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。

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。

公开(公告)号：US09194755B2

公开(公告)日：2015-11-24

申请号：US13640648

申请日：2011-04-05

申请人： Bruno Robert Gaully ,  Thierry Poix ,  Maurice Georges Vernochet

发明人： Bruno Robert Gaully ,  Thierry Poix ,  Maurice Georges Vernochet

IPC分类号： G01K1/14 ,  G01K13/02 ,  F01D17/08 ,  F01D17/10 ,  F02C9/18 ,  F02C9/52

CPC分类号： G01K13/02 ,  F01D17/085 ,  F01D17/105 ,  F02C9/18 ,  F02C9/52 ,  G01K1/14

摘要： A device for measuring a compressor inlet temperature in a primary stream flow passage of a bypass turbojet. The device includes an airtight hollow structure forming a connection arm of an intermediate casing of the turbojet and configured to pass radially through a flow passage for the primary stream and a flow passage for a secondary stream of the turbojet, the connection arm including at least one inlet air orifice opening out into the primary stream flow passage at an inlet of a compressor and at least one air outlet orifice leading to a zone of the turbojet in which surrounding pressure is less than pressure in the primary stream flow passage at the inlet of the compressor; and a temperature probe having its sensitive element arranged inside the connection arm.

摘要翻译： 一种用于测量旁通涡轮喷气发动机的一次流流道中的压缩机入口温度的装置。 该装置包括气密中空结构，其形成涡轮喷气发动机的中间壳体的连接臂并且被配置为径向地通过用于主流的流动通道和用于涡轮喷气发动机的二次流的流动通道，连接臂包括至少一个 入口空气孔口在压缩机的入口处打开到主流流动通道中，并且至少一个空气出口孔口通向涡轮喷气发动机的区域，其中周围压力小于主流道中的压力。 压缩机; 以及温度探针，其敏感元件布置在连接臂的内部。

公开(公告)号：US20130051426A1

公开(公告)日：2013-02-28

申请号：US13640648

申请日：2011-04-05

申请人： Bruno Robert Gaully ,  Thierry Poix ,  Maurice Georges Vernochet

发明人： Bruno Robert Gaully ,  Thierry Poix ,  Maurice Georges Vernochet

IPC分类号： G01K13/02

CPC分类号： G01K13/02 ,  F01D17/085 ,  F01D17/105 ,  F02C9/18 ,  F02C9/52 ,  G01K1/14

摘要： A device for measuring a compressor inlet temperature in a primary stream flow passage of a bypass turbojet. The device includes an airtight hollow structure forming a connection arm of an intermediate casing of the turbojet and configured to pass radially through a flow passage for the primary stream and a flow passage for a secondary stream of the turbojet, the connection arm including at least one inlet air orifice opening out into the primary stream flow passage at an inlet of a compressor and at least one air outlet orifice leading to a zone of the turbojet in which surrounding pressure is less than pressure in the primary stream flow passage at the inlet of the compressor; and a temperature probe having its sensitive element arranged inside the connection arm.

摘要翻译： 一种用于测量旁通涡轮喷气发动机的一次流流道中的压缩机入口温度的装置。 该装置包括气密中空结构，其形成涡轮喷气发动机的中间壳体的连接臂并且被配置为径向地通过用于主流的流动通道和用于涡轮喷气发动机的二次流的流动通道，连接臂包括至少一个 入口空气孔口在压缩机的入口处打开到主流流动通道中，并且至少一个空气出口孔口通向涡轮喷气发动机的区域，其中周围压力小于主流道中的压力。 压缩机; 以及温度探针，其敏感元件布置在连接臂的内部。