法
公开(公告)号：US08459038B1
公开(公告)日：2013-06-11
申请号：US13369783
申请日：2012-02-09
申请人： Ray D. Lickfold , Gregg Williams , Robert S. Thompson, Jr.
发明人： Ray D. Lickfold , Gregg Williams , Robert S. Thompson, Jr.
IPC分类号： F02C1/00
CPC分类号： F02C9/28 , F02C3/107 , F02K3/025 , F02K3/04 , F05D2270/05 , F05D2270/101 , F05D2270/301 , F05D2270/303 , Y02T50/671
摘要： A load applied to a low pressure spool of a two-spool turboshaft engine is controlled responsive to inlet pressure and temperature so as to regulate a relationship between the rotational speeds of the low and high pressure spools of the two-spool turboshaft engine so as to provide for operating the low pressure compressor attached to the low pressure spool with sufficient surge margin.
摘要翻译：响应于入口压力和温度来控制施加到双阀芯涡轮轴发动机的低压阀芯的负载，以便调节双阀芯涡轮轴发动机的低压和高压阀芯的转速之间的关系，从而提供以足够的浪涌余量操作连接到低压阀芯的低压压缩机。

3. 发明授权

US08820092B2 Gas turbine engine cooling system and method 有权
标题翻译：燃气轮机发动机冷却系统及方法
公开(公告)号：US08820092B2
公开(公告)日：2014-09-02
申请号：US12937213
申请日：2009-04-09
申请人： Robert S. Thompson, Jr. , Gregg Williams , David W. Jarrell , Curtis E. Lynch , Mark E. Suchezky
发明人： Robert S. Thompson, Jr. , Gregg Williams , David W. Jarrell , Curtis E. Lynch , Mark E. Suchezky
IPC分类号： F02C7/12 , F01D5/18 , F02C7/16 , F02C7/224 , F01D5/08
CPC分类号： F02C7/224 , F01D5/081 , F02C7/16 , F05D2260/205 , Y02T50/676
摘要： Fuel (12) is supplied to a rotatable portion (118) of a gas turbine engine (10) comprising a rotor (24) and at least one blade (26, 26.1) operatively coupled thereto, so as to provide for cooling at least one of the rotor (24) or the at least one blade (26, 26.1) by transforming the fuel (12) to a vapor or gaseous state. The fuel (12) is discharged in a vapor or gaseous state from the rotatable portion (118) directly into a combustion chamber (16) of the gas turbine engine (10).
摘要翻译：燃料（12）被供应到包括转子（24）的燃气涡轮发动机（10）的可旋转部分（118）和与其可操作地耦合的至少一个叶片（26,26.1），以便提供冷却至少一个的转子（24）或至少一个叶片（26,26.1），通过将燃料（12）转化成蒸气或气态。燃料（12）以蒸汽或气态从可旋转部分（118）排放直接进入燃气涡轮发动机（10）的燃烧室（16）。

4. 发明授权

US08545106B2 System and method for isolating a rolling-element bearing 有权
标题翻译：用于隔离滚动体轴承的系统和方法
公开(公告)号：US08545106B2
公开(公告)日：2013-10-01
申请号：US12832702
申请日：2010-07-08
申请人： Craig R. Miller , Robert S. Thompson, Jr.
发明人： Craig R. Miller , Robert S. Thompson, Jr.
IPC分类号： F16C33/66
CPC分类号： F16C33/6659 , F16C19/163 , F16C27/045 , F16C2360/24 , F16F15/0237
摘要： Lubrication fluid is discharged through an axial gap between a outer bearing race and a bearing housing from a cavity bounded in part by a forward surface of the outer bearing race that is axially slideable within the bearing housing so as to provide for changing the axial gap. The pressure in the cavity is automatically controlled responsive to an axial force on outer bearing race by an axial position of the outer bearing race that determines a size of the axial gap, so as to provide for increasing the pressure responsive to increasing axial force over at least a portion of an operating range. The lubrication fluid in the axial gap provides for isolating axial vibrations of the outer bearing race relative to the bearing housing.
摘要翻译：润滑流体通过外轴承座和轴承座之间的轴向间隙从外轴承座的前表面限定的空腔排出，外轴承座的轴向可在轴承壳体内滑动，以便改变轴向间隙。通过外轴承座的轴向位置来响应于外轴承座上的轴向力来自动控制空腔中的压力，该轴承位置确定轴向间隙的尺寸，以便响应于增加的轴向力而增大压力操作范围的至少一部分。轴向间隙中的润滑流体提供了隔离外轴承座相对于轴承座的轴向振动。

5. 发明授权

US06220016B1 Rocket engine cooling system 失效
标题翻译：火箭发动机冷却系统
公开(公告)号：US06220016B1
公开(公告)日：2001-04-24
申请号：US09522817
申请日：2000-03-10
申请人： Guido D. Defever , Robert S. Thompson, Jr.
发明人： Guido D. Defever , Robert S. Thompson, Jr.
IPC分类号： F02K1100
CPC分类号： F02K9/52 , F02K9/48 , F02K9/62 , F02K9/64 , F02K9/66 , F02K9/72 , F05D2240/40
摘要： A rocket engine comprises first and second combustion chambers with respective combustion chamber liners bounding respective annular passages, wherein the first combustion chamber discharges into the second, and the respective annular passages are in fluid communication with one another. A portion of the effluent from the first combustion chamber flows from the first combustion chamber to the second combustion chamber through the respective annular passages via orifices in the respective combustion chamber liners, so as to provide for effusion cooling of a surface of the second combustion chamber. The first combustion chamber preferably operates fuel rich, reducing the temperature of the effusion cooling gases, which may be further cooled by a portion of unburned fuel. A flow restriction such as a turbine between the first and second combustion chambers provides a pressure differential therebetween that induces flow of effusion cooling gases.
摘要翻译：火箭发动机包括第一和第二燃烧室，其中相应的燃烧室衬套限定相应的环形通道，其中第一燃烧室排放到第二燃烧室中，并且相应的环形通道彼此流体连通。来自第一燃烧室的流出物的一部分通过相应的环形通道经由各个燃烧室衬套中的孔从第一燃烧室流到第二燃烧室，以便提供第二燃烧室的表面的积液冷却。第一燃烧室优选地运行富燃料，降低了可以被一部分未燃烧燃料进一步冷却的排出冷却气体的温度。在第一和第二燃烧室之间的诸如涡轮机之类的流量限制件提供了它们之间的压力差，其引起渗出冷却气体的流动。

6. 发明授权

US06269647B1 Rotor system 有权
标题翻译：转子系统
公开(公告)号：US06269647B1
公开(公告)日：2001-08-07
申请号：US09522873
申请日：2000-03-10
申请人： Robert S. Thompson, Jr. , Gregg G. Williams
发明人： Robert S. Thompson, Jr. , Gregg G. Williams
IPC分类号： F02C100
CPC分类号： F02K9/52 , F02K9/48 , F02K9/62 , F02K9/64 , F02K9/66 , F02K9/72 , F05D2240/40
摘要： A rotor system for a rocket engine comprises a first hollow shaft portion and a surrounding annular duct. The interior of the first hollow shaft portion is adapted to receive a first propellant component, and is in fluid communication with a first rotary orifice. The annular duct is adapted to receive a second propellant component, and is in fluid communication with a second rotary orifice located proximate to the first rotary orifice. The rotor system further comprises a third rotary orifice operatively connected to second hollow shaft portion and in fluid communication with the interior of the first hollow shaft portion for discharging a second portion of the first propellant component at second location. The rotary orifices are operatively connected to respective rotary pressure traps that isolate the pressure at the respective rotary orifices from the respective inlet pressures of the respective propellant components.
摘要翻译：用于火箭发动机的转子系统包括第一空心轴部分和周围的环形管道。第一空心轴部分的内部适于接收第一推进剂部件，并且与第一旋转孔流体连通。环形管道适于接收第二推进剂部件，并且与位于第一旋转孔口附近的第二旋转孔流体连通。转子系统还包括可操作地连接到第二空心轴部分并与第一空心轴部分的内部流体连通的第三旋转孔口，用于在第二位置排放第一推进剂部件的第二部分。旋转孔可操作地连接到相应的旋转压力阱，其将相应旋转孔处的压力与相应的推进剂组分的相应入口压力隔离。

7. 发明授权

US06189324B1 Environment control unit for turbine engine 有权
标题翻译：涡轮发动机环境控制单元
公开(公告)号：US06189324B1
公开(公告)日：2001-02-20
申请号：US09412137
申请日：1999-10-05
申请人： Samuel B. Williams , John F. Jones , Robert S. Thompson, Jr.
发明人： Samuel B. Williams , John F. Jones , Robert S. Thompson, Jr.
IPC分类号： F28B900
CPC分类号： B64D13/06 , B64D41/00 , B64D2013/0644 , Y02T50/56
摘要： An environmental control unit to supply cool dry air to an aircraft cabin has a plurality of bleed air sources from an aircraft engine compressor supplying working fluid to an air cycle cooling circuit. An electronic control computer having a plurality of inputs and selects a bleed air source depending upon cabin cooling and pressurization requirements. A speed control valve responsive to an output from the control computer, modulates the flow of working fluid through a turbo-alternator, thereby synchronizing the frequency of electrical power produced by the turbo-alternator with that of an aircraft engine alternator. The turbo-alternator supplies additional electrical power to the aircraft, thereby minimizing the deleterious effect of warm air bled from the engine compressor on aircraft performance.
摘要翻译：向飞机机舱供应冷却干燥空气的环境控制单元具有多个来自飞行器发动机压缩机的排出空气源，其向工作流体供应空气循环冷却回路。一种具有多个输入并根据机舱冷却和加压要求选择放气源的电子控制计算机。响应于来自控制计算机的输出的速度控制阀，调制通过涡轮交流发电机的工作流体的流动，从而使由涡轮交流发电机产生的电功率与飞机发动机交流发电机的频率同步。涡轮发电机为飞机提供额外的电力，从而最小化从发动机压缩机排出的热空气对航空器性能的有害影响。

8. 发明授权

US06205770B1 Rocket engine 有权
标题翻译：火箭发动机
公开(公告)号：US06205770B1
公开(公告)日：2001-03-27
申请号：US09522871
申请日：2000-03-10
申请人： Gregg G. Williams , Robert S. Thompson, Jr. , Richard D. Stephens , Dean S. Musgrave , John F. Jones , Guido D. Defever
发明人： Gregg G. Williams , Robert S. Thompson, Jr. , Richard D. Stephens , Dean S. Musgrave , John F. Jones , Guido D. Defever
IPC分类号： F02K948
CPC分类号： F02K9/52 , F02K9/48 , F02K9/62 , F02K9/64 , F02K9/66 , F02K9/72 , F05D2240/40
摘要： A rocket engine comprises first and second rotary injectors for injecting respective fuel and oxidizer propellant components into a first combustion chamber, and the effluent therefrom drives a turbine that rotates the rotary injectors. The mixture within the first combustion chamber is preferably fuel-rich so as to reduce the associated combustion temperature, and the fuel-rich effluent mixes in a second combustion chamber with additional oxidizer injected by a third rotary injector so as to generate a high temperature effluent suitable for propulsion. The rotary injectors are adapted so as to isolate the low pressure propellant supply from the relatively high pressures in the respective combustion chambers.
摘要翻译：火箭发动机包括用于将相应的燃料和氧化剂推进剂组分喷射到第一燃烧室中的第一和第二旋转喷射器，并且其流出物驱动旋转旋转喷射器的涡轮机。第一燃烧室内的混合物优选为富燃料，以便降低相关的燃烧温度，并且富含燃料的流出物在第二燃烧室中与另外的由第三旋转喷射器注入的氧化剂混合，从而产生高温流出物适合推进。旋转喷射器适于将低压推进剂供应与相应燃烧室中的较高压力隔离。

9. 发明授权

US5687563A Multi-spool turbofan engine with turbine bleed 失效
标题翻译：多涡轮风扇发动机带涡轮流失
公开(公告)号：US5687563A
公开(公告)日：1997-11-18
申请号：US589649
申请日：1996-01-22
申请人： Robert S. Thompson, Jr.
发明人： Robert S. Thompson, Jr.
IPC分类号： F02K3/06 , F02C3/13 , F02K3/075 , F02K3/077 , F02C9/18
CPC分类号： F02K3/075 , F02C3/13 , F02K3/077 , F05D2220/50 , Y02T50/671
摘要： A multi-spool turbofan engine has a plurality of circumferentially spaced poppet valves with diverters secured thereto for precisely controlling bleed of combustion gas aft of the high pressure turbine whereby the high pressure spool operates at high idle RPM so as to power accessories and the low pressure spool operates at low RPM so as to minimize noise and fuel consumption.
摘要翻译：多卷轴涡轮风扇发动机具有多个周向间隔开的提升阀，其具有固定到其上的转向器，用于精确地控制高压涡轮机的燃烧气体尾部的流出，由此高压阀芯在高空转RPM下运行，以便为附件提供动力和低压阀芯以低RPM运行，以最小化噪音和燃料消耗。

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