阅读说明：本技术 三轮式燃油箱惰化装置及其控制方法 (Three-wheel type fuel-tank inert gas device and its control method ) 是由 薛勇 张斌 郭军亮 岳鹏 田玉雯 江华 于 2019-09-03 设计创作，主要内容包括：本发明涉及一种用于飞行器的三轮式燃油箱惰化装置,包括：动力涡轮(10)；降压涡轮(11)；增压涡轮(2)；以及与增压涡轮(2)连通的空气分离器(7)。动力涡轮(10)借助第一电动离合器(14)与增压涡轮(2)同轴连接或断开连接,和/或借助第二电动离合器(15)与降压涡轮(11)同轴连接或断开连接。空气分离器(7)将进入其中的压缩空气分离成富氧气体(8)和富氮气体(9),富氧气体(8)在飞行器处于低海拔高度时被送入降压涡轮(11)以降低富氧气体(8)的压力,富氮气体(9)在飞行器处于高海拔高度时被送入动力涡轮(10)以降低动力涡轮(10)的负载。上述燃油箱惰化装置一方面能够在飞行器处于低海拔高度时提高空气分离器的性能,另一方面能够在飞行器处于高海拔高度时改善增压效果。(The present invention relates to a kind of Three-wheel type fuel-tank inert gas devices for aircraft, comprising: power turbine (10)；It is depressured turbine (11)；Charging turbine (2)；And the air separator (7) being connected to charging turbine (2).Power turbine (10) is coaxially connected by the first electric clutch (14) and charging turbine (2) or disconnects, and/or coaxially connected by the second electric clutch (15) and decompression turbine (11) or disconnect.Air separator (7) will enter compressed air therein and be separated into oxygen rich gas (8) and nitrogen-rich gas (9), oxygen rich gas (8) is admitted to decompression turbine (11) when aircraft is in low altitude area height to reduce the pressure of oxygen rich gas (8), and nitrogen-rich gas (9) is admitted to power turbine (10) when aircraft is in High aititude height to reduce the load of power turbine (10).On the one hand above-mentioned fuel-tank inert gas device can improve the performance of air separator when aircraft is in low altitude area height, on the other hand can improve supercharging effect when aircraft is in High aititude height.)

1. a kind of Three-wheel type fuel-tank inert gas device for aircraft, comprising:

Power turbine (10)；

It is depressured turbine (11)；

Charging turbine (2)；And

The air separator (7) being connected to the charging turbine (2),

It is characterized in that,

The power turbine (10) is coaxially connected by the first electric clutch (14) and the charging turbine (2) or disconnection connects It connects, and/or coaxially connected by the second electric clutch (15) and the decompression turbine (11) or disconnect, and

The air separator (7) will enter compressed air therein and be separated into oxygen rich gas (8) and nitrogen-rich gas (9),

The oxygen rich gas (8) is admitted to the decompression turbine (11) when the aircraft is in low altitude area height to reduce The pressure of oxygen rich gas (8) is stated, the nitrogen-rich gas (9) is admitted to the power when the aircraft is in High aititude height Turbine (10) is to reduce the loads of the power turbine (10).

2. Three-wheel type fuel-tank inert gas device as described in claim 1, which is characterized in that the charging turbine (2), described dynamic Power turbine (10) and the decompression turbine (11) are coaxially connected, and pass through first electric clutch (14) and described second One or two of electric clutch (15) disconnects.

3. Three-wheel type fuel-tank inert gas device as described in claim 1, which is characterized in that the charging turbine (2) and high pressure Gas source (1) connection, the temperature of the high-pressure air source (1) are controlled as lower than 120 DEG C.

4. Three-wheel type fuel-tank inert gas device as described in claim 1, which is characterized in that the charging turbine (2) successively connects It connects ozone converter (3) and filter (4) and is finally connected with the air separator (7).

5. Three-wheel type fuel-tank inert gas device as claimed in claim 4, which is characterized in that the filter (4) with it is described It is provided with temperature sensor (5) and/or pressure sensor (6) between air separator (7), the air separation is entered with detection The temperature and/or pressure of the compressed air of device (7).

6. a kind of method for controlling Three-wheel type fuel-tank inert gas device as described in claim 1, includes the following steps:

(i) when the Three-wheel type fuel-tank inert gas device is in low altitude area mode, first electric clutch (14) is disconnected And it is closed second electric clutch (15), will be sent by the oxygen rich gas (8) that the air separator (7) are separated The decompression turbine (11) is simultaneously ultimately discharged into atmosphere；

(ii) when the Three-wheel type fuel-tank inert gas device is in H/A mode, it is closed first electric clutch (14) And second electric clutch (15) is disconnected, will be sent by the nitrogen-rich gas (9) that the air separator (7) are separated The power turbine (10) is to reduce the loads of the power turbine (10), and nitrogen-rich gas (9) is discharged into fuel tank (13) later.

7. method as claimed in claim 6, which is characterized in that determine the Three-wheel type fuel tank using critical altitude (H) Inerting unit should be at H/A mode or low altitude area mode.

Technical field

The present invention relates to a kind of Three-wheel type fuel-tank inert gas devices, and control this Three-wheel type fuel-tank inert gas device Method.

Background technique

According to the investigation result for domestic and international great flight safety accident, aircraft fuel tank catches fire explosion to people on machine Member and equipment safety have significant threat.Therefore, aircraft fuel tank explosion accident probability how is reduced as aircraft security The research emphasis of problem.Show that aircraft fuel-tank inert gas is a kind of cost-effective with result of study through a large number of experiments Fire-proof and explosion-proof mode.

Fuel-tank inert gas refers to: the gas phase of aircraft fuel tank is filled with using inert gas such as nitrogen, carbon dioxide etc. Space displaces the oxygen in the gas-phase space, to reduce the oxygen content in fuel tank, oxygen concentration is caused to reach flammable pole Limit is following.By inerting disposal, even if encountering external incendiary source, explosion on fire will not occur for aircraft fuel tank.Therefore, it fires Fuel tank inerting technology is widely adopted at present.

Airborne nitrogen inerting system processed is that the technology, which utilizes, starts power traction with most extensive and mature fuel-tank inert gas technology Gas, by Middle hollow fiber membrane nitrogen and oxygen, nitrogen-rich gas required for generating is passed through fuel tank gas-phase space, is dropped with this Oxygen concentration in low gas-phase space.For example, in the European patent application submitted by HAMILTON SUNDSTRAND company Such a fuel tank Inert systems for aircraft are just described in EP3241757A1.The system is increased using engine bleed Pressure is to reduce the oxygen concentration in gas-phase space.But the technology is very high to bleed pressure requirement, and hollow fiber membrane nitrogen There are low efficiency, the service life is short, easy blocking, the disadvantages of generating pollution to environment.

Furthermore by Nanjing Aero-Space University in the Chinese patent application submitted on December 21st, 2017 A kind of airborne oxygen generation-nitrogen generation coupling system with expanding machine is disclosed in CN107840315A.Within the system, engine is come from The bleed of compressor is divided into two-way after pressure stabilizing, cooling, drives two sets of charging turbines, another way quilt to expanding machine acting all the way By hollow fiber membrane nitrogen system after the boosting of first charging turbine, nitrogen-rich gas is produced for inerting aircraft fuel tank.By It also needs in this oxygen generation-nitrogen generation coupling system using hollow fiber membrane nitrogen system, therefore before being inevitably present The many disadvantages.

For this purpose, in the industry also it has been suggested that using the solution route substituted to nitrogen-rich gas pressurization with bleed pressurization.For example, It is empty that a kind of low-power richness nitrogen is described in the United States Patent (USP) US6913636B2 submitted by HAMILTON SUNDSTRAND company Gas generating system.The nitrogen-rich gas (NEA) for being mainly characterized by being separated using air separator of the system does work to turbine, It the advantage is that the high pressure that can use NEA improves the inlet pressure of ASM, and then improve the purity and flow of separation of nitrogen.But , since ground stage atmospheric pressure is larger, to cause inside and outside seperation film pressure difference minimum, the performance of air separator therefore under Drop.

Therefore, need to develop a kind of improved Three-wheel type fuel-tank inert gas device at present.

Summary of the invention

The purpose of the present invention is to provide one kind, and air separator can be improved when aircraft is in low altitude area height Performance and the fuel-tank inert gas device for improving supercharging effect when aircraft is in High aititude height.

The first aspect of the present invention is related to a kind of Three-wheel type fuel-tank inert gas device for aircraft, comprising: power whirlpool Wheel；It is depressured turbine；Charging turbine；And the air separator being connected to charging turbine.Power turbine is by the first electric clutch Device and charging turbine are coaxially connected or disconnect, and/or coaxially connected or disconnected by the second electric clutch and decompression turbine Connection is opened, and air separator will enter compressed air therein and be separated into oxygen rich gas and nitrogen-rich gas, oxygen rich gas exists Aircraft is admitted to decompression turbine to reduce the pressure of oxygen rich gas when being in low altitude area height, nitrogen-rich gas is in aircraft Power turbine is admitted to when High aititude height to reduce the load of power turbine.

It is preferred that charging turbine, power turbine and decompression turbine can be coaxially connected, and pass through the first electric clutch One or two of device and the second electric clutch disconnect.

It is preferred that charging turbine can be connected to high-pressure air source, the temperature of high-pressure air source be preferably controlled for lower than 120 DEG C or high temperature gas source are cooled to lower than 120 DEG C.

It is preferred that charging turbine can be sequentially connected ozone converter and filter and finally be connected with air separator It is logical.

More preferably, it is provided with temperature sensor and/or pressure sensor, between filter and air separator with inspection Survey the temperature and/or pressure for entering the compressed air of air separator.

The second aspect of the present invention is related to a kind of side for controlling Three-wheel type fuel-tank inert gas device as described in relation to the first aspect Method includes the following steps:

(i) when Three-wheel type fuel-tank inert gas device is in low altitude area mode, the first electric clutch and second is disconnected The oxygen rich gas separated by air separator is sent into decompression turbine and is ultimately discharged into atmosphere by electric clutch；

(ii) it when Three-wheel type fuel-tank inert gas device is in H/A mode, is closed the first electric clutch and disconnects The nitrogen-rich gas separated by air separator is sent into power turbine to reduce the negative of power turbine by the second electric clutch It carries, nitrogen-rich gas is discharged into fuel tank later.

It is preferred that can use critical altitude to determine that Three-wheel type fuel-tank inert gas device should be at H/A mode Or low altitude area mode.

The advantages of above-mentioned each technical solution is: Three-wheel type fuel-tank inert gas device of the invention and its control method can Aircraft fuel tank is protected, prevent that burning occurs inside fuel tank and and then causes explosion.The fuel-tank inert gas device is logical It crosses and increases oxygen-enriched side inside and outside differential pressure, and increase the infiltration of oxygen-enriched side oxygen molecule, and then improve the purity of nitrogen-rich gas, so that fuel oil Case quickly reaches non-flammable safe condition.

It can be seen that the innovation of the invention consists in that:

(1) expansion decompression is carried out using gas exhaust piping of the high revolving speed of power turbine to oxygen rich gas, reduces oxygen rich gas Pressure at expulsion, the pressure difference of air separator two sides can be increased in this way, to increase the infiltration capacity of oxygen, and improve rich nitrogen Purity of the gas in exit；

(2) switch of the first and second electric clutch of structure matching based on Three-wheel type fuel-tank inert gas device, can be with The working condition for neatly controlling inerting system, to can obtain optimal work shape when aircraft is in different height State.

Detailed description of the invention

The structure and control method of Three-wheel type fuel-tank inert gas device in order to further illustrate the present invention, below in conjunction with The present invention is described in detail for the drawings and specific embodiments, in which:

Fig. 1 is the operation principle schematic diagram of fuel-tank inert gas device of the invention；

Fig. 2 shows a preferred embodiments of fuel-tank inert gas device according to the present invention.

Description of symbols

1 high-pressure air source

2 charging turbines

3 ozone converters

4 filters

5 temperature sensors

6 pressure sensors

7 air separators

8 oxygen rich gas (OEA)

9 nitrogen-rich gas (NEA)

10 power turbines

11 decompression turbines

12 Flame arresters

13 fuel tanks

14 first clutches

15 second clutches

Specific embodiment

Illustrate the structure and its control method of Three-wheel type fuel-tank inert gas device of the invention with reference to the accompanying drawing, wherein Identical component is indicated by identical appended drawing reference.

As shown in Figure 1, the figure shows the working principles of fuel-tank inert gas device of the invention.It can be seen that aircraft Power turbine T₁By the first electric clutch L₁It is coaxially connected or disconnect and electronic by second with charging turbine C Clutch L₂With decompression turbine T₂It is coaxially connected or disconnect.That is, charging turbine, decompression turbine and power turbine are not It can be only driven, and can be disconnected by clutch by shaft work.

The present invention is using the high pressure gas of nitrogen-rich gas NEA in power turbine T₁Middle expansion working drives power turbine T₁'s On the one hand shaft rotation, shaft work can drive charging turbine C to be pressurized high-pressure air source, on the other hand can drive decompression whirlpool Take turns T₂The pressure of oxygen rich gas OEA exhaust ports is depressured.The pressure for reducing oxygen rich gas OEA exhaust ports can make air The pressure difference of separator two sides increases, and increases the infiltration capacity of oxygen, to improve the gas purity at nitrogen-rich gas NEA at mouth.By This, passes through two electric clutch L₁、L₂Power turbine T can be controlled₁Load.

Fig. 2 shows a preferred embodiments of fuel-tank inert gas device according to the present invention.

As shown in Fig. 2, the Three-wheel type fuel-tank inert gas device for aircraft is mainly by power turbine 10, decompression turbine 11, charging turbine 2 and air separator 7 are constituted.Due to these components fuel-tank inert gas device structure and function for this It is well-known for the those of ordinary skill in field, omits the specific descriptions for each component herein.Aircraft moves Power turbine 10 is coaxially connected by the first electric clutch 14 and charging turbine 2 or disconnects, and/or by second it is electronic from Clutch 15 and decompression turbine 11 are coaxially connected or disconnect.

It is preferred that charging turbine 2, power turbine 10 and decompression turbine 11 are coaxially connected, and the first electricity can be passed through Dynamic clutch 14 and/or the second electric clutch 15 disconnect.Specifically, the purposes of the first electric clutch 14 is control Whether it is driven by shaft work between charging turbine 2 and power turbine 10, and the purposes of the second electric clutch 15 is control decompression Whether rotated coaxially between turbine 11 and power turbine 10.

2 one side of charging turbine is connected to high-pressure air source 1, is on the other hand also sequentially connected ozone converter 3 and filter 4, and be finally connected with air separator 7.In the present embodiment, the temperature of high-pressure air source 1 is controlled as lower than 120 DEG C. Temperature sensor 5 and/or pressure sensor 6 can also be set between filter 4 and air separator 7, to detect entrance The temperature and/or pressure of the compressed air of air separator 7.

Using above-mentioned setting, air separator 7 will enter compressed air therein and be separated into oxygen rich gas and nitrogen-rich gas. In Fig. 2, oxygen rich gas and nitrogen-rich gas are indicated with appended drawing reference 8 and 9 respectively.Oxygen rich gas 8 is in low altitude area in aircraft Decompression turbine 11 is admitted to when height to reduce the pressure of oxygen rich gas 8, nitrogen-rich gas 9 is when aircraft is in High aititude height Power turbine 10 is admitted to reduce the load of power turbine 10.

More specifically, when aircraft is in low altitude area height (i.e. fuel-tank inert gas device is in low altitude area mode), First electric clutch 14 is in an off state and the second electric clutch 15 is in closed state.At this point, oxygen rich gas 8 is sent Enter to be depressured turbine 11 and be ultimately discharged into atmosphere, to reduce the pressure of oxygen rich gas 8, to improve the work effect of air separator 7 Rate.

When aircraft is in High aititude height (i.e. fuel-tank inert gas device is in H/A mode), the first electric clutch Device 14 is in closed state and the second electric clutch 15 is in an off state.At this point, nitrogen-rich gas 9 is admitted to power turbine 10 To reduce the load of power turbine 10, nitrogen-rich gas 9 is discharged into fuel tank 13 later.

Low altitude area height and High aititude height are distinguished using critical altitude H.H is for the common of this field for the critical altitude Its optimum value can be obtained by test using the knowledge of this field for technical staff.Therefore, it omits herein for critical height Degree H's further describes, because this is unrelated with the innovative point of the application.

In addition, Flame arrester 12 can also be arranged between power turbine 10 and fuel tank 13, enter fuel oil to control The oxygen-enriched air amount of case.

The control method of Three-wheel type fuel-tank inert gas device according to the present invention will be simply introduced below.

Specifically, under low altitude area altitudes, since atmospheric pressure is higher, the pressure at expulsion for reducing oxygen rich gas can be with The efficiency of air separator is significantly improved, therefore the control method of Three-wheel type fuel-tank inert gas device is the following steps are included: disconnect First electric clutch and the second electric clutch of closure, the oxygen rich gas separated by air separator is sent into and is depressured Turbine 11 is simultaneously ultimately discharged into atmosphere, to reduce the pressure of oxygen rich gas, to improve the working efficiency of air separator

Under High aititude altitudes, since atmospheric pressure is lower, engine charge pressure frequently results in height with reduction The pressure reduction of pressurized air source.At this point, increasing the property that can dramatically increase air separator into the gas pressure of air separator Energy.In addition, the pressure at expulsion for reducing oxygen rich gas cannot significantly improve air separation since upper atmosphere pressure is already close to vacuum The efficiency of device.Therefore the control method of Three-wheel type fuel-tank inert gas device is the following steps are included: be closed the first electric clutch simultaneously And the second electric clutch is disconnected, the nitrogen-rich gas separated by air separator is sent into power turbine to reduce power whirlpool The load of wheel, nitrogen-rich gas is discharged into fuel tank to obtain better supercharging effect later.

Equally, between low altitude area height and High aititude height, there are such a critical altitude H: as flying height≤H When, it disconnects the first electric clutch and is closed the second electric clutch, that is, fuel-tank inert gas device is in low altitude area mode； As flying height > H, it is closed the first electric clutch and disconnects the second electric clutch, that is, fuel-tank inert gas device is in H/A mode.Therefore, it can use critical altitude H to determine that fuel-tank inert gas device should be at H/A mode or low Altitude mode.

Although combining preferred embodiment above to working principle, the structure of Three-wheel type fuel-tank inert gas device of the invention And its control method is illustrated, but those of ordinary skill in the art is it should be appreciated that above-mentioned example is only For what is illustrated, and it cannot function as limitation of the present invention.It therefore, can be in the spirit of claims to this Invention is modified and modification, within the scope of these modifications and variations will all be fallen in required by claims of the present invention.