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1. 发明授权

US09500135B2 Fuel feed circuit for an aeroengine having a high pressure pump system with two pumps 有权
标题翻译：具有两个泵的高压泵系统的航空发动机的燃料供给回路
公开(公告)号：US09500135B2
公开(公告)日：2016-11-22
申请号：US13500499
申请日：2010-09-30
申请人： Nicolas Alain Bader , Regis Michel Paul Deldalle , Laurent Gilbert Yves Hodinot , Nicolas Potel
发明人： Nicolas Alain Bader , Regis Michel Paul Deldalle , Laurent Gilbert Yves Hodinot , Nicolas Potel
IPC分类号： F02C7/22 , F02C7/236 , F02C9/36 , F02C9/26 , F02C9/30
CPC分类号： F02C9/263 , F02C7/22 , F02C7/236 , F02C9/26 , F02C9/30 , F02C9/36
摘要： A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system for delivering fuel at high pressure to combustion chamber injectors, the high-pressure pumping system including first and second positive displacement gear pumps driven simultaneously by the engine. A hydraulic switch member is interposed between respective outlets of the pumps, which makes it possible, in one state, to combine outlet flows from the two pumps to deliver fuel at high pressure to the combustion chamber injectors, and in another state, to discharge some or all of outlet flow from the first pump to a low-pressure feed line, an electrical control member serving to cause the hydraulic switch member to pass from one state to the other.
摘要翻译：一种用于航空发动机的燃料供给回路，该回路包括用于将燃料高压地输送到燃烧室喷射器的高压泵送系统，所述高压泵送系统包括由发动机同时驱动的第一和第二正排量齿轮泵。液压开关构件介于泵的相应出口之间，这使得在一个状态下可以组合来自两个泵的出口流将高压燃料输送到燃烧室喷射器，并且在另一种状态下排出一些或从第一泵到低压进料管线的所有出口流量，用于使液压开关构件从一个状态传递到另一个状态的电气控制构件。

2. 发明申请

US20120260658A1 FUEL FEED CIRCUIT FOR AN AEROENGINE 有权
标题翻译：燃油送料电路
公开(公告)号：US20120260658A1
公开(公告)日：2012-10-18
申请号：US13500499
申请日：2010-09-30
申请人： Nicolas Alain Bader , Regis Michel Paul Deldalle , Laurent Gilbert Yves Hodinot , Nicolas Potel
发明人： Nicolas Alain Bader , Regis Michel Paul Deldalle , Laurent Gilbert Yves Hodinot , Nicolas Potel
IPC分类号： F02C7/236
CPC分类号： F02C9/263 , F02C7/22 , F02C7/236 , F02C9/26 , F02C9/30 , F02C9/36
摘要： A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system for delivering fuel at high pressure to combustion chamber injectors, the high-pressure pumping system including first and second positive displacement gear pumps driven simultaneously by the engine. A hydraulic switch member is interposed between respective outlets of the pumps, which makes it possible, in one state, to combine outlet flows from the two pumps to deliver fuel at high pressure to the combustion chamber injectors, and in another state, to discharge some or all of outlet flow from the first pump to a low-pressure feed line, an electrical control member serving to cause the hydraulic switch member to pass from one state to the other.
摘要翻译：一种用于航空发动机的燃料供给回路，该回路包括用于将燃料高压地输送到燃烧室喷射器的高压泵送系统，所述高压泵送系统包括由发动机同时驱动的第一和第二正排量齿轮泵。液压开关构件介于泵的相应出口之间，这使得在一个状态下可以组合来自两个泵的出口流将高压燃料输送到燃烧室喷射器，并且在另一种状态下排出一些或从第一泵到低压进料管线的所有出口流量，用于使液压开关构件从一个状态传递到另一个状态的电气控制构件。

3. 发明申请

US20140023525A1 FUEL CIRCUIT COMPRISING MEANS FOR CONTROLLING A PUMP 审中-公开
标题翻译：包含用于控制泵的装置的燃料电路
公开(公告)号：US20140023525A1
公开(公告)日：2014-01-23
申请号：US14009933
申请日：2012-04-12
申请人： Nicolas Potel , NIcolas Alain Bader
发明人： Nicolas Potel , NIcolas Alain Bader
IPC分类号： F04B23/04
摘要： A turbomachine fuel circuit including: a low pressure pump; a high pressure pump; a low pressure conduit connecting the low pressure pump to the high pressure pump; a high pressure conduit supplied by the high pressure pump, in which a component is arranged; a mechanism for testing operation of the component; a check valve capable of closing off a segment of the conduit when the pressure in the low pressure conduit is less than a predetermined threshold value; and the testing mechanism is capable of detecting that the check valve at least partly closes off the segment.
摘要翻译：一种涡轮机燃料回路，包括：低压泵; 高压泵; 将低压泵连接到高压泵的低压管道; 由高压泵供给的高压导管，其中配置有部件; 用于测试部件运行的机构; 当所述低压管道中的压力小于预定阈值时能够关闭所述管道的一段的止回阀; 并且测试机构能够检测止回阀至少部分地关闭该段。

4. 发明授权

US08443654B2 Device for monitoring the obstruction of at least two filters of a fluid circulation system of an aircraft gas turbine engine 有权
标题翻译：用于监测飞机燃气涡轮发动机的流体循环系统的至少两个过滤器的阻塞的装置
公开(公告)号：US08443654B2
公开(公告)日：2013-05-21
申请号：US13163141
申请日：2011-06-17
申请人： Nicolas Alain Bader , Thierry Poix , Nicolas Potel
发明人： Nicolas Alain Bader , Thierry Poix , Nicolas Potel
IPC分类号： G01M15/14
CPC分类号： B01D37/046 , B01D35/143 , B01D2201/54 , F23K5/06 , F23K5/18 , F23K2301/202 , F23R3/00
摘要： A device monitors an obstruction of two fluid filters of a fluid circulation system of a gas turbine engine of an aircraft. A first obstruction sensor sends a first detection signal of an obstruction of a first filter. A second obstruction sensor sends a second detection signal of an obstruction of a second filter. A processor includes a monitoring input to measure the first and second detection signals. The first obstruction sensor includes a Wheatstone bridge including a strain gauge resistor. The second obstruction sensor is connected in parallel with the strain gauge resistor. The first detection signal is sent over a first predetermined variation range. The second detection signal is sent over a second predetermined variation range, distinct from the first variation range. The processor identifies the obstruction of one of the fluid filters as a function of one of the variation ranges of the detection signals.
摘要翻译：一种装置监测飞机的燃气涡轮发动机的流体循环系统的两个流体过滤器的阻塞。第一阻塞传感器发送第一滤波器的阻塞的第一检测信号。第二阻塞传感器发送第二滤波器的阻塞的第二检测信号。处理器包括用于测量第一和第二检测信号的监视输入。第一阻塞传感器包括惠斯登电桥，其包括应变计电阻器。第二阻塞传感器与应变计电阻并联连接。第一检测信号通过第一预定变化范围发送。第二检测信号在与第一变化范围不同的第二预定变化范围内发送。处理器根据检测信号的变化范围之一来识别流体滤波器之一的阻塞。

5. 发明申请

US20110308306A1 DEVICE FOR MONITORING THE OBSTRUCTION OF AT LEAST TWO FILTERS OF A FLUID CIRCULATION SYSTEM OF AN AIRCRAFT GAS TURBINE ENGINE 有权
标题翻译：用于监测航空器涡轮发动机的流体循环系统的至少两个过滤器的装置
公开(公告)号：US20110308306A1
公开(公告)日：2011-12-22
申请号：US13163141
申请日：2011-06-17
申请人： Nicolas Alain BADER , Thierry Poix , Nicolas Potel
发明人： Nicolas Alain BADER , Thierry Poix , Nicolas Potel
IPC分类号： G01M15/14
CPC分类号： B01D37/046 , B01D35/143 , B01D2201/54 , F23K5/06 , F23K5/18 , F23K2301/202 , F23R3/00
摘要： A device for monitoring the obstruction of at least two fluid filters of a fluid circulation system of a gas turbine engine of an aircraft, the device comprising a first obstruction sensor, intended to monitor a first fluid filter, set up to send a first detection signal of an obstruction of the first filter and a processor comprising a monitoring input linked to said first sensor to measure the first detection signal. The device also comprises a second obstruction sensor, intended to monitor a second fluid filter, set up to send a second detection signal of an obstruction of the second filter, the monitoring input of the processor being connected to the first obstruction sensor to measure said second detection signal over a single monitoring input.
摘要翻译：一种用于监测飞行器的燃气涡轮发动机的流体循环系统的至少两个流体过滤器的阻塞的装置，该装置包括第一阻塞传感器，用于监测第一流体过滤器，其被设置为发送第一检测信号第一滤波器的障碍物和包括与所述第一传感器相关联的监测输入的处理器以测量第一检测信号。该装置还包括第二阻塞传感器，其旨在监测第二流体过滤器，其被设置为发送第二过滤器的障碍物的第二检测信号，所述处理器的监视输入连接到第一阻塞传感器以测量所述第二阻塞传感器检测信号通过单个监控输入。

6. 发明授权

US10513988B2 Fuel circuit comprising means for controlling a pump 有权
公开(公告)号：US10513988B2
公开(公告)日：2019-12-24
申请号：US14009933
申请日：2012-04-12
申请人： Nicolas Potel , Nicolas Alain Bader
发明人： Nicolas Potel , Nicolas Alain Bader
IPC分类号： F02C9/46 , F02C7/236 , F02C7/232 , F04B23/04
摘要： A turbomachine fuel circuit including: a low pressure pump; a high pressure pump; a low pressure conduit connecting the low pressure pump to the high pressure pump; a high pressure conduit supplied by the high pressure pump, in which a component is arranged; a mechanism for testing operation of the component; a check valve capable of closing off a segment of the conduit when the pressure in the low pressure conduit is less than a predetermined threshold value; and the testing mechanism is capable of detecting that the check valve at least partly closes off the segment.

7. 发明授权

US09309882B2 Method of determining whether to replace a high pressure pump in a hydraulic regulation system of a turbomachine 有权
标题翻译：确定是否更换涡轮机液压调节系统中的高压泵的方法
公开(公告)号：US09309882B2
公开(公告)日：2016-04-12
申请号：US14344777
申请日：2012-08-13
申请人： Nicolas Potel , Nicolas Gomes
发明人： Nicolas Potel , Nicolas Gomes
IPC分类号： F04B51/00 , F04D29/56 , G01D5/22 , G01M15/14 , F04D27/00
CPC分类号： F04B51/00 , F04D27/001 , F04D29/563 , G01D5/2291 , G01M15/14
摘要： A method tracking positive displacement efficiency of a high pressure positive displacement pump in a hydraulic regulator system of a turbomachine delivering a flow rate based on an engine speed of the turbomachine, the flow rate delivered to an actuator actuating variable geometry vanes of the turbomachine and to a bypass valve feeding engines of the turbomachine, the method including: starting engines of the turbomachine at a low engine speed, the valve being closed; using a computer to order a movement of the actuator; progressively increasing the engine speed until the flow rate reaches a predetermined value sufficient for opening the valve; storing in the computer a position of the actuator and the engine speed corresponding to opening of the valve; repeating the preceding operations at successive instants during a lifetime of the engines; and replacing the high pressure positive displacement pump when the engine speed exceeds a predetermined value.
摘要翻译：一种跟踪涡轮机械的液压调节器系统中的高压正排量泵的正排量效率的方法，其基于涡轮机的发动机转速传递流量，将流量输送到致动器，该致动器致动涡轮机的可变几何叶片，并且所述涡轮机的旁通阀供给发动机，所述方法包括：以低发动机转速启动所述涡轮机的发动机，所述阀关闭; 使用计算机来命令致动器的运动; 逐渐增加发动机转速，直到流量达到足以打开阀门的预定值; 在计算机中存储致动器的位置和对应于阀的打开的发动机速度; 在发动机寿命期间的连续时刻重复上述操作; 并且当发动机转速超过预定值时更换高压容积式泵。

8. 发明申请

US20130283811A1 FUEL CIRCUIT FOR AN AVIATION TURBINE ENGINE, THE CIRCUIT HAVING A FUEL PRESSURE REGULATOR VALVE 有权
标题翻译：用于航空发动机的燃油电路，具有燃油压力调节阀的电路
公开(公告)号：US20130283811A1
公开(公告)日：2013-10-31
申请号：US13978470
申请日：2012-01-04
申请人： Nicolas Potel , Sebastien Gameiro
发明人： Nicolas Potel , Sebastien Gameiro
IPC分类号： F02C7/22
CPC分类号： F02C7/22 , F02C7/222 , F02C7/224 , F02C7/236 , F02C9/26 , F02C9/263 , F02C9/28 , F05D2260/406 , F05D2270/303
摘要： A fuel circuit for an aviation turbine engine, the fuel circuit including: a main fuel line for feeding fuel to a combustion chamber of the engine and including a positive displacement pump; an auxiliary fuel line connected to the main fuel line at a junction situated downstream from the pump and serving to feed fuel to hydraulic actuators to control variable-geometry equipment of the engine, the auxiliary fuel line including electrohydraulic servo-valves upstream from each actuator; and a fuel pressure regulator valve arranged on the main fuel line downstream from the pump.
摘要翻译：一种用于航空涡轮发动机的燃料回路，所述燃料回路包括：用于将燃料供给到所述发动机的燃烧室并包括容积式泵的主燃料管线; 辅助燃料管路，其连接于位于泵下游的连接处，用于向液压致动器供给燃料以控制发动机的可变几何设备，辅助燃料管线包括每个致动器上游的电动液压伺服阀; 以及设置在泵下游的主燃料管线上的燃料压力调节阀。

9. 发明授权

US09702301B2 Fuel circuit for an aviation turbine engine, the circuit having a fuel pressure regulator valve 有权
公开(公告)号：US09702301B2
公开(公告)日：2017-07-11
申请号：US13978470
申请日：2012-01-04
申请人： Nicolas Potel , Sebastien Gameiro
发明人： Nicolas Potel , Sebastien Gameiro
IPC分类号： F02C7/22 , F02C9/26 , F02C9/28 , F02C7/224 , F02C7/236
CPC分类号： F02C7/22 , F02C7/222 , F02C7/224 , F02C7/236 , F02C9/26 , F02C9/263 , F02C9/28 , F05D2260/406 , F05D2270/303
摘要： A fuel circuit for an aviation turbine engine, the fuel circuit including: a main fuel line for feeding fuel to a combustion chamber of the engine and including a positive displacement pump; an auxiliary fuel line connected to the main fuel line at a junction situated downstream from the pump and serving to feed fuel to hydraulic actuators to control variable-geometry equipment of the engine, the auxiliary fuel line including electrohydraulic servo-valves upstream from each actuator; and a fuel pressure regulator valve arranged on the main fuel line downstream from the pump.

10. 发明授权

US09115647B2 Method for monitoring a pressure relief valve of a fuel injection circuit for a turbomachine 有权
标题翻译：用于监测用于涡轮机的燃料喷射回路的减压阀的方法
公开(公告)号：US09115647B2
公开(公告)日：2015-08-25
申请号：US13552066
申请日：2012-07-18
申请人： Brice Andre , Nicolas Potel
发明人： Brice Andre , Nicolas Potel
IPC分类号： E03B7/07 , F02C7/236 , F02C9/26
CPC分类号： F02C7/236 , F02C9/26 , F05D2270/3015 , Y10T137/0318
摘要： A detection method of a breakdown of a pressure relief valve of a fuel injection circuit for a turbomachine, the injection circuit including a low pressure stage and a high pressure stage, the low pressure stage having an inlet and an outlet, the high pressure stage having an inlet and an outlet, the low pressure stage being connected to the high pressure stage, the pressure relief valve being connected in parallel with respect to the high pressure stage, the injection circuit further including a recirculation loop including an inlet connected to the outlet of the high pressure stage and an outlet connected to the outlet of the low pressure stage, the method including measuring a differential pressure in the injection circuit.
摘要翻译：一种用于涡轮机的燃料喷射回路的泄压阀的故障的检测方法，所述喷射回路包括低压级和高压级，所述低压级具有入口和出口，所述高压级具有入口和出口，所述低压级连接到所述高压级，所述减压阀相对于高压级并联连接，所述注入回路还包括再循环回路，所述再循环回路包括连接到所述高压级的出口的入口所述高压级和连接到所述低压级的出口的出口，所述方法包括测量所述注入回路中的压差。

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