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1. 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。

2. 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。

3. 发明授权

US4467599A Turboran speed limiting control system 失效
标题翻译： Turboran限速控制系统
公开(公告)号：US4467599A
公开(公告)日：1984-08-28
申请号：US334552
申请日：1981-12-28
申请人： M. Samuel Moore
发明人： M. Samuel Moore
IPC分类号： F02C7/047 , F02C9/28
CPC分类号： F02C7/047 , F02C9/28 , F05D2270/02
摘要： The maximum speed of a turbofan engine varies in accordance with moderately complex relationships involving the temperature, the pressure or altitude, and whether or not the subordinate systems such as the anti-ice systems are operative. The maximum allowable rotational speed for the fan section of a turbofan engine increases with increased altitude or reduced pressure, and normally increases as the ambient temperature increases up to speeds limited by the centrifugal and other forces acting on the turbine blades. However, there is a maximum fan rotational speed above which the engine should not be operated, and there is a limit which decreases with increasing temperature above which the fan should not be operated regardless of the pressure. In addition, when the anti-ice or other subordinate systems are operative, these limits are reduced substantially. The present invention involves the electronic determination of the normal linear relationship of fan speed with temperature at a fixed pressure or at a series of fixed pressures, a determination of the maximum fan speed limit for each temperature, in terms of a function having a negative slope with increasing pressure, an electronic circuit arrangement for shifting from one characteristic to the other to avoid damage to the turbofan engine by running it at above-specification rotational speed; and also includes switching arrangements for changing operational limits upon operation of the de-icing or similar equipment.
摘要翻译：涡轮风扇发动机的最大速度根据涉及温度，压力或高度的适度复杂的关系，以及诸如防冰系统等下属系统是否可操作而变化。涡轮风扇发动机的风扇部分的最大允许转速随着高度或降低的压力而增加，并且通常随着环境温度升高到由作用在涡轮机叶片上的离心力和其他力限制的速度而增加。然而，有一个最大的风扇转速，发动机不应该在其上运行，并且有一个极限，随着温度的升高而降低，不管压力如何，风扇不应该被运行。此外，当防冰或其他下属系统可操作时，这些限制大大降低。本发明涉及电风扇速度与固定压力或一系列固定压力下的温度的正常线性关系的电子确定，根据具有负斜率的功能确定每个温度的最大风扇速度极限随着压力的增加，电子电路装置从一个特性转移到另一个特征，以避免通过以高于规定的转速运行来损害涡轮风扇发动机; 并且还包括用于在除冰或类似设备的操作时改变操作限制的切换装置。

4. 发明授权

US4698454A Lightweight thermocouple assembly 失效
标题翻译：轻巧的热电偶组件
公开(公告)号：US4698454A
公开(公告)日：1987-10-06
申请号：US646822
申请日：1984-09-04
申请人： M. Samuel Moore
发明人： M. Samuel Moore
IPC分类号： G01K1/16 , G01K7/02 , G01K7/04 , H01L35/02
CPC分类号： G01K7/04 , G01K1/16 , G01K7/023
摘要： A thermocouple system has been nicknamed the "Binocular" thermocouple assembly because the terminal housing has a configuration similar to a pair of binoculars, with the chromel and alumel terminals mounted in spaced circular openings in the terminal housing. A thermocouple probe extends outwardly from the terminal housing, and is provided with two peripheral grooves, into one of which the terminal housing is secured by swaging. The second groove in the thermocouple probe is spaced away from the terminal housing by a short distance along the probe, and a washer is securely swaged into this second groove. A nut having external threads is mounted between the terminal housing and the washer for securing the thermocouple probe to its sensing location, for example, mounted adjacent a turbine engine. The probe has a relatively thick outer wall for most of its length for high strength under adverse mechanical and temperature conditions, and has a relatively thin wall near its end, for fast response to temperature changes, with the two sections being interconnected by a tapered transition section. The thermocouple wires are insulated from the inner walls of the probe by compressing high temperature particulate material; and similarly, the terminals are mounted within the openings in the terminal housing by fuse bonded ceramic or refractory materials and glasses which bond to both the stainless steel terminal housing and also to the chromel and alumel terminals.
摘要翻译：热电偶系统被称为“双目”热电偶组件，因为端子壳体具有类似于一对双筒望远镜的构造，其中铬和铝电极端子安装在端子壳体中的间隔开的圆形开口中。热电偶探头从端子壳体向外延伸，并且设置有两个外围凹槽，其中一个通过锻造固定住端子壳体。热电偶探针中的第二个凹槽沿着探头与端子壳体间隔一段很短的距离，垫圈牢固地铆接到第二个凹槽中。具有外螺纹的螺母安装在端子壳体和垫圈之间，用于将热电偶探头固定到其感测位置，例如安装在涡轮发动机附近。在不利的机械和温度条件下，探针的大部分长度具有较高的强度，并且在其端部附近具有较薄的壁，用于快速响应温度变化，两个部分通过锥形过渡相互连接部分。热电偶线通过压缩高温颗粒材料与探头的内壁绝缘; 并且类似地，端子通过熔接的陶瓷或难熔材料和玻璃安装在端子壳体的开口内，该玻璃或玻璃结合到不锈钢端子壳体以及粘结到铬铁和铝电极端子。

5. 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。

6. 发明授权

US4502043A Engine temperature transient compensating circuit 失效
标题翻译：发动机温度瞬变补偿电路
公开(公告)号：US4502043A
公开(公告)日：1985-02-26
申请号：US357587
申请日：1982-03-12
申请人： M. Samuel Moore
发明人： M. Samuel Moore
IPC分类号： F01D17/08 , G01K3/00 , G01M15/00
CPC分类号： G01K3/005 , F01D17/085
摘要： A turbine engine may occasionally be required to operate momentarily at an overtemperature condition which, provided it does not exceed a predetermined maximum temperature and time duration, is known to be harmless. A temperature read-out device attached to an engine operating under such conditions would measure this harmless overtemperature transient, indicate an overtemperature state, and display a warning. The circuitry of the present invention monitors a signal representing engine temperature, and beginning at the start of the harmless overtemperature transient, and generates an opposing compensating signal for a predetermined period of time. The opposing compensating signal is combined with the signal representing engine temperature and the resultant signal, is applied to the temperature readout device so that the signal representing engine temperature is reduced below the level which would cause an overtemperature condition to be indicated on the temperature readout device.
摘要翻译：偶尔需要涡轮发动机在超温条件下暂时操作，只要其不超过预定的最高温度和持续时间，已知是无害的。连接到在这种条件下运行的发动机的温度读出装置将测量这种无害的过热瞬态，指示过热状态，并显示警告。本发明的电路监视表示发动机温度的信号，并且在无害过热瞬变开始时开始，并且在预定的时间段内产生相对的补偿信号。将相对的补偿信号与表示发动机温度和所得到的信号的信号组合，被施加到温度读出装置，使得表示发动机温度的信号降低到低于在温度读出装置上指示过热状态的水平。

7. 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。

8. 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。

9. 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。

10. 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。

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