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1. 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。

2. 发明授权

US4597259A Pressure responsive engine control system 失效
标题翻译：压力响应发动机控制系统
公开(公告)号：US4597259A
公开(公告)日：1986-07-01
申请号：US608400
申请日：1984-05-09
申请人： M. Samuel Moore , Charles F. Paluka
发明人： M. Samuel Moore , Charles F. Paluka
IPC分类号： F01D17/08 , F01D17/24 , F02C7/262 , F02C9/28
CPC分类号： F01D17/08 , F01D17/24 , F02C7/262 , F02C9/28 , F05D2270/301
摘要： A control system for a jet or turbine aircraft includes a electrical pressure sensor of the type which does not include interconnected mechanical linkages, such as capacitive transducers, and which are therefore stable over a wide range of temperature and other adverse conditions. The pressure sensor is coupled to detect the pressure resulting from the operation of the aircraft engine. The system detects departures from normal operating conditions, such as a flameout of the aircraft engine, and restores the aircraft engine to normal operating conditions by reignition, by operating the starter motor, or other similar steps. Controllable hysteresis may be introduced into the system to determine both the pressure at which the control action is initiated and a different pressure where it is stopped. The system may operate in conjunction with pressure metering and other aircraft systems without hysteresis.
摘要翻译：用于喷气式或涡轮式飞行器的控制系统包括不包括互连机械联动装置的类型的电压传感器，例如电容换能器，因此在宽范围的温度和其它不利条件下它们是稳定的。压力传感器被联接以检测由飞行器发动机的操作产生的压力。该系统检测到诸如飞机发动机的熄火等正常工作条件的偏离，并且通过重新点火，通过操作起动马达或其它类似的步骤将飞机发动机恢复到正常操作条件。可控制的滞后可以被引入到系统中以确定控制动作的起始压力和停止控制动作的不同压力。该系统可以与压力计量和其他飞行器系统一起运行而没有滞后。

3. 发明授权

US4573806A Thermocouple isolation block system 失效
标题翻译：热电偶隔离块系统
公开(公告)号：US4573806A
公开(公告)日：1986-03-04
申请号：US729544
申请日：1985-05-02
申请人： M. Samuel Moore , Charles F. Paluka
发明人： M. Samuel Moore , Charles F. Paluka
IPC分类号： G01K7/02 , G01K1/08 , G01K1/14
CPC分类号： G01K7/023
摘要： An aircraft engine which may, for example, be a turbine engine, is provided with an engine temperature thermocouple harness for monitoring the temperature of the aircraft engine. A protective isolation assembly allows for the use of two separate aircraft circuits coupled to receive temperature indicating signals from the thermocouple system. The protective assembly includes two resistors sealed in a metal housing to be connected at the branch point from the existing aircraft temperature monitoring system; and the housing for the protective assembly is electrically and mechanically connected in direct proximity to the thermocouple harness output terminal housing. A short circuit of the second engine temperature monitor circuit would have negligible effect on the existing temperature indicator circuitry in view of the presence of the isolation block assembly.
摘要翻译：可以例如是涡轮发动机的飞机发动机设置有用于监测飞行器发动机的温度的发动机温度热电偶线束。保护隔离组件允许使用耦合以接收来自热电偶系统的温度指示信号的两个单独的飞行器电路。保护组件包括密封在金属外壳中的两个电阻器，以在现有飞机温度监控系统的分支点处连接; 并且用于保护组件的壳体在电气和机械连接处直接接近热电偶线束输出端子壳体。考虑到隔离块组件的存在，第二发动机温度监控电路的短路对现有的温度指示器电路将具有可忽略的影响。

4. 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。

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

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。

7. 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。

8. 发明授权

US4116052A Jet engine test set 失效
标题翻译：喷气发动机试验台
公开(公告)号：US4116052A
公开(公告)日：1978-09-26
申请号：US834277
申请日：1977-09-19
申请人： Charles F. Paluka
发明人： Charles F. Paluka
IPC分类号： G01M15/00 , G01M15/05
CPC分类号： G01M15/05 , G01M15/00
摘要： The present test apparatus is connected to a jet engine to perform a large number of tests of the mode of operation of the jet engine on both a static and dynamic basis. The multifunctional tester includes four sets of numerical displays on the face of the instrument. The first of these displays shows a sequence number and represents the specific test sequence which is being undertaken by the test apparatus at a particular time. An advance switch is provided to advance to the desired test sequence; and the initiate switch which starts the displayed test sequence. Both the advance switch and the initiate switch have indicator lights associated with them indicating that the test apparatus is ready either to have the sequence advanced, or to initiate a test represented by the sequence number. Input switches are also provided on the face of the test instrument for entering the trim RPM for the particular jet engine under test. Inputs to the multifunctional test apparatus include various jet engine temperatures, jet engine rotational speeds, the guide vane angle, and certain fuel limiting amplifier parameters. Predetermined limits for the test results for various static and dynamic tests are stored in the test apparatus, and when the test results do not fall within the limits, the display with the test results which are out of limits, is flashed.
摘要翻译：本测试装置连接到喷气发动机，以在静态和动态的基础上执行喷气发动机的操作模式的大量测试。该多功能测试仪包括仪器表面四组数字显示。这些显示器中的第一个显示序列号并且表示在特定时间由测试装置进行的特定测试序列。提供一个提前开关以提前到所需的测试顺序; 以及启动显示的测试序列的启动开关。提前开关和启动开关都具有与它们相关联的指示灯，指示测试装置准备好使序列前进，或者启动由序列号表示的测试。输入开关也设在测试仪器的表面，用于进入被测试的特定喷气发动机的调整RPM。多功能测试装置的输入包括各种喷气发动机温度，喷气发动机转速，导向叶片角度以及某些燃料限制放大器参数。各种静态和动态测试的测试结果的预定限制存储在测试设备中，当测试结果不在限制范围内时，闪烁测试结果超出显示范围。

9. 发明授权

US3931619A Overtemperature monitor and integrator apparatus 失效
标题翻译：超温监视器和积分器
公开(公告)号：US3931619A
公开(公告)日：1976-01-06
申请号：US313429
申请日：1972-12-08
申请人： Manuel S. Moore , Charles F. Paluka
发明人： Manuel S. Moore , Charles F. Paluka
IPC分类号： F01D21/00 , G01K3/00 , G01K3/04 , G08B21/18 , G08B23/00
CPC分类号： G01K3/04 , F01D21/003 , G01K3/005 , G08B21/182
摘要： Temperature is sensed in equipment where life is reduced by overtemperature. The sensed temperature is compared to a set point and an output indication showing overtemperature operation is provided to the equipment operator. In addition, a signal is produced which is proportional to the sensed temperature above a reference or threshold value. This signal is passed through a coulomb meter which indicates the total charge. This charge is an integration of the product of the time of duration and the amount of overtemperature, for indicating the accumulated thermal stesses.
摘要翻译：在通过过热降低生命的设备中检测到温度。将感测到的温度与设定点进行比较，并向设备操作者提供显示过热操作的输出指示。此外，产生与感测到的温度成比例高于参考值或阈值的信号。该信号通过表示总电荷的库仑计。该充电是指持续时间和过热量的积分，用于指示累积的热量。

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