公开(公告)号：WO2011117609A1

公开(公告)日：2011-09-29

申请号：PCT/GB2011/050534

申请日：2011-03-17

Applicant: AIRBUS OPERATIONS LIMITED ,  LAM, Joseph K-W ,  TICHBORNE, Franklin ,  PARMENTER, David ,  MASTERS, Simon

Inventor： LAM, Joseph K-W ,  TICHBORNE, Franklin ,  PARMENTER, David ,  MASTERS, Simon

IPC: F02M37/22 ,  F02M37/00

CPC classification number: F02M37/221 ,  F02M37/0052 ,  F02M37/223

Abstract: A fuel system comprising a liquid fuel tank, an engine, and a coalescing filter adapted to separate water from fuel, the filter having an inlet fluidically connected to the fuel tank, a first outlet fluidically connected to a fuel feed system for the engine, and a second outlet fluidically connected to the fuel tank, wherein the coalescing filter is adapted to discharge fuel filtrate from the second outlet and filtrand from the first outlet. Also, a method of removing water or ice from a fuel tank, the method comprising directing a flow of fuel from a fuel tank to a coalescing filter adapted to separate water from fuel, discharging filtrand from a first outlet of the coalescing filter to a fuel feed system for consumption by an engine, and discharging fuel filtrate from a second outlet of the coalescing filter and returning the fuel filtrate to the fuel tank.

Abstract translation: 一种燃料系统，包括液体燃料箱，发动机和适于将燃料分离的聚结过滤器，所述过滤器具有流体连接到所述燃料箱的入口，与所述发动机的燃料供给系统流体连接的第一出口，以及 流体连接到燃料箱的第二出口，其中聚结过滤器适于从第二出口排出燃料滤液和从第一出口排出过滤器。 另外，一种从燃料箱中除去水或冰的方法，该方法包括将来自燃料箱的燃料流引导至适于将燃料分离出的水的聚结过滤器，将过滤器从聚结过滤器的第一出口排出到燃料 进料系统，用于由发动机消耗，并将燃料滤液从聚结过滤器的第二出口排出并将燃料滤液返回到燃料箱。

公开(公告)号：WO2011117610A1

公开(公告)日：2011-09-29

申请号：PCT/GB2011/050535

申请日：2011-03-17

Applicant: AIRBUS OPERATIONS LIMITED ,  LAM, Joseph K-W ,  TICHBORNE, Franklin ,  MASTERS, Simon ,  PARMENTER, David

Inventor： LAM, Joseph K-W ,  TICHBORNE, Franklin ,  MASTERS, Simon ,  PARMENTER, David

IPC: B01D53/26 ,  B64D37/32 ,  B64D37/34 ,  B01D53/86

CPC classification number: B01D53/265 ,  B01D53/8671 ,  B01D2257/104 ,  B01D2259/4516 ,  B01D2259/4575 ,  B64D37/32 ,  B64D37/34 ,  Y02T50/44

Abstract: A fuel system comprising a fuel tank (1), a vent tank (3) having a duct open to the ambient atmosphere, a first vent line (4, 5) fluidically connecting the fuel tank ullage to the vent tank (3), a gas drying system (8) including a pump (9) and a dehumidifying device (20) disposed within the vent tank, and a second vent line (13,14) fluidically connecting a dry gas outlet (12) of the dehumidifying device (20) to the ullage, wherein the pump (9) is operable to maintain a higher pressure within the ullage than in the vent tank (3) so as to drive vapour rich gas from the ullage into the vent tank via the first vent line (4,5). Also, a method of operating the fuel system and a method of retro - fitting the gas drying system in an existing fuel system. The gas drying system may optionally be a gas drying/inerting system.

Abstract translation: 一种燃料系统，包括燃料箱（1），具有与周围大气开放的通道的排气罐（3），将燃料箱排空流体连接到通风罐（3）的第一排气管线（4,5） 气体干燥系统（8），包括设置在通气罐内的泵（9）和除湿装置（20），以及第二排气管线（13,14），流体连接除湿装置（20）的干燥气体出口 ），其中泵（9）可操作以在空气中保持比通气罐（3）中更高的压力，以便将富含蒸汽的气体通过第一排气管线（4）从空气驱动进入通气罐 ，5）。 另外，操作燃料系统的方法以及将现有燃料系统中的气体干燥系统复原的方法。 气体干燥系统可以可选地是气体干燥/惰化系统。

公开(公告)号：WO2006013351A1

公开(公告)日：2006-02-09

申请号：PCT/GB2005/003026

申请日：2005-08-02

Applicant: AIRBUS UK LIMITED ,  TICHBORNE, Franklin, George ,  LEY, Kim, Michael

Inventor： TICHBORNE, Franklin, George ,  LEY, Kim, Michael

IPC: G01R31/02

CPC classification number: G01R31/025 ,  B64D37/32

Abstract: Unsafe electric energies can exist in aircraft fuel tanks as a result of static build-up or induced currents from lightning strikes. The invention provides an aircraft fuel tank (1) including two discharge paths (18-21-5 & 18-20-15-16-17-12) for the safe discharge of electricity from the tank (1) before it reaches levels where an arc, spark or other electric discharge, able to ignite fuel in the tank, could occur. The failure of both the discharge paths (18-21-5 & 18-20-15-16-17-12) would significantly increase the risk of an ignition causing electrical discharge occurring. The tank (1) thus also includes a circuit (11) for monitoring the integrity of each discharge path. By having at least two discharge paths (18-21-5 & 18-20-15-16-17-­12), should one discharge path fail (which failure being detected by the monitoring circuit (11), at least one alternative discharge path exists for the safe discharge of electrical energy from the fuel tank (1), until the failed discharge path is repaired.

Abstract translation: 由于静电积聚或雷击引起的电流，飞机燃料箱中可能会存在不安全的电能。 本发明提供了一种飞机燃料箱（1），其包括两个排放路径（18-21-5和18-20-15-16-17-12），用于在达到水平之前从罐（1）安全排放电力 可能会发生能够点燃罐中的燃料的电弧，火花或其他放电。 放电路径（18-21-5和18-20-15-16-17-12）的故障将显着增加引起放电发生的点火风险。 因此，罐（1）还包括用于监测每个排放路径的完整性的回路（11）。 通过具有至少两个放电路径（18-21-5和18-20-15-16-17-12），如果一个放电路径失效（由监视电路（11）检测到该故障），至少一个替代放电 存在用于从燃料箱（1）安全排出电能的路径，直到故障排放路径被修复。

公开(公告)号：WO2006013346A1

公开(公告)日：2006-02-09

申请号：PCT/GB2005/003018

申请日：2005-08-02

Applicant: AIRBUS UK LIMITED ,  TICHBORNE, Franklin, George ,  LEY, Kim, Michael

Inventor： TICHBORNE, Franklin, George ,  LEY, Kim, Michael

IPC: B64D37/02

CPC classification number: B64D45/02 ,  B64D37/02 ,  B64D37/32 ,  B65D90/24 ,  G01F23/266 ,  G01F23/268

Abstract: Unsafe electric energies can exist in aircraft fuel tanks as a result of static build-up or induced currents from lightning strikes. The invention provides an aircraft having a ground circuit (19) and including a fuel tank (1) having a fuel probe circuit having its own ground circuit (18). Multiple discharge paths (18-26-19) allow the safe discharge of electricity from the tank (1) before it reaches levels where an arc, spark or other electric discharge, able to ignite fuel in the tank, could occur. The discharge paths all pass via a conductive foam (26) having a relatively high impedance that allow static bleed, but does not significantly increase the risk of currents induced by lightning reaching levels at which an ignition-causing electrical discharge might occur. The foam (26) is securely bonded to both the aircraft ground circuit (19) and the fuel probe ground (18), the bonds having a large area of surface-to-surface contact.

Abstract translation: 由于静电积聚或雷击引起的电流，飞机燃料箱中可能会存在不安全的电能。 本发明提供一种具有接地电路（19）并包括具有燃料探针电路的燃料箱（1）的飞行器，燃料探针电路具有其自身的接地电路（18）。 多个排放路径（18-26-19）允许在达到可以发生能够点燃罐内的燃料的电弧，火花或其他放电的水平面之前从罐（1）安全地排放电力。 放电路径全部通过具有允许静态放电的相对高阻抗的导电泡沫（26），但是不会显着增加由闪电达到可能发生引发点火放电的电平的风险。 泡沫（26）牢固地结合到飞行器接地电路（19）和燃料探针接地（18）两者上，这些键具有大的面对面接触面积。

公开(公告)号：WO2011010124A1

公开(公告)日：2011-01-27

申请号：PCT/GB2010/051136

申请日：2010-07-12

Applicant: AIRBUS OPERATIONS LIMITED ,  LAM, Joseph K-W ,  TICHBORNE, Franklin ,  MASTERS, Simon ,  PARMENTER, David

Inventor： LAM, Joseph K-W ,  TICHBORNE, Franklin ,  MASTERS, Simon ,  PARMENTER, David

IPC: B64D37/32

CPC classification number: B64D37/32 ,  Y10T137/86324

Abstract: An aircraft fuel tank ventilation system, comprising a refrigerative dehumidifying device (17) having a refrigerating element (21) in contact with air flowing between a vent (15) open to the atmosphere and a fuel tank (4, 5). Also, a method of dehumidifying air introduced into an aircraft fuel tank via the ventilation system, the method comprising directing atmospheric air from the vent into contact with the refrigerating element, and cooling the refrigerating element so as to remove water vapour from the air flowing from the vent towards the fuel tank by condensation.

Abstract translation: 一种飞机燃料箱通风系统，包括具有与在大气开放的通风口（15）和燃料箱（4,5）之间流动的空气接触的制冷元件（21）的制冷除湿装置（17）。 此外，通过通风系统对引入飞机燃料箱的空气进行除湿的方法，其特征在于，包括将来自所述排气口的大气与所述冷冻元件接触的方法，以及冷却所述冷冻元件，以从所述空气流中流出的空气 通过冷凝通向燃料箱的通风口。

公开(公告)号：WO2010139974A1

公开(公告)日：2010-12-09

申请号：PCT/GB2010/050845

申请日：2010-05-24

Applicant: AIRBUS OPERATIONS LIMITED ,  TICHBORNE, Franklin ,  BEALE, James

Inventor： TICHBORNE, Franklin ,  BEALE, James

IPC: G01F23/26

CPC classification number: G01F23/266 ,  G01F23/265 ,  G01N33/2847

Abstract: A fuel level probe (200) has a series of stacked, annular capacitors (202), the capacitance of which changes with the dielectric constant of the fluid (214, 216, 218) in which they are immersed. A multiplexer (210) provides sequential measurement of each capacitor (202) to determine a step change in capacitance and hence fluid levels based on the time at which the capacitance changes.

Abstract translation: 燃料水平探头（200）具有一系列堆叠的环形电容器（202），其电容随着浸入其中的流体（214,216,218）的介电常数而变化。 多路复用器（210）提供每个电容器（202）的顺序测量，以基于电容变化的时间来确定电容的阶跃变化，从而确定液位。

公开(公告)号：WO2007071909A1

公开(公告)日：2007-06-28

申请号：PCT/GB2006/004501

申请日：2006-12-01

Applicant: AIRBUS UK LIMITED ,  TICHBORNE, Franklin, George ,  LEY, Kim, Michael

Inventor： TICHBORNE, Franklin, George ,  LEY, Kim, Michael

IPC: B64D37/02 ,  B60K15/06 ,  G01F23/00

CPC classification number: B64D37/00 ,  G01F9/00 ,  G01F23/0076

Abstract: One or more main aircraft fuel tanks (34) are provided with one or more fuel gauges (42) arranged to provide a measure of the amount of fuel in said one or more main fuel tanks. One or more auxiliary fuel tanks (30) are also provided. The aircraft uses fuel during a first phase of fuel consumption, upon commencement of which phase the auxiliary fuel tanks hold fuel. After the first phase said one or more auxiliary fuel tanks (30) are empty and a second phase commences. During the first phase, an indication of the amount of fuel carried by the aircraft is provided by means of summing (i) the amount of fuel in the main fuel tanks (34) as measured by said one or more fuel gauges (42) and (ii) the amount of fuel remaining in said one or more auxiliary fuel tanks (30) as calculated using a measure relating to the fuel consumption rate. During the second phase of fuel consumption, an indication of the amount of fuel carried by the aircraft is provided on the basis of the amount of fuel measured by said one or more fuel gauges (42).

Abstract translation: 一个或多个主飞行器燃料箱（34）设置有一个或多个燃料计（42），其布置成提供所述一个或多个主燃料箱中的燃料量的量度。 还提供一个或多个辅助燃料箱（30）。 在燃料消耗的第一阶段，飞机使用燃料，在辅助燃料箱开始阶段，燃料储存在燃料中。 在第一阶段之后，一个或多个辅助燃料箱（30）是空的并且第二阶段开始。 在第一阶段期间，借助于（i）由所述一个或多个燃料计（42）测量的主燃料箱（34）中的燃料量和 （ii）使用与燃料消耗率相关的措施计算的所述一个或多个辅助燃料箱（30）中剩余的燃料量。 在燃料消耗的第二阶段期间，基于由所述一个或多个燃料计（42）测量的燃料量来提供飞机携带的燃料量的指示。

公开(公告)号：WO2006032873A1

公开(公告)日：2006-03-30

申请号：PCT/GB2005/003628

申请日：2005-09-21

Applicant: AIRBUS UK LIMITED ,  TICHBORNE, Franklin, George ,  CLARKE, Raymond ,  BROWN, Michael, Daniel

Inventor： TICHBORNE, Franklin, George ,  CLARKE, Raymond ,  BROWN, Michael, Daniel

IPC: G01M3/32

CPC classification number: G01F23/263 ,  G01F9/008

Abstract: A method of detecting a fuel leak from a fuel store of an aircraft is described. A processor (1) receives inputs (2, 3) relating to the amount of fuel in the fuel store and to the rate of fuel used by the aircraft, both inputs being subject to noise. The processor defines a fuel flow system state defined by a noise-compensated measures of the amount of fuel in the fuel store, a fuel leak amount estimate and a fuel leak rate estimate. The processor (1) periodically calculates a new estimated state of the system in view of a previous estimated state of the system and values of the inputs (2, 3). The processor monitors the fuel leak amount estimate and the fuel leak rate estimate and if either exceeds a respective threshold value send a signal to a fuel leak warning means (4). The method employs a recursive state estimation method that improves leak detection, reduces false alarms and is less demanding on processor and memory requirements.

Abstract translation: 描述了从飞行器的燃料仓检测燃料泄漏的方法。 处理器（1）接收与燃料储存器中的燃料量相关的输入（2,3）和飞机使用的燃料的速率，两个输入都受到噪声的影响。 处理器定义由燃料储存器中的燃料量的噪声补偿措施，燃料泄漏量估计和燃料泄漏率估计定义的燃料流量系统状态。 考虑到系统的先前估计状态和输入（2,3）的值，处理器（1）周期性地计算系统的新估计状态。 处理器监视燃料泄漏量估计和燃料泄漏率估计，并且如果超过相应的阈值，则向燃料泄漏警告装置（4）发送信号。 该方法采用递归状态估计方法，改进泄漏检测，减少假警报，对处理器和内存要求要求较低。