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1. 发明授权

US4468924A Turbine engine power optimization control system 失效
标题翻译：涡轮发动机功率优化控制系统
公开(公告)号：US4468924A
公开(公告)日：1984-09-04
申请号：US422863
申请日：1982-09-24
申请人： M. Samuel Moore
发明人： M. Samuel Moore
IPC分类号： F02C9/28 , F02C9/44
CPC分类号： F02C9/44 , F02C9/28 , F05D2270/02
摘要： Pushbutton controls are provided for the power management of a turbine powered aircraft; and these pushbuttons may be mounted on the aircraft pilot's control handwheel. The turbine engine has a maximum rated permissible rotational speed which initially increases with increasing air temperature and with increasing altitude or reduced pressure; and has an absolute maximum limitation, with this maximum permissible rotational speed decreasing at increasing temperatures starting at about 10 or 15 degrees below zero, centigrade; and these limitations are reduced when supplemental equipment such as de-icing equipment is turned on. In accordance with the present invention, a series of "maps", or rotational speed control characteristics reflecting the factors mentioned above, are provided, and the pushbutton controls select among these characteristics, with the "take-off" power button permitting the highest maximum speeds, etc. In addition, automatic timing to reduce the maximum power levels, such as "Take-Off" power or "Performance Climb" power, is provided, to avoid over-stressing the turbine engines. The system may include additional arrangements for limiting the maximum allowable rotational speed of the turbine engine to a speed below that indicated by any of the "maps", when certain pushbuttons such as the "Approach" pushbutton is actuated.
摘要翻译：提供按钮控制，用于涡轮动力飞机的电源管理; 并且这些按钮可以安装在飞行员飞行员的控制手轮上。涡轮发动机具有最大额定允许转速，其最初随着空气温度升高并且随着高度或降低的压力而增加; 并且具有绝对的最大限制，在最高允许转速下降时，起升温度在零下10度或15度以下; 并且当诸如除冰设备的补充设备被打开时，这些限制被减少。根据本发明，提供了一系列反映上述因素的“地图”或转速控制特性，并且按钮控制在这些特性之中选择允许最大最大值的“起飞”电源按钮速度等。此外，提供了降低最大功率水平的自动定时，例如“起飞”功率或“性能爬升”功率，以避免涡轮发动机的过度应力。当诸如“接近”按钮的某些按钮被致动时，该系统可以包括用于将涡轮发动机的最大允许转速限制到低于任何“地图”所指示的速度的附加装置。

2. 发明授权

US4428199A Turbocharger control system 失效
标题翻译：涡轮增压器控制系统
公开(公告)号：US4428199A
公开(公告)日：1984-01-31
申请号：US289472
申请日：1981-08-03
申请人： M. Samuel Moore , Charles F. Paluka
发明人： M. Samuel Moore , Charles F. Paluka
IPC分类号： F02B3/06 , F02B37/00 , F02B37/007 , F02B37/12 , F02B37/24 , F02C9/16
CPC分类号： F02B37/24 , F02B37/00 , F02B37/007 , F02B37/12 , F02C9/16 , F01N13/107 , F02B3/06 , Y02T10/144
摘要： A diesel engine which may, for example, be a V-12 engine, is provided with a turbocharger having two sections, a turbine section which receives exhaust gases and which drives the associated compressor section. The turbocharger increases the input air pressure to the input manifold of the diesel engine up to several times atmospheric pressure. Both the turbine section and the compressor section of the turbocharger have adjustable vanes to vary the coupling with the exhaust gases, in the case of the turbine section, and with respect to the input air in the case of the compressor. An associated control circuit senses the temperature at the inlet to the turbine (the engine exhaust temperature), the speed of the engine, and the engine inlet manifold pressure, and adjusts the orientation of the turbine and compressor vanes for optimal engine performance for all engine speeds, while avoiding cavitation or "stall" conditions in the compressor.
摘要翻译：例如可以是V-12发动机的柴油发动机设置有具有两个部分的涡轮增压器，涡轮部分接收废气并驱动相关联的压缩机部分。涡轮增压器将输入空气压力增加到柴油发动机的输入歧管，达到大气压力的几倍。涡轮机部分和涡轮增压器的压缩机部分都具有可调叶片，以在涡轮部分的情况下改变与排气的联接，并且在压缩机的情况下相对于输入空气。相关的控制电路检测涡轮入口处的温度（发动机排气温度），发动机速度和发动机进气歧管压力，并调整涡轮机和压缩机叶片的方向，以获得所有发动机的最佳发动机性能同时避免压缩机中的气蚀或“失速”情况。

3. 发明授权

US4292806A Turbocharger control system 失效
标题翻译：涡轮增压器控制系统
公开(公告)号：US4292806A
公开(公告)日：1981-10-06
申请号：US15956
申请日：1979-02-28
申请人： M. Samuel Moore , Charles F. Paluka
发明人： M. Samuel Moore , Charles F. Paluka
IPC分类号： F02B3/06 , F02B37/00 , F02B37/007 , F02B37/12 , F02B37/24 , F02C9/16
CPC分类号： F02C9/16 , F02B37/00 , F02B37/007 , F02B37/12 , F02B37/24 , F01N13/107 , F02B3/06 , Y02T10/144
摘要： A diesel engine which may, for example, be a V-12 engine, is provided with a turbocharger having two sections, a turbine section which receives exhaust gases and which drives the associated compressor section. The turbocharger increases the input air pressure to the input manifold of the diesel engine up to several times atmospheric pressure. Both the turbine section and the compressor section of the turbocharger have adjustable vanes to vary the coupling with the exhaust gases, in the case of the turbine section, and with respect to the input air in the case of the compressor. An associated control circuit senses the temperature at the inlet to the turbine (the engine exhaust temperature), the speed of the engine, and the engine inlet manifold pressure, and adjusts the orientation of the turbine and compressor vanes for optimal engine performance, while avoiding cavitation or "stall" conditions in the compressor.
摘要翻译：例如可以是V-12发动机的柴油发动机设置有具有两个部分的涡轮增压器，涡轮部分接收废气并驱动相关联的压缩机部分。涡轮增压器将输入空气压力增加到柴油发动机的输入歧管，达到大气压力的几倍。涡轮机部分和涡轮增压器的压缩机部分都具有可调叶片，以在涡轮部分的情况下改变与排气的联接，并且在压缩机的情况下相对于输入空气。相关的控制电路检测涡轮入口处的温度（发动机排气温度），发动机速度和发动机进气歧管压力，并调整涡轮机和压缩机叶片的方向以获得最佳的发动机性能，同时避免压缩机中的气蚀或“失速”状况。

4. 发明授权

US4787053A Comprehensive engine monitor and recorder 失效
标题翻译：综合引擎监控和录像机
公开(公告)号：US4787053A
公开(公告)日：1988-11-22
申请号：US784724
申请日：1985-10-04
申请人： M. Samuel Moore
发明人： M. Samuel Moore
IPC分类号： F01D21/00 , F02C9/00 , G01D21/02 , G01K1/02 , G05B23/02 , G06F17/40 , G07C3/00 , G11B5/02 , G01M15/00
CPC分类号： F01D21/00 , F02C9/00 , G01D21/02 , G01K1/02 , G07C3/00
摘要： A comprehensive turbine engine monitoring and recording system includes an electronics unit which may be engine mounted, and which contains at least a nonvolatile memory and a data-processor, for use with a remote unit suitable for either cockpit mounting or for accessing by a ground portable unit which may include an additional data-processor and display and/or printer units. Raw input data is supplied to the electronics unit, and this input information may include engine and outside air temperature, torque, engine speed, vibration, altitude and airspeed data, for examples. Exceedance data relative to the operation of the aircraft above pre-defined limits of temperature, torque and speed are recorded, with the details of each exceedance being permanently stored. In addition, over-limits levels are segregated and the total time during which the engine is operated within each of the over-limits bands is measured, and is recorded in a non-volatile, electronically alterable memory which is periodically updated during operation of the aircraft. The number of starts, and power cycles are also counted and stored, and the total running time of the engine is also recorded. Upon command from the remote unit, information is transferred from the non-volatile memory to any of a number of remote data storage, or data processing units, which may include printer and/or display units, so that the time at which the turbine has been operated at specific over-temperature levels, and other important operating data may be readily accessed. Data required for engine trend monitoring is also automatically recorded so that long term plots and interpretation of engine degradation may be accomplished.
摘要翻译：综合的涡轮发动机监测和记录系统包括可以引擎安装的电子单元，并且至少包含非易失性存储器和数据处理器，用于与适用于驾驶舱安装或通过便携式地面接入的远程单元单元，其可以包括附加的数据处理器和显示器和/或打印机单元。原始输入数据被提供给电子单元，并且该输入信息可以包括发动机和外部空气温度，扭矩，发动机速度，振动，高度和空速数据。记录相对于飞机运行超出预定温度，扭矩和速度限制的数据，每个超出的细节被永久存储。此外，测量超限水平，并且测量在每个超限频带内发动机运行的总时间，并且被记录在非易失性电子可变存储器中，该存储器在操作期间被周期性地更新飞机。还计数和存储启动次数和功率循环，并记录发动机的总运行时间。根据来自远程单元的命令，信息从非易失性存储器传送到可包括打印机和/或显示单元的多个远程数据存储器或数据处理单元中的任何一个，使得涡轮机具有的时间在特定的过温水平下运行，并且可以容易地访问其他重要的操作数据。还会自动记录发动机趋势监测所需的数据，以便可以实现发动机退化的长期图解和解释。

5. 发明授权

US4763285A Helicopter low-g monitor, recorder and warning system 失效
标题翻译：直升机低压监视器，录像机和警告系统
公开(公告)号：US4763285A
公开(公告)日：1988-08-09
申请号：US897994
申请日：1986-08-19
申请人： M. Samuel Moore , Charles F. Paluka
发明人： M. Samuel Moore , Charles F. Paluka
IPC分类号： F02C9/00 , G01D21/02 , G07C3/00 , G06G7/48 , G01C21/00 , G08B23/00
CPC分类号： G07C3/00 , F02C9/00 , G01D21/02
摘要： When helicopters are accomplishing certain special maneuvers such as powered descent, or the like involving low "g" conditions, the helicopter blades may teeter excessively with respect to the mast, and under severe conditions, the mast may shear. To sense such low "g" conditions, which may be dangerous, an accelerometer is mounted on the helicopter frame close to the center of gravity of the helicopter and is coupled to data processing circuitry which classifies the low-g conditions in bands or levels of severity, recording the duration of exceedances in which the low-g conditions are below predetermined levels, and issues warning signals to the helicopter pilot through the helicopter intercom system and a suitable warning light.
摘要翻译：当直升机正在实现诸如涉及低“g”条件的诸如动力下降等的某些特殊操作时，直升机叶片可能相对于桅杆过度地踩踏，并且在恶劣的条件下，桅杆可能会剪切。为了感测这种可能是危险的低“g”条件，加速度计被安装在靠近直升机重心的直升机机架上，并被耦合到数据处理电路，该数据处理电路将低g条件在频带或级别记录低g条件低于预定水平的超时时间，并通过直升机对讲系统和适当的警示灯向直升机飞行员发出警告信号。

6. 发明授权

US4619110A Helicopter engine warning or control system 失效
标题翻译：直升机发动机警告或控制系统
公开(公告)号：US4619110A
公开(公告)日：1986-10-28
申请号：US729547
申请日：1985-05-02
申请人： M. Samuel Moore
发明人： M. Samuel Moore
IPC分类号： F02C9/28
CPC分类号： F02C9/28 , F05D2220/329 , F05D2270/09
摘要： A helicopter turbine engine over-stress warning and protection system includes arrangements for sensing the engine temperature, the engine speed, and the output torque from the engine. An audible signal warning is provided which may vary as the over-stress limits are approached. For example, when the helicopter engine is at or above the over-stress limits, it may have a constant fairly loud tone into the pilot's earphones or into a speaker in the cockpit. This warning tone signal becomes interrupted and provides progressively greater periods of silence as the helicopter engine drops below the over-stress limits. The warning signal stops at a pre-set point such as, for example, when the engine is being operated from 5% to 15% below the over-stress limits. Dynamic response control circuits are provided to avoid false actuation of the alarm system; automatic limitation of the fuel flow to the engine may be provided in combination with a conveniently located override actuator; and arrangements may also be provided for automatically injecting water or alcohol into the engine as over-stress conditions are approached.
摘要翻译：直升机涡轮发动机过应力警告和保护系统包括用于感测发动机温度，发动机转速和来自发动机的输出转矩的装置。提供可听见的信号警告，其可以随着接近过应力极限而变化。例如，当直升机发动机处于或超过过应力极限时，它可能对飞行员的耳机或驾驶舱中的扬声器具有恒定的相当大的音调。当直升机发动机降到超过应力极限以下时，这个警告音信号就会中断，并提供更多的沉默时间。警告信号在预设点停止，例如当发动机从超过应力极限的5％到15％的运行时停止。提供动态响应控制电路以避免报警系统的误动作; 燃料流向发动机的自动限制可以与方便定位的超控致动器组合提供; 并且还可以提供用于在接近过压条件时将水或酒精自动注入发动机的装置。

7. 发明授权

US4460225A Thermocouple wiring harness and connector system 失效
标题翻译：热电偶线束和连接器系统
公开(公告)号：US4460225A
公开(公告)日：1984-07-17
申请号：US330832
申请日：1981-12-15
申请人： M. Samuel Moore , Aramais Harootion
发明人： M. Samuel Moore , Aramais Harootion
IPC分类号： G01K7/02 , H01R13/22
CPC分类号： H01R13/22 , G01K7/023
摘要： A high temperature thermocouple wiring harness and connector system incorporating multiple individual thermocouple probes replaceably attached through connectors to the wiring harness. Each connector has a wiring harness portion, a removable probe portion, and a fastener for holding the two portions together. The wiring harness portion has a housing and two electrical conductors connected to the cable of the wiring harness and having contact surfaces outside the housing. The removable probe portion has a similar housing, a thermocouple probe mounted on the housing, and two electrical conductors attached to the thermocouple and having contact surfaces outside the housing. The fastener retains the connector portions together and insures that the contact surfaces of the conductors are held together. The fastener is formed of a material that has a coefficient of thermal expansion less than the coefficient of thermal expansion of the connector portions. As the ambient temperature surrounding the connector increases, the lower relative coefficient of thermal expansion of the fastener in relation to the connector portion causes the conductors to be held together with increasing force.
摘要翻译：一个高温热电偶线束和连接器系统，结合了多个单独的热电偶探头，通过连接器可替换地连接到线束。每个连接器具有线束部分，可移除的探针部分和用于将两个部分保持在一起的紧固件。线束部分具有壳体和连接到线束的电缆的两个电导体并且具有在壳体外部的接触表面。可拆卸的探针部分具有类似的壳体，安装在壳体上的热电偶探针和连接到热电偶并且在壳体外部具有接触表面的两个电导体。紧固件将连接器部分保持在一起并确保导体的接触表面保持在一起。紧固件由具有小于连接器部分的热膨胀系数的热膨胀系数的材料形成。随着连接器周围的环境温度升高，紧固件相对于连接器部分的较低的相对热膨胀系数使导体以增加的力保持在一起。

8. 发明授权

US4185460A Engine power management system 失效
标题翻译：发动机电源管理系统
公开(公告)号：US4185460A
公开(公告)日：1980-01-29
申请号：US864857
申请日：1977-12-27
申请人： M. Samuel Moore , Charles F. Paluka
发明人： M. Samuel Moore , Charles F. Paluka
IPC分类号： F02C9/42 , F02K3/12 , F02C9/04
CPC分类号： F02C9/42 , Y02T50/671
摘要： An aircraft having two turbine engines is provided with both torque and temperature sensitive electronic circuitry to control the fuel supplied to the turbine engines. Pushbutton switches are provided for the selection of the desired torque level by the pilot. The fuel to either engine is reduced, regardless of output torque and its relationship to the pushbutton values of selected torque, when the engine temperature exceeds a predetermined safety level. Failsafe operation is provided through the use of a main fuel supply path including a manual fuel control valve extending from the fuel pump to the engine fuel nozzles, and a normally closed bypass fuel control line which selectively diverts fuel from the principal path under the control of the temperature and torque responsive electronic circuitry. An electromagnetically operated valve in the bypass line is normally closed and is selectively operated to the desired open condition under the control of the torque and temperature responsive circuitry mentioned above, to reduce fuel supplied to the turbine engines.
摘要翻译：具有两个涡轮发动机的飞机设置有扭矩和温度敏感的电子电路，以控制供应到涡轮发动机的燃料。提供按钮开关用于由飞行员选择所需的扭矩水平。当发动机温度超过预定的安全水平时，不管输出扭矩和其与所选转矩的按钮值的关系如何，对任一发动机的燃料减少。通过使用包括从燃料泵延伸到发动机燃料喷嘴的手动燃料控制阀的主要燃料供给路径以及在主控制路径下选择性地转移燃料的常闭旁路燃料控制线来提供故障保护操作，温度和转矩响应电子电路。旁路管路中的电磁操作阀常闭，并在上述转矩和温度响应电路的控制下选择性地操作到所需的开启状态，以减少供应到涡轮发动机的燃料。

9. 发明授权

US4147035A Engine load sharing control system 失效
标题翻译：发动机负荷共享控制系统
公开(公告)号：US4147035A
公开(公告)日：1979-04-03
申请号：US878304
申请日：1978-02-16
申请人： M. Samuel Moore , Charles F. Paluka
发明人： M. Samuel Moore , Charles F. Paluka
IPC分类号： F02C9/42 , F01B21/02 , F02D25/00
CPC分类号： F02C9/42
摘要： Two turbine engines are connected to a common gear box to drive a common load, such as a helicopter rotor, and circuitry is provided for controlling the two mechanically intercoupled engines in order to provide: (1) individual temperature shutoff for the engines, (2) limitation on the maximum total torque supplied by the two engines to avoid exceeding the power handling capability of the gear box for the associated load, (3) speed control for the engines, and (4) substantially equal sharing of the torque load by the two engines. By suitably combining the signals which require analysis, and supplying a single properly conditioned signal to the fuel control unit of each engine, tight control without oscillation or cycling may be achieved. Notch filtering to avoid reinforcement of mechanical resonances, and a variable response characteristic depending on the magnitude of the error signal may be included in the circuitry. Through the use of the circuitry noted above, and the avoidance of duplicate or conflicting feedback loops, a tighter servo control may be achieved without adverse results such as oscillation or overshoot. The pilot input is both a coarse mechanical input applied to set the fuel control units of both turbine engines to a level above the expected final power output level, and a relatively precise electrical signal which is supplied to the electronic control circuitry which cuts back the fuel supplied by one or both of the fuel control units.
摘要翻译：两个涡轮发动机连接到普通齿轮箱以驱动公共负载，例如直升机转子，并且提供用于控制两个机械相互联接的发动机的电路，以便提供：（1）用于发动机的单独的温度关闭，（2 ）限制两个发动机提供的最大总转矩，以避免超过相关负载的齿轮箱的动力处理能力，（3）发动机的速度控制，以及（4）扭矩负载的大致相等的共享两个引擎。通过适当地组合需要分析的信号，并且向每个发动机的燃料控制单元提供单个适当调节的信号，可以实现无振荡或循环的严格控制。用于避免加强机械共振的陷波滤波以及取决于误差信号幅度的可变响应特性可以包括在电路中。通过使用上述电路，并避免重复或冲突的反馈回路，可以实现更严格的伺服控制，而不会产生不利的结果，例如振荡或过冲。导频输入既是应用于将两个涡轮发动机的燃料控制单元设置到高于预期最终功率输出水平的水平的粗略机械输入，以及提供给电子控制电路的相对精确的电信号，该电信号切断燃料由一个或两个燃料控制单元提供。

10. 发明授权

US4575803A Engine monitor and recorder 失效
标题翻译：发动机监控和记录仪
公开(公告)号：US4575803A
公开(公告)日：1986-03-11
申请号：US335841
申请日：1981-12-30
申请人： M. Samuel Moore
发明人： M. Samuel Moore
IPC分类号： F01D21/00 , G01K1/02 , G05B23/02 , G06F17/40 , G07C3/00 , G01K7/02
CPC分类号： G07C3/00 , F01D21/00 , G01K1/02
摘要： A turbine engine monitoring and recording system includes an engine mounted unit which contains at least a non-volatile memory and a data-processor, and a remote unit suitable for either cockpit mounting or for accessing by a ground portable unit including an additional data-processor and a display unit. Thermocouples and other sensors mounted on the engine supply raw data to the engine mounted electronics unit, and this input information includes temperature data. Elevated over-temperature levels are segregated and the time during which the engine is within each of the over-temperature bands is measured, and is recorded in a non-volatile, electronically alterable memory which is periodically updated during operation of the aircraft. The number of starts is also counted and stored, and the total running time of the engine is also recorded. Upon command from the remote unit, information is transferred from the non-volatile memory to the remote display unit, so that the time at which the turbine has been operated at specific over-temperature levels may be readily accessed.
摘要翻译：涡轮发动机监测和记录系统包括：至少包含非易失性存储器和数据处理器的发动机安装单元，以及适合于驾驶舱安装或由地面便携式单元进行访问的远程单元，其包括附加的数据处理器和显示单元。安装在发动机上的热电偶和其他传感器将原始数据提供给发动机安装的电子单元，并且该输入信息包括温度数据。测量过高温度水平升高，并且测量发动机处于每个超温带内的时间，并记录在飞行器运行期间周期性更新的非易失性电子可变存储器中。还计数和存储启动次数，并记录发动机的总运行时间。根据来自远程单元的命令，信息从非易失性存储器传送到远程显示单元，使得可以容易地访问在特定过温度水平下运行涡轮机的时间。

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