CN101631718B - Water scavenging system - Google Patents
Water scavenging system Download PDFInfo
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- CN101631718B CN101631718B CN2008800080494A CN200880008049A CN101631718B CN 101631718 B CN101631718 B CN 101631718B CN 2008800080494 A CN2008800080494 A CN 2008800080494A CN 200880008049 A CN200880008049 A CN 200880008049A CN 101631718 B CN101631718 B CN 101631718B
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Abstract
A method of removing water (7) from a fuel tank (2) using a water scavenging line (4) which has an inlet (6) immersed in the water and an outlet (5) coupled to a water tank (3). The method comprises filling the fuel tank with fuel (30) whereby the fuel exerts hydrostatic pressure on the water, the hydrostatic pressure driving the water up the water scavengingline against the force of gravity and into the water tank. The use of hydrostatic pressure provides an automatic and relatively simple method of extracting the water from the bottom of the fuel tank. The water tank enables the extracted water to be stored for disposal at a later time, typically by feeding the water into an engine.
Description
Technical field
This present invention relates to a kind of water removal system.
Background technology
A kind of method of anhydrating of from aircraft fuel tank, removing has been described in US4809934.Remove water pipe and collect the water that is dispersed in the fuel that just in time is arranged in the boost pump upper reaches.First problem of this system is the complex arrangement of requirement Venturi tube and jet dredge pump.Another problem be when driving engine during with relative low-speed running water can flow in the driving engine.This can reduce the operating efficiency of driving engine.Further problem is that system can not be fully except that anhydrating from Fuel Tank during single flight.
A kind of method of anhydrating of from Fuel Tank, removing has been described in US6170470.Water pipe feeds water from Fuel Tank in the driving engine.Because when driving engine during with relative high-speed operation the water of inflow engine will remarkable adverse influence can not arranged to the performance characteristic of driving engine, so when the speed of driving engine surpasses minimum threshold, open the valve in the water pipe.Problem about the method for US6170470 is the communication line that the measurement of engine rotate speed device must be provided and connect this valve.These parts all have the risk of inefficacy, and must communication line be gone out from Fuel Tank lira close and safe in essence mode with liquid.
Be that in case aircraft takes off, the water that ambient air temperature is just reduced in-30 or-40 degrees centigrade and the fuel froze after about 20 minutes with aircraft fuel interconnection concrete difficulty together.After water froze, water was trapped in the Fuel Tank and thaws when landing up to Fuel Tank.If therefore water is not removed in initial 20 minutes, then can build up up to causing problem or being discharged by manual through water after the flight several times.
Content of the present invention
First aspect of the present invention provides a kind of utilization to remove water pipe and from Fuel Tank, removes the method for anhydrating; The said pipe that dewaters has water-immersed inlet and is connected to the outlet of water tank; Said method comprises: make said Fuel Tank be full of fuel; Said thus fuel applies hydrostatic pressure in water, and said hydrostatic pressure overcomes gravity forces water to rise and enter in the said water tank along the said water pipe that removes, and with water from said water tank in drain hose is fed to driving engine.
Second aspect of the present invention provides a kind of being used for to remove the water removal system that anhydrates from Fuel Tank, and said water removal system comprises:
Water tank;
Remove water pipe, the said pipe that dewaters has the outlet that is connected to said water tank; And
Drain hose, said drain hose have inlet that is connected to said water tank and the outlet that can be connected to driving engine in use,
Wherein, the said pipe that dewaters has an inlet, and said inlet can be immersed in the bottom of said Fuel Tank and in use in the said water that removes under the said outlet of water pipe, and hydrostatic pressure can overcome gravity and forces water to rise and get into said water tank along removing water pipe thus.
The use of hydrostatic pressure provide a kind of bottom from said Fuel Tank extract water automatically and simple relatively method.Said water tank can be stored the water of extraction and is provided with post-processing.
Preferably with the said said inlet that removes water pipe be positioned at be located in the said Fuel Tank refuel during the water position that trends towards gathering.Usually this is the nadir at said Fuel Tank.
Can water be trapped in the water tank through check valve, perhaps can be trapped in the water tank through being positioned at the position Jiang Shui that is higher than the water tank nadir except that the outlet of water pipe.Under latter instance, a part of removing water pipe can be passed the wall extension of water tank, such as diapire that passes water tank or sidewall.
Be to be understood that said Fuel Tank can fully be full of fuel, or only partly be full of fuel.As long as make said Fuel Tank filling must exceed the said said outlet that removes water pipe, then said Fuel Tank will apply enough hydrostatic pressures and get into said water tank to force water.
Usually also utilize hydrostatic pressure to make water flow into driving engine from said water tank.This has eliminated the needs to manual drain operation, and can use less relatively water tank.
Preferably the volume of said water tank is less than 0.1% of said propellant capacity, though said water tank by the situation of manual draining under, the volume of said water tank is about the larger capacity of 0.5% (but preferably being not more than 1%) magnitude of said fuel tank capacity.
Common said Fuel Tank is an aircraft fuel tank, though said system can be used to other purposes, for example fuel system of automobile.
Be configured to from aircraft fuel tank, remove under the situation of anhydrating in said system, the said inlet of said drain hose can be towards the back skew of said water tank with respect to the heading of said aircraft.As a result, water will trend towards flowing towards the said inlet of said drain hose when said aircraft is faced upward.In this case, preferably the said inlet of said drain hose also is oriented to be higher than the nadir of said water tank.This has prevented that water flows into said drain hose when said rounding out.
Likewise, be configured to from aircraft fuel tank, remove under the situation of anhydrating in said system, the said said outlet that removes water pipe can be towards the front skew of said water tank with respect to the heading of aircraft.As a result, because fuel will trend towards flowing and getting into said Fuel Tank towards the said water pipe that removes when said aircraft dives in landing with during landing, so said system can be by automatic topping-up.
Preferably, the said said outlet that removes water pipe is positioned at the place ahead of the said inlet of said drain hose with respect to the heading of said aircraft, above-mentioned two advantages are provided whereby.
Preferably, said water tank has 2 to 5 times capacity of the maximum water volume of gathering for each expectation of flying or travel.Water volume approximately is 40ppm (0.004%) with the ratio of volume of fuel; The water that each travelling is gathered for 8000 liters of Fuel Tanks of representative type is 0.32 liter, thereby said water tank will be customized to and remain between 0.6 and 1.5 liter.
Be installed under the situation in the aircraft increase of the effective pitch of the said aircraft of response valve in the preferred said drain hose or respond the reducing of effective pitch of said aircraft and open in said system.
Under the situation about opening in the increase of said response valve effective pitch, said valve provides the substitute of engine speed measurement mechanism, and this is to open automatically because of the increase of said response valve effective pitch of said aircraft during taking off and climbing.Because said engine speed will be high relatively when taking off and climb, can not influence the performance characteristic of said driving engine significantly so this means water will flow into said driving engine.
In case one of concrete difficulty of aircraft fuel system is said aircraft has taken off then water that ambient air temperature is just reduced in-30 or-40 degrees centigrade and the fuel froze after about 20 minutes.It is trapped in the said Fuel Tank and thaws when landing up to said Fuel Tank after water freezes.Therefore if water is not removed in the junior two ten minutes, so in that it will little by little gather up to it and cause problem or discharged by manual through flight back several times.Therefore another advantage that during taking off and climbing, moves the water to flow into said driving engine is before water freezing, just to have removed water.
Under the situation about opening reducing of said response valve effective pitch; Said valve can be turned said water tank (only being full of fuel now so all flow into said driving engine because of all water during taking off and climbing) during said aircraft landing and the landing, and operation is prepared in order to refuel next time.
Preferably said valve has closed condition, and said valve stops the water flows in the said drain hose under said closed condition; Said valve also has forward and reverse opening state, and under said forward and reverse opening state, said valve allows water to flow through said valve, and the increase that wherein said valve is configured to respond the effective angle of said valve changes to its forward open mode from its closed condition; And said valve be configured to respond said valve effective angle reduce change to its reverse opening state from its closed condition.Perhaps, can thermostatic control valve be set parallelly connectedly with said drain hose, said thermostatic control valve is opened under temperature drops to uniform temperature the time.
Preferably, said water tank has opening at its top, and said opening can permit fuel to flow into said water tank in use.
In some embodiments of the present invention, said water tank horizontal vertical than (as with delimit) greater than 2, most preferably greater than 4.This makes the pressure head in the said water tank reach maxim, so that hydrostatic pressure can be used to hydraulic pressure is gone out said water tank.In an embodiment of the invention, said water tank is long along heading, and therefore the horizontal vertical ratio of said water tank is less than 1.
Description of drawings
To illustrate and describe embodiment of the present invention at present, wherein:
Fig. 1 shows an airplane;
Fig. 2-the 5th has the scheme drawing of the Fuel Tank of water removal system;
Fig. 6 a-6c shows in detail the pendulum valve;
Fig. 7 a-7c shows the first optional pendulum valve;
Fig. 8 a-8c shows the second optional pendulum valve;
Fig. 9 a shows water removal system according to another implementation of the invention;
Fig. 9 b shows the water removal system with a pair of sieve;
Figure 10 a shows the water removal system according to another implementation of the invention when facing upward aboard;
Figure 10 b shows in the flat system of flying over Figure 10 a in the journey of aircraft; And
Figure 10 c shows the system of Figure 10 a when water tank turned letter and aircraft nutation.
The specific embodiment
With reference to figure 1, aircraft 100 comprises the fuselage 102 that supports a pair of wing, and left wing is marked as 103.Each wing all carries driving engine, and the driving engine of left-hand side is marked as 104 among Fig. 1.The fuel of each driving engine all is stored in centre tank and the one or more wing tank.
Fig. 2 shows water removal system, and this system is installed in the wing tank 2.Water removal system comprises water tank 3 and removes water pipe 4, should remove water pipe 4 and have the inlet 6 in outlet 5 and the pond water 7 that is immersed in Fuel Tank 2 bottoms in water tank 3 bottoms.Water tank 3 is diameter 60mm, long 0.4m and open-topped standpipe normally.
Fig. 2-4 shows the fuel 30 that is in lower, medium and higher oil level in the case 2 respectively.When Fuel Tank is filled, the water 7 weight application hydrostatic pressures of fuel to converging in fuel tank bottom.This hydrostatic pressure overcome gravity force water along remove water pipe 4 rise, through check valve 8 and enter within the water tank 3, almost completely remove up to water as shown in Figure 3 from the bottom of Fuel Tank.When Fuel Tank continued filling fuel, the fuel bubble was through water (in Fig. 3 with 31 show in the said fuel foam three) and gathering in the layer 32 at water tank 3 tops.
When level of fuel reached the top of water tank 3, fuel flowed into water tank, the water tank that is full of as shown in Figure 4 through the opening 33 of tank top.
Get back to Fig. 2, drain hose 10 stretches out from the bottom of water tank 3.This drain hose has the inlet 11 in water tank 3, and links to each other with pump input pipe 13 and the outlet 12 parallel with last oil pipe 14.Last oil pipe 14 has the inlet 15 in Fuel Tank, and the oil level at these inlet 15 places is higher than the oil level except that pipe inlet 6 places.Inlet 6,15 all has filter or filter screen 16,17.
Valve 20 comprises the pendulum 40 that is articulated in the supporting structure (not shown) through axle 41.Axle 41 has cam 42.Chamber 43 in the drain hose 10 has inlet 44 and outlet 45.Door 46 is installed in the chamber 43 and the translation between the open position shown in the off position shown in Fig. 6 a and Fig. 6 b and the 6c of this ability.This 46 blocks inlet 44 and outlet 45 of chamber 43 at its off position, and allows fluid to flow through valve at its open position, shown in Fig. 6 b and 6c.
When the aircraft level, valve 20 be in Fig. 3,4 and 6a shown in closed condition.When " effective pitch " of aircraft increases to 7 degree when above, valve 20 changes to the forward open mode shown in Fig. 5 and the 6b from its closed condition." effective pitch " is defined as combining of physics pitch (being the physics pitch angle of aircraft) and the acceleration of quickening owing to advancing to obtain.
Along with valve 20 as shown in Figure 5 opening, drive water and the hydrostatic pressure that produces through the gravity head by the water in the water tank supplies water to pump 21 along drain hose 10.Note, because it is the density of the density ratio fuel of water is big, therefore relatively large along the gravity head of drain hose 10 force feed water.In other words, compare with the supposed situation that is full of fuel in the water tank 3, above-mentioned gravity pressure is big first watch.Thereby gravity head is tending towards preferentially the water fuel of last oil pipe 14 (rather than from) force feed to petrolift, is so when the water level in water tank is higher than the outlet 12 of drain hose 10 at least.The inductor pipe (not shown) that protrudes in the drain hose 10 also can be set alternatively.This has formed small throttling and has strengthened owing to Venturi effect trends towards making flowing in drain hose 10.
Notice that the structure shown in Fig. 2-5 is schematically, and if in the pitch angle of all expectations and water tank, all require the gravity head that provides enough under the situation of all water levels, then water tank 3 can be adjusted to the top of the outlet 12 that is located immediately at drain hose 11.
It is higher and thinner to it shall yet further be noted that water tank 3 can be designed to, so that make the gravity head maximization.More particularly; Horizontal vertical than (we are defined as it
among this paper wherein H be the height of water tank; A is the average cross-section of water tank) higher relatively; For example under the situation of the cylindrical water tank with 60mm diameter and 0.4m length, the horizontal vertical ratio of water tank is approximately 7.5.
If water tank 3 receives negative G, then water can be poured out and enter in the Fuel Tank 2 from the opening 33 at water tank 3 tops.Yet, since water tank 3 less (with capacity be the Fuel Tank 2 of about 8000 liters of magnitudes compare have the capacity of about 1 liter of magnitude), this can not influence performance.All water of turned letter will be assembled when fuel make up next time equally, by this way.
The size of water tank 3 is designed to provide in two to three minutes during taking off and climbing 0.5 premium on currency stream.The concentration of the water of the supply engine that causes thus in this stage is approximately 2500ppm.
After taking off and climbing, open valve 20 so that the rated capacity of pump 21 descends, and central fuel tank pump catcher.Simultaneously, because the pitch of aircraft drops to below 7 degree, valve 20 ad hoc is input to fuel in the pump near the off position shown in Fig. 6 b and through last oil pipe 14.
When aircraft carried out " underriding " during landing, the effective pitch of aircraft dropped to below-5 degree, and valve 20 changes to the reverse opening state shown in Fig. 6 c from closed condition.In this stage, water tank 3 possibly be empty, perhaps possibly comprise the fuel head on the residual fuel liquid level in the Fuel Tank.Note in the water tank 3 little water being arranged or do not have water (most of water before take off and climb during inflow engine), but water tank 3 possibly contain some fuel.If note having a large amount of water in the water tank, then water tank 3 freezes and possibly stop up sluicing valve 20.If water tank 3 contains fuel, then fuel can be during landing inflow engine, the turned letter water tank is that next fuel make up is prepared.
The first optional pendulum valve 20a (it can be used to replace valve 20) has been shown in Fig. 7 a-7c.In this case, replace adopting cam and cam follower, valve comprises the pendulum 50 that links to each other with door 51 through articulated linkage 52.Pendulum 50 has vertical arm 55 and horizontal arm 56, and vertically arm 55 and horizontal arm 56 are fixed relative to one another and be pivoted to a supporting structure (not shown) through axle 57.Connecting rod 52 is rotationally attached to door 51 at the one of which end through pivot 53, and is rotationally attached to the horizontal arm 56 of pendulum 50 through pivot 54 at its other end.Door 51 is slidably mounted in the chamber 57, and this door stretches out from drain hose at upside and downside, and between three control positioies shown in Fig. 7 a-7c, is driven by connecting rod 52.
The second optional pendulum valve 20b (it can be used to replace valve 20 or valve 20a) has been shown in Fig. 8 a-8c.In this case, replace adopting translation door, valve 20b has the closing member that between its opening and closing position, rotates.
Specifically, valve 20b has the pendulum 60 that is installed on the cylindrical closing member 61, and this cylindrical closing member 61 is arranged in the cylindrical chamber 62 in the drain hose 10.Closing member 61 has pair of channels 63,64, when pendulum with respect to the angle of drain hose reach+when 7 degree or-5 were spent, shown in Fig. 8 b and 8c, this pair of channels 63,64 was alignd with the entrance and exit of chamber 62 respectively.Attention is for ease of explanation, and drain hose 10, chamber 62 and closing member 61 are illustrated to be put vertically and be parallel to pendulum 60, and in fact their on even keels are directed and meet at right angles with pendulum 60.Equally, in Fig. 8 a-8c, exaggerated the angular deviation of 63,64 in passage for ease of explanation.In fact passage will extend (and chamber 62 is bigger with respect to drain hose 10 with closing member 61) with narrower angle so that required operation to be provided.
Compare with the valve shown in Fig. 7 a-7c and Fig. 8 a-8c, the advantage of the valve 20 shown in Fig. 6 a-6c is:
1, through adjusting shape and/or the size and/or the position of cam 42, easily the opening and closing characteristic of control cock;
2, because door 46 only has two control positioies, so chamber 43 relative compact;
3, from the maintenance purpose, can easily pendulum be separated with other parts of valve; And
Even the pitch of 4 aircrafts excessive (that is, if if pitch increase to basically+7 degree are above or be reduced to below-5 degree basically or have high acceleration/accel or deceleration/decel), the operation of valve is also unaffected.
In the alternate embodiments (not shown), several water tanks are through single shared pendulum valve 20 whole driving engines that are connected to parallelly connectedly, wherein each water tank all have separately remove water pipe and drain hose.
In another alternate embodiments (not shown), can the thermostatic control sluicing valve be installed on the pipeline parallelly connected with putting valve 20,20a or 20b.When temperature drops to 2 degrees centigrade (supposition) that will occur when aircraft cruises aloft when following, the thermostatic control sluicing valve is opened.This has guaranteed from water tank, to remove all water.Alternatively, thermostatic control valve can replace " underriding " operation of pendulum valve 20,20a, 20b, that is to say that the available similar pendulum valve that only has the forward open mode replaces putting valve 20,20a, 20b.For example, thermostatic control valve can be like wax formula valve that is used for the automotive engine calorstat or the bimetallic leaf spring of opening valve.
Fig. 9 a shows water removal system 70 according to another implementation of the invention.This water removal system comprises water tank 71, and run through water tank diapire 73 remove water pipe 72.When Fuel Tank was filled, fuel was to the water (not shown) weight application hydrostatic pressure that converges in fuel tank bottom.This hydrostatic pressure overcomes gravity forces water along removing water pipe 72 risings and entering in the water tank 71.
With the embodiment contrast of Fig. 2, the outlet 74 that removes water pipe 72 does not have check valve.Replace, stop current to return except that water pipe through the nadir that will be positioned on the diapire 73 except that the outlet 74 of water pipe 72 and be higher than water tank.With enough height of outlet 74 location, to guarantee that when all water from Fuel Tank have been pressed into water tank water level remains on outlet below 74.Also can locate outlet 74 enough low, be enough to hydraulic pressure is gone into water tank with the hydrostatic pressure of assurance from fuel head.
Compare with the embodiment of Fig. 2, lack check valve, the advantage aspect simplicity and reliability is provided thus except that in the water pipe.
Remove the bending of water pipe and lead the bottom of wall 76 towards water tank.This anti-sealing ejection from the top of water tank, and towards the bottom 73 guiding water of water tank, the bottom 73 of water tank is downward-sloping towards the inlet 76 of the nadir of Fuel Tank and drain hose 75.Drain hose 75 through pitch control cock (not shown) to lead to pump input pipe (not shown) with the drain hose 10 similar modes of the embodiment of Fig. 2.
Fig. 9 b shows the modification of the system among Fig. 9 a, and this modification has a pair of porous sieve 77 that helps from fuel, to separate the globule.Leave slit 78 preventing vent plug at the top of sieve, and stay slit 79 can flow to drain hose to allow water in the bottom of sieve.
Figure 10 a-10c shows the water removal system 80 of another embodiment according to the present invention.This water removal system comprises water tank 81 and removes water pipe 82, should remove water pipe 82 with the diapire 83 that water pipe 72 similar modes run through water tank that removes shown in Fig. 9 a.
Drain hose 84 leads to pump input pipe (not shown).But the embodiment contrast with Fig. 2 does not need the pitch control cock in drain hose.Replace, only need simple relatively check valve 85.
The inlet of drain hose 84 squints at the back and is higher than the nadir of water tank towards water tank, between the diapire 83 of this inlet and water tank, is provided with short tube or manger 87.As a result, when during aircraft is taking off and climbing, facing upward, shown in Figure 10 a, water level rises on the top of short tube 87 and enters in the drain hose 84.
Similarly, the outlet that removes water pipe 82 skew and be higher than the nadir of water tank towards the water tank front is provided with short tube or manger 88 between the diapire 83 of this outlet and water tank.As a result, when aircraft dived in landing with during landing, shown in Figure 10 c, fuel level rose on the top of short column 88, entered into except that water pipe 82 interior and entering Fuel Tanks 89.
Thereby the structure of Figure 10 a-10c can be worked under the situation that does not have the pitch control cock.Another advantage of native system is shown in Figure 10 c, when this system in most of fuel is turned from case in landing with during landing is self-priming.Water tank has big area (as from above finding) and is long along heading so that take off with land during the maximization of pitch angle effect.Because water tank is long and flat,, and therefore more likely need induction pipe to cause extra suction at the pump intake place so pressure head will be less than the pressure head in preceding embodiment.Hydrostatic pressure is attempted to cause when current get into water tank 81 from removing water pipe 82 with drain hose 84 during refueling, and possibly need check valve 85 in the drain hose 84.Under the situation that does not have check valve 85, fuel will will be stayed Fuel Tank along drain hose 84 upwards mobile (because fuel is lighter) and water.
Although described the present invention in the above according to one or more preferred implementations, should be understood that, do not breaking away under the situation of liking the scope of the present invention that claim limits enclosed, can carry out various changes or modification.
Claims (27)
1. a utilization removes water pipe and from Fuel Tank, removes the method for anhydrating; The said pipe that dewaters has water-immersed inlet and is connected to the outlet of water tank; Wherein said inlet is dipped in the bottom and the water under said outlet that is in said Fuel Tank; Said method comprises: said Fuel Tank is full of fuel, and fuel applies hydrostatic pressure to water thus, and said hydrostatic pressure overcomes gravity forces water to remove the water pipe rising and get into said water tank along said; And with water from said water tank in drain hose is fed to driving engine.
2. method according to claim 1, this method also comprises: utilize hydrostatic pressure that water is conducted in the fuel pipe of engine from said water tank.
3. method according to claim 1 and 2, wherein, said Fuel Tank is an aircraft fuel tank.
4. method according to claim 3, this method also comprises: respond said aircraft effective pitch increase and open the valve in the said drain hose.
5. method according to claim 4, this method also comprises: respond the reducing of effective pitch of said aircraft and open the said valve in the said drain hose.
6. one kind is used for removing the water removal system that anhydrates from Fuel Tank, and said water removal system comprises:
Water tank;
Remove water pipe, the said pipe that dewaters has the outlet that is connected to said water tank; And
Drain hose, said drain hose has the inlet that is connected to said water tank, and can be connected to the outlet of the fuel pipe of engine in use,
Wherein, The said pipe that dewaters has inlet; Said inlet can be dipped into the bottom that is in said Fuel Tank and in use in the said water that removes under the said outlet of water pipe, and hydrostatic pressure can overcome gravity and forces said water to rise and get into said water tank along the said water pipe that removes thus.
7. system according to claim 6, this system also are included in the said check valve that removes in the water pipe.
8. system according to claim 6, wherein, said position of removing the said outlet of water pipe is higher than the nadir of said water tank.
9. system according to claim 8, wherein, the wall that a said part of removing water pipe is passed said water tank extends.
10. according to Claim 8 or 9 described systems, wherein, the said said outlet that removes water pipe comprises the guide of the bottom of pointing to said water tank.
11. system according to claim 6, this system also is included in the valve in the said drain hose.
12. system according to claim 11, wherein, the said valve in said drain hose be configured to respond this valve effective angle change and open and close.
13. system according to claim 12, wherein, said valve has closed condition, and said valve stops the water flows in the said drain hose under said closed condition; And forward open mode and reverse opening state, said valve allows water to flow through said valve under said forward open mode and reverse opening state,
Wherein, the increase that is configured to respond the effective angle of said valve of said valve changes to its forward open mode from its closed condition; And said valve be configured to respond said valve effective angle reduce change to its reverse opening state from its closed condition.
14. system according to claim 6, this system are configured to from aircraft fuel tank, remove and anhydrate, the said inlet of wherein said drain hose squints towards the back of said water tank with respect to the heading of said aircraft.
15. system according to claim 14, wherein, the said inlet of said drain hose is higher than the nadir of said water tank.
16. according to claim 14 or 15 described systems, this system also is included in the check valve in the said drain hose.
17. system according to claim 6, this system are configured to from aircraft fuel tank, remove and anhydrate, the wherein said said outlet that removes water pipe is squinted towards the front of said water tank with respect to the heading of said aircraft.
18. system according to claim 6, this system are configured to from aircraft fuel tank, remove and anhydrate, the wherein said said outlet that removes water pipe is positioned in the front of the said inlet of said drain hose with respect to the heading of said aircraft.
19. system according to claim 6, wherein, said water tank has opening at its top, and said opening can permit fuel to flow into said water tank in use.
20. system according to claim 6, wherein, the horizontal vertical ratio of said water tank is greater than 2.
21. system according to claim 20, wherein, the horizontal vertical ratio of said water tank is greater than 4.
22. a fuel tank system, said fuel tank system comprises:
Fuel Tank;
The fuel pipe of engine; And
According to the described water removal system of one of claim 6 to 21; Said water removal system is installed into: the said outlet of said drain hose links to each other with the said fuel pipe of engine; The said said inlet that removes water pipe immerses in the water of said fuel tank bottom; And the said said outlet that removes water pipe is connected to the said water tank on the said inlet, and hydrostatic pressure can overcome gravity and forces water to rise and get into said water tank along the said water pipe that removes thus.
23. system according to claim 22, this system also comprises the fuel pipe of engine that is connected to said water tank and said Fuel Tank parallelly connectedly.
24. according to claim 22 or 23 described systems, this system also comprises the pump that is connected to said water tank and said Fuel Tank parallelly connectedly.
25. according to claim 22 or 23 described systems, wherein, said Fuel Tank is an aircraft fuel tank.
26. according to claim 22 or 23 described systems, wherein, the volume of said water tank is less than 1% of said propellant capacity.
27. system according to claim 26, wherein, the volume of said water tank is less than 0.1% of said propellant capacity.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0704725A GB0704725D0 (en) | 2007-03-12 | 2007-03-12 | Water Scavenging System |
| GB0704725.1 | 2007-03-12 | ||
| GB0710621.4 | 2007-06-04 | ||
| GB0710621A GB0710621D0 (en) | 2007-06-04 | 2007-06-04 | Water scavenging system |
| PCT/GB2008/050156 WO2008110838A1 (en) | 2007-03-12 | 2008-03-05 | Water scavenging system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101631718A CN101631718A (en) | 2010-01-20 |
| CN101631718B true CN101631718B (en) | 2012-11-14 |
Family
ID=37988808
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2008800080494A Expired - Fee Related CN101631718B (en) | 2007-03-12 | 2008-03-05 | Water scavenging system |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN101631718B (en) |
| GB (1) | GB0704725D0 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102313112A (en) * | 2011-06-03 | 2012-01-11 | 哈尔滨飞机工业集团有限责任公司 | Depositing tank for pitot-static systems |
| FR3014134B1 (en) * | 2013-12-04 | 2015-12-11 | Snecma | DEVICE FOR RETAINING DRAIN FLUIDS FOR A PROPULSIVE ASSEMBLY |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1581595A (en) * | 1924-07-12 | 1926-04-20 | Herbert C Osborne | Valve |
| US3079941A (en) * | 1959-12-28 | 1963-03-05 | Douglas Aircraft Co Inc | Fuel tank drain system |
| US4809934A (en) * | 1987-02-12 | 1989-03-07 | British Aerospace Public Limited Company | On-board disposal of water in aircraft fuel tanks |
| GB2241443A (en) * | 1990-02-28 | 1991-09-04 | Mtu Friedrichshafen Gmbh | Fuel separator with automatic water drainage |
| US6170470B1 (en) * | 1999-07-09 | 2001-01-09 | Brunswick Corporation | Fuel supply system for an internal combustion engine |
-
2007
- 2007-03-12 GB GB0704725A patent/GB0704725D0/en not_active Ceased
-
2008
- 2008-03-05 CN CN2008800080494A patent/CN101631718B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1581595A (en) * | 1924-07-12 | 1926-04-20 | Herbert C Osborne | Valve |
| US3079941A (en) * | 1959-12-28 | 1963-03-05 | Douglas Aircraft Co Inc | Fuel tank drain system |
| US4809934A (en) * | 1987-02-12 | 1989-03-07 | British Aerospace Public Limited Company | On-board disposal of water in aircraft fuel tanks |
| GB2241443A (en) * | 1990-02-28 | 1991-09-04 | Mtu Friedrichshafen Gmbh | Fuel separator with automatic water drainage |
| US6170470B1 (en) * | 1999-07-09 | 2001-01-09 | Brunswick Corporation | Fuel supply system for an internal combustion engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101631718A (en) | 2010-01-20 |
| GB0704725D0 (en) | 2007-04-18 |
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