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1. 发明授权

US09222418B2 Fuel feed circuit with hydraulic actuator and fuel metering unit for an aeroengine 有权
标题翻译：具有用于航空发动机的液压致动器和燃料计量单元的燃料供给回路
公开(公告)号：US09222418B2
公开(公告)日：2015-12-29
申请号：US13500756
申请日：2010-09-30
申请人： Nicolas Alain Bader , Frederic Brettes , Bastien Dore , Laurent Gilbert Yves Hodinot
发明人： Nicolas Alain Bader , Frederic Brettes , Bastien Dore , Laurent Gilbert Yves Hodinot
IPC分类号： F02C9/48 , F02C7/236 , F02C9/26 , F02K1/17
CPC分类号： F02C9/48 , F02C7/236 , F02C9/263 , F02K1/17
摘要： A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system including first and second positive displacement pumps, a hydraulic actuator, and a fuel metering unit. As a function of a position of a slide of the actuator, a feed orifice of the actuator may be connected to a high-pressure delivery orifice connected to an outlet of the second pump, or to a low-pressure delivery orifice connected to a low-pressure feed line. The fuel metering unit includes through sections, one of these through sections being connected to an outlet of the high-pressure pumping system and the other through section being connected to an outlet of the high-pressure pumping system and leading to a high-pressure pilot chamber of the hydraulic actuator.
摘要翻译：一种用于航空发动机的燃料供给电路，该电路包括包括第一和第二容积式泵的高压泵送系统，液压致动器和燃料计量单元。作为致动器的滑动位置的函数，致动器的进料孔可以连接到连接到第二泵的出口的高压输送孔，或连接到低压输送孔压力进料管线。燃料计量单元包括贯穿部分，这些通过部分中的一个连接到高压泵送系统的出口，另一个通过部分连接到高压泵送系统的出口，并通向高压引燃器液压执行器的腔室。

2. 发明申请

US20110232479A1 PISTON WITH A DUCT UNDER A GASKET 有权
标题翻译：活塞在垫圈下面
公开(公告)号：US20110232479A1
公开(公告)日：2011-09-29
申请号：US13071850
申请日：2011-03-25
申请人： Frederic BRETTES , Alain Francois Jean Lavie
发明人： Frederic BRETTES , Alain Francois Jean Lavie
IPC分类号： F01B31/00
CPC分类号： F01D17/26 , F05D2260/6022 , F15B15/1452 , F15B15/1485 , F15B21/042 , F16J1/008 , F16J1/09
摘要： The invention relates to a piston having a first face, a second face opposite to the first face, a third face connecting said first and second faces together and presenting a groove, and a sealing gasket housed in said groove. The piston includes a duct constituted by a first segment situated inside the piston and connecting said first face to said groove, by a second segment situated inside the piston and connecting said second face to said groove, and by an intermediate segment connecting together said first and second segments and crossing said groove, the walls of said intermediate segment being formed by the walls of said groove and by said sealing gasket in such a manner that said intermediate segment forms a leaktight tube that opens out solely via the first segment and via the second segment, said intermediate segment presenting at least one obstacle suitable for impeding the flow of fluid that flows along said intermediate segment.
摘要翻译：本发明涉及具有第一面，与第一面相对的第二面的活塞，将第一和第二面连接在一起并具有凹槽的第三面和容纳在所述凹槽中的密封垫。活塞包括由位于活塞内部并通过位于活塞内部并将所述第二面连接到所述凹槽的第二段连接到所述凹槽的第一段构成的管道，以及将所述第一和第二区段连接在一起的中间区段第二段并与所述槽交叉，所述中间段的壁由所述槽的壁和所述密封衬垫形成，使得所述中间段形成一个泄漏管，该密封管仅通过第一段和第二段打开所述中间段呈现适于阻止沿着所述中间段流动的流体流动的至少一个障碍物。

3. 发明申请

US20080178596A1 FUEL-INJECTION DEVICE IN A TURBOMACHINE 有权
标题翻译：燃油喷射装置在涡轮机中
公开(公告)号：US20080178596A1
公开(公告)日：2008-07-31
申请号：US12016624
申请日：2008-01-18
申请人： Frederic BRETTES , Jean Charles Cappellari , Laurent Gilbert Yves Hodinot , Sandrine Huet
发明人： Frederic BRETTES , Jean Charles Cappellari , Laurent Gilbert Yves Hodinot , Sandrine Huet
IPC分类号： F02C1/00
CPC分类号： F23K5/147 , F02C7/232 , F02C7/236 , F02C9/263 , Y10T137/2562 , Y10T137/2605 , Y10T137/262 , Y10T137/7725
摘要： A fuel-injection device in a turbomachine, comprising a high-pressure pump (10) supplying a flow control valve (16), whose outlet is connected via a pressurization and cut-off valve (20) to a fuel-injector (18) feed pipe (22), the valve (20) being connected to the inlet and to the outlet of the pump (10) in order to define two fuel pressurization thresholds, one being used to start-up and restart the turbomachine, and the other being used for operating the turbomachine as from an idle speed and for commanding an equipment with variable geometry (24).
摘要翻译：一种涡轮机中的燃料喷射装置，包括供应流量控制阀（16）的高压泵（10），其出口通过加压和截止阀（20）连接到燃料喷射器（18），进料管（22），阀（20）连接到泵（10）的入口和出口，以便限定两个燃料加压阈值，一个用于起动和重新启动涡轮机，另一个用于从怠速速度操作涡轮机，并用于命令具有可变几何形状的设备（24）。

4. 发明申请

US20120266600A1 FUEL FEED CIRCUIT FOR AN AEROENGINE 有权
标题翻译：燃油送料电路
公开(公告)号：US20120266600A1
公开(公告)日：2012-10-25
申请号：US13500756
申请日：2010-09-30
申请人： Nicolas Alain Bader , Frederic Brettes , Bastien Dore , Laurent Gilbert, Yves Hodinot
发明人： Nicolas Alain Bader , Frederic Brettes , Bastien Dore , Laurent Gilbert, Yves Hodinot
IPC分类号： F02C7/22
CPC分类号： F02C9/48 , F02C7/236 , F02C9/263 , F02K1/17
摘要： A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system including first and second positive displacement pumps, a hydraulic actuator, and a fuel metering unit. As a function of a position of a slide of the actuator, a feed orifice of the actuator may be connected to a high-pressure delivery orifice connected to an outlet of the second pump, or to a low-pressure delivery orifice connected to a low-pressure feed line. The fuel metering unit includes through sections, one of these through sections being connected to an outlet of the high-pressure pumping system and the other through section being connected to an outlet of the high-pressure pumping system and leading to a high-pressure pilot chamber of the hydraulic actuator.
摘要翻译：一种用于航空发动机的燃料供给电路，该电路包括包括第一和第二容积式泵的高压泵送系统，液压致动器和燃料计量单元。作为致动器的滑动位置的函数，致动器的进料孔可以连接到连接到第二泵的出口的高压输送孔，或连接到低压输送孔压力进料管线。燃料计量单元包括贯穿部分，这些通过部分中的一个连接到高压泵送系统的出口，另一个通过部分连接到高压泵送系统的出口，并通向高压引燃器液压执行器的腔室。

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