An electrically driven inerting system and method of adjustment

Abstract

The application discloses a self-adaptable electric drive inerting system and a regulating method, and the system comprises an air source, a silencer, a first filter, a cut-off valve, a first air compressor, a motor, a second air compressor, a first temperature sensor, a first flow regulating valve, a cooling air source, a second flow regulating valve, a three-loop heat exchanger, an ejector, a discharge device, a second filter, an ozone converter, a second temperature sensor, a second pressure sensor, an air separation device, a first oxygen concentration sensor, a flow sensor, a third flow regulating valve, a one-way valve, a flame suppressor, a third pressure sensor, a third temperature sensor, a second oxygen concentration sensor and a fuel tank. The application can effectively solve the problems of high engine compensation loss and poor system regulation caused by engine bleed air.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft fuel tank fire prevention and explosion suppression, and relates to a self-adaptive electric drive inerting system and a regulating method. BACKGROUND

[0002] Since the 1970s, aircrafts are often equipped with on-board hollow fiber membrane nitrogen inerting systems. The system provides a certain pressure and temperature air source to the membrane separation device through engine bleed air, and realizes the separation of oxygen and nitrogen by relying on the difference in the permeation rate of oxygen and nitrogen in the hollow fiber membrane. Due to its economic efficiency and other advantages, the system has become the most widely used aircraft fuel tank inerting system. However, from the application status in recent years, the inerting system still has many problems, such as large compensation loss of the aircraft due to the need for engine bleed air, limited use occasions due to the high required pressure at the system inlet, membrane wire blockage, and serious membrane performance degradation due to ozone sensitivity, etc.

[0003] Some people use a pressurization method to increase the engine bleed air pressure and increase the inlet pressure of the membrane separation device to improve the nitrogen production efficiency. Some people use a coupling system of aircraft cabin environmental control and on-board nitrogen production to solve the problem of low engine bleed air pressure during aircraft idling flight, which leads to low nitrogen production system efficiency or inability to work. However, these measures cannot fundamentally solve the problem of high engine compensation loss caused by engine bleed air. SUMMARY

[0004] In view of the shortcomings of the existing inerting system, such as high engine compensation loss caused by engine bleed air and poor system regulation, the application provides a self-adaptive electric drive inerting system.

[0005] In order to achieve the above-mentioned task, the application adopts the following technical solutions:

[0006] A self-adaptive electric drive inerting system, comprising: an air source, a silencer, a first filter, a shut-off valve, a first air compressor, an electric motor, a second air compressor, a first temperature sensor, a first flow regulating valve, a cooling air source, a second flow regulating valve, a three-circuit heat exchanger, an ejector, a discharge device, a second filter, an ozone converter, a second temperature sensor, a second pressure sensor, an air separation device, a first oxygen concentration sensor, a flow sensor, a third flow regulating valve, a check valve, a flame arrestor, a third pressure sensor, a third temperature sensor, a second oxygen concentration sensor, and a fuel tank; wherein:

[0007] The air source is connected with the silencer, the first filter, the cut-off valve and the first air compressor inlet in sequence through pipes; the motor is a double-output shaft motor, the power end of the first air compressor is connected with one output shaft of the motor, and the other output shaft of the motor is connected with the second air compressor; the first air compressor outlet is connected with the first hot end loop inlet of the three-loop heat exchanger and the motor cooling channel respectively; wherein, the three-loop heat exchanger comprises a first hot end loop inlet, a first hot end loop outlet, a second hot end loop inlet, a second hot end loop outlet, a cold end inlet and a cold end outlet; the air source can be drawn from the cargo cabin, the passenger cabin or the external environment;

[0008] The first hot end loop outlet of the three-loop heat exchanger is connected with the second air compressor inlet through a pipe, the second air compressor outlet is divided into two paths through a three-way pipe, one path is connected with the first flow regulating valve inlet, and the other path is connected with the second hot end loop inlet of the three-loop heat exchanger; the first flow regulating valve outlet is connected with the ejector bypass inlet end through a pipe; the first temperature sensor is installed on the pipeline between the second air compressor and the three-way pipe, and the first flow regulating valve is used for discharging part of the high-pressure gas at the second air compressor outlet to the external environment through the exhaust device;

[0009] The cooling air source, the second flow regulating valve and the cold end inlet of the three-loop heat exchanger are connected in sequence through pipes, the cold end outlet of the three-loop heat exchanger is connected with the ejector inlet through a pipe, and the ejector outlet is connected with the exhaust device through a pipe;

[0010] The second hot end loop outlet of the three-loop heat exchanger is connected with the second filter, the ozone converter and the air inlet of the air separation device in sequence through pipes, the oxygen-enriched gas outlet of the air separation device is connected with the exhaust device through a pipe, and the oxygen-enriched gas is discharged to the outside of the machine;

[0011] The nitrogen-rich gas outlet of the air separation device is connected with the third flow regulating valve, the one-way valve, the flame suppressor and the fuel tank gas inlet in sequence through pipes; the first oxygen concentration sensor and the flow sensor are arranged on the pipeline between the air separation device and the third flow regulating valve; the third pressure sensor, the third temperature sensor and the second oxygen concentration sensor are installed in the fuel tank.

[0012] Further, before the ground takes off, the ejector passes the high-pressure gas from the second air compressor outlet through the exhaust device, and the external environment of the cooling air source enters the three-loop heat exchanger under the action of the ejector, so that the three-loop heat exchanger realizes cooling heat exchange in the ground state; in the flight process, the ram air source is continuously generated into the cold end of the three-loop heat exchanger by relying on the flight speed.

[0013] Further, the air separation device comprises an air inlet, a nitrogen-rich gas outlet, an oxygen-rich gas outlet; a second temperature sensor and a second pressure sensor are arranged on the pipeline between the ozone converter and the air separation device; wherein the second filter is used for fine filtering the second hot end outlet gas of the three-loop heat exchanger.

[0014] Further, the system further comprises a controller, the controller comprising a signal input end and a signal output end, the first temperature sensor, the second temperature sensor, the second pressure sensor, the first oxygen concentration sensor, the flow sensor, the third pressure sensor, the third temperature sensor, and the second oxygen concentration sensor being connected to the signal input end of the controller through cables; the cut-off valve, the motor, the first flow regulating valve, the second flow regulating valve, and the third flow regulating valve being connected to the signal output end of the controller through cables.

[0015] Further, the first oxygen concentration sensor is used for monitoring the oxygen volume fraction of the outlet gas of the air separation device, and the separation performance of the air separation device is calculated in combination with the flow data of the flow sensor and the oxygen volume fraction data of the second oxygen concentration sensor under a certain working temperature and pressure, so as to determine whether the air separation device needs to be maintained or replaced; the flow sensor is used for monitoring the flow of the nitrogen-rich gas at the outlet of the air separation device, which is one of the data for determining the separation performance of the air separation device; the required nitrogen-rich gas flow is calculated according to the temperature, pressure, and oxygen volume fraction in the gas phase space in the fuel tank, and the third flow regulating valve is adjusted through the monitoring data of the flow sensor to achieve the required nitrogen-rich gas flow; the second oxygen concentration sensor is used for monitoring the oxygen volume fraction in the gas phase space in the fuel tank, and provides the oxygen volume fraction data in the gas phase space in the fuel tank for the controller.

[0016] Further, the normal working mode of the system is as follows:

[0017] Under the action of the motor-driven first compressor, the air of the air source successively passes through the silencer, the first filter, and the cut-off valve, and enters the first compressor after being preliminarily filtered of impurities to be pressurized and heated, most of the gas pressurized and heated enters the three-loop heat exchanger to be cooled, a part of the gas enters the motor cooling channel to take away the heat generated by the motor, the gas cooled by the three-loop heat exchanger further enters the second compressor to be further pressurized and heated, a part of the gas pressurized and heated by the second compressor enters the ejector after the first flow regulating valve; in the ground preparation stage, the first flow regulating valve is opened, and the high-temperature and high-pressure gas at the outlet of the second compressor drives the ambient air of the cooling air source to enter the cold end of the three-loop heat exchanger through the second flow regulating valve, so that the three-loop heat exchanger is cooled and heat-exchanged in the ground state; in the high-altitude flight stage, the cooling air source is supplied with the ambient ram air generated by the flight speed, and the first flow regulating valve is closed at this time.

[0018] The second compressor pressurized and heated gas enters the three-loop heat exchanger for cooling and heat exchange at ground state or all at high altitude state, the cooled and reduced temperature gas enters the second filter to further remove impurities, and then enters the ozone converter to remove trace ozone contained in the gas, and then in the air separation device, the oxygen and nitrogen in the air are separated by using the principle that the oxygen and nitrogen have different permeation rates in the hollow fiber membrane, to form an oxygen-rich gas which is discharged to the outside environment, and the remaining nitrogen-rich gas is sent to the fuel tank through the third flow regulating valve, the one-way valve and the flame arrestor, to reduce the oxygen volume fraction in the upper gas phase space of the fuel tank, so as to achieve the inerting state of the fuel tank.

[0019] Further, the high-temperature protection mode of the system is:

[0020] The first temperature sensor monitors the temperature of the gas at the outlet of the second compressor, and when the temperature information monitored by the first temperature sensor exceeds the first temperature preset value for a certain time, the controller sends a control instruction to the motor to reduce the rotating speed of the motor driving the second compressor;

[0021] The second temperature sensor and the second pressure sensor monitor the temperature and pressure information at the inlet of the air separation device, respectively, and when the temperature information monitored by the second temperature sensor exceeds the second temperature preset value or the pressure information monitored by the second pressure sensor exceeds the pressure preset value, the controller sends a control instruction to the motor to reduce the rotating speed of the motor driving the second compressor; when the temperature information monitored by the second temperature sensor or the pressure information monitored by the second pressure sensor still exceeds the second temperature preset value and the pressure preset value within a preset time, the controller sends a control instruction to open the cut-off valve, and then the controller sends a control instruction to close the motor, and the system enters the high-temperature protection mode.

[0022] A real-time adaptive adjustment method of an electric drive inerting system that can be adaptively adjusted, comprising the following steps:

[0023] The controller receives the ambient temperature and pressure information sent by the aircraft central computer, and the pressure, temperature and oxygen concentration information of the fuel tank monitored by the third pressure sensor, the third temperature sensor and the second oxygen concentration sensor;

[0024] The controller analyzes the relationship between the flow and concentration of the nitrogen-rich gas generated by the air separation device, and calculates the flow of the nitrogen-rich gas required to achieve the inerting state of the fuel tank according to the internal calculation program of the controller;

[0025] The controller judges whether the nitrogen-rich gas flow rate expectation value is same as the air separation device outlet nitrogen-rich gas flow rate monitored by the current flow sensor, if same, the controller does not make any adjustment to the system, and enters the calculation of next moment; if not same, the controller signal output end transmits control instruction to adjust the motor speed and the third flow regulating valve opening to achieve the expected nitrogen-rich gas flow rate, and then enters the calculation of next moment.

[0026] Compared with the prior art, the application has the following technical features:

[0027] 1. The electric drive inerting system of the application relies on electric power to drive the secondary air compressor to provide air separation device with air of certain temperature and pressure, the system only needs power supply, and the air source can come from the cargo cabin, passenger cabin and external environment, etc., solving the problem of high system compensation loss caused by engine bleed air in traditional membrane separation nitrogen inerting system.

[0028] 2. The electric drive inerting system of the application monitors the temperature, pressure and oxygen concentration in the fuel tank, and the temperature, pressure and oxygen concentration and flow rate information at the inlet and outlet of the air separation device in real time, and obtains the required nitrogen-rich gas flow rate and concentration through the real-time calculation of the built-in calculation program of the controller, and then outputs the control signal to the driving motor and the flow regulating valve, realizing the self-adaptive adjustment of the electric drive inerting system. BRIEF DESCRIPTION OF DRAWINGS

[0029] Figure 1 It is a schematic diagram of the electric drive inerting system which can be self-adaptively adjusted.

[0030] Figure 2 It is a schematic diagram of the self-adaptive adjustment of the electric drive inerting system.

[0031] Among them, 1 is an air source, 2 is a silencer, 3 is a first filter, 4 is a cut-off valve, 5 is a first air compressor, 6 is a motor, 7 is a second air compressor, 8 is a first temperature sensor, 9 is a first flow regulating valve, 10 is a cooling air source, 11 is a second flow regulating valve, 12 is a three-loop heat exchanger, 13 is an ejector, 14 is a discharge device, 15 is a second filter, 16 is an ozone converter, 17 is a second temperature sensor, 18 is a second pressure sensor, 19 is an air separation device, 20 is a first oxygen concentration sensor, 21 is a flow sensor, 22 is a third flow regulating valve, 23 is a check valve, 24 is a flame arrestor, 25 is a third pressure sensor, 26 is a third temperature sensor, 27 is a second oxygen concentration sensor, 28 is a fuel tank, and 29 is a controller. DETAILED DESCRIPTION

[0032] The application will be further described below in combination with embodiments, and the following description is only for some embodiments of the application, not all embodiments. Based on the embodiments of the application, all other embodiments obtained by those skilled in the art without creative labor are within the protection scope of the application.

[0033] The present application provides an airborne nitrogen generating and inerting system driven by a motor, which can obtain air from a cargo cabin, a passenger cabin or an external environment, and does not need to obtain air from an engine, thereby reducing system compensation loss, and having strong self-adaptive adjustment capacity and high system working efficiency.

[0034] Referring to the accompanying drawings, the present application provides an electrically driven inerting system with self-adaptive adjustment, comprising: an air source 1, a silencer 2, a first filter 3, a cut-off valve 4, a first air compressor 5, a motor 6, a second air compressor 7, a first temperature sensor 8, a first flow regulating valve 9, a cooling air source 10, a second flow regulating valve 11, a three-loop heat exchanger 12, an ejector 13, a discharge device 14, a second filter 15, an ozone converter 16, a second temperature sensor 17, a second pressure sensor 18, an air separation device 19, a first oxygen concentration sensor 20, a flow sensor 21, a third flow regulating valve 22, a one-way valve 23, a flame arrestor 24, a third pressure sensor 25, a third temperature sensor 26, a second oxygen concentration sensor 27 and a fuel tank 28; wherein:

[0035] The air source 1 is connected with the silencer 2, the first filter 3, the cut-off valve 4 and the inlet of the first air compressor 5 through pipes in sequence; the motor 6 is a double-output shaft motor, the power end of the first air compressor 5 is connected with one output shaft of the motor 6, and the other output shaft of the motor 6 is connected with the second air compressor 7; the outlet of the first air compressor 5 is connected with the first hot end loop inlet of the three-loop heat exchanger 12 and the cooling channel of the motor 6 respectively; wherein, the three-loop heat exchanger 12 comprises a first hot end loop inlet, a first hot end loop outlet, a second hot end loop inlet, a second hot end loop outlet, a cold end inlet and a cold end outlet; wherein, the air source 1 can obtain air from a cargo cabin, a passenger cabin or an external environment, thereby avoiding high compensation loss caused by obtaining air from an engine.

[0036] The first hot end loop outlet of the three-loop heat exchanger 12 is connected with the inlet of the second compressor 7 through a pipeline, the outlet of the second compressor 7 is divided into two paths through a three-way pipe, one of the two paths is connected with the inlet of the first flow regulating valve 9, and the other path is connected with the second hot end loop inlet of the three-loop heat exchanger 12; the outlet of the first flow regulating valve 9 is connected with the bypass inlet end of the ejector 13 through a pipeline; the first temperature sensor 8 is installed on the pipeline between the second compressor 7 and the three-way pipe; the first temperature sensor 8 is used for monitoring the outlet temperature of the second compressor 7, so as to avoid the irreversible damage of the second compressor caused by working in an overheated state. The first flow regulating valve 9 can make part of the high-pressure gas at the outlet of the second compressor 7 discharged to the external environment through the exhaust device, so as to expand the working envelope of the second compressor 7 and avoid the surge phenomenon of the second compressor 7 in a small flow state with a high pressure head. In the scheme, the first compressor 5 and the second compressor 7 are driven by a motor, compared with the compressor driven by a turbine on an airplane, the compressor in the scheme only needs to be powered, does not need to drive the turbine by ram air, has a simple structure and is more efficient; the rotating speed of the second compressor 7 is adjustable, and can be adjusted in real time according to the change of the system working state, so as to achieve the best working state.

[0037] The cooling air source 10, the second flow regulating valve 11 and the cold end inlet of the three-loop heat exchanger 12 are sequentially connected through pipelines, the cold end outlet of the three-loop heat exchanger 12 is connected with the inlet of the ejector 13 through a pipeline, and the outlet of the ejector 13 is connected with the exhaust device 14 through a pipeline. In the pre-flight preparation stage on the ground, the ejector 13 drives the external environment of the cooling air source 10 into the three-loop heat exchanger 12 through the exhaust device 14 under the action of the high-pressure gas from the outlet of the second compressor, so that the three-loop heat exchanger 12 realizes cooling and heat exchange in the ground state. In the flight process, the ram air source is continuously generated into the cold end of the three-loop heat exchanger 12 by relying on the flight speed.

[0038] The second hot end loop outlet of the three-loop heat exchanger 12 is sequentially connected with the second filter 15, the ozone converter 16 and the air inlet of the air separation device 19 through pipelines, the oxygen-enriched gas outlet of the air separation device 19 is connected with the exhaust device 14 through a pipeline, and the oxygen-enriched gas is discharged outside the machine; the air separation device 19 comprises an air inlet, a nitrogen-enriched gas outlet and an oxygen-enriched gas outlet; the second temperature sensor 17 and the second pressure sensor 18 are arranged on the pipeline between the ozone converter 16 and the air separation device 19; the second filter 15 can finely filter the gas at the second hot end outlet of the three-loop heat exchanger 12, and can filter out liquid and solid particles as small as 1 micrometer. In the scheme, the three-loop heat exchanger 12 is designed to cool and heat exchange the high-temperature gas at the outlets of the first compressor 5 and the second compressor 7, and the two hot end loops are integrated in one heat exchanger, which has the advantage of high integration degree, and can greatly reduce the volume and weight of the system.

[0039] The air separation device 19 nitrogen-rich gas outlet is connected with the third flow regulating valve 22, the one-way valve 23, the flame inhibitor 24, and the fuel tank 28 gas inlet in sequence through pipelines; the first oxygen concentration sensor 20 and the flow sensor 21 are arranged on the pipeline between the air separation device 19 and the third flow regulating valve 22; the third pressure sensor 25 and the third temperature sensor 26 are arranged in the fuel tank 28; and the second oxygen concentration sensor 27 is arranged in the fuel tank 28. The first oxygen concentration sensor 20 is used for monitoring the oxygen volume fraction of the gas at the outlet of the air separation device 19; the separation performance of the air separation device 19 is calculated by combining the flow data of the flow sensor 21 and the oxygen volume fraction data of the second oxygen concentration sensor 20 under a certain working temperature and pressure, and it is judged whether the air separation device 19 needs to be maintained or replaced. The flow sensor 21 is used for monitoring the flow of the nitrogen-rich gas at the outlet of the air separation device 19, and is used as one of the data for judging the separation performance of the air separation device 19; the required nitrogen-rich gas flow is calculated according to the temperature, pressure and oxygen volume fraction in the gas phase space in the fuel tank, and the third flow regulating valve 22 is adjusted by monitoring the data of the flow sensor 21 to achieve the required nitrogen-rich gas flow. The second oxygen concentration sensor 27 is used for monitoring the oxygen volume fraction in the gas phase space in the fuel tank 28, and provides the oxygen volume fraction data in the gas phase space in the fuel tank 28 for the controller 29.

[0040] The self-adaptable electric drive inerting system further comprises a controller 29, the controller 29 comprising a signal input end and a signal output end, the first temperature sensor 8, the second temperature sensor 17, the second pressure sensor 18, the first oxygen concentration sensor 20, the flow sensor 21, the third pressure sensor 25, the third temperature sensor 26, and the second oxygen concentration sensor 27 being connected with the signal input end of the controller 29 through cables; and the cut-off valve 4, the motor 6, the first flow regulating valve 9, the second flow regulating valve 11, and the third flow regulating valve 22 being connected with the signal output end of the controller 29 through cables.

[0041] The normal working mode of the present application is as follows:

[0042] As Figure 1As shown, the self-adaptable electric drive inerting system of the present application, the air source 1 can be one of the cargo cabin, passenger cabin and the external environment, under the action of the first air compressor 5 driven by the motor 6, the air of the air source 1 successively passes through the silencer 2, the first filter 3, the cut-off valve 4, and enters the first air compressor 5 after the impurities of the preliminary filtered air, and is pressurized and heated, most of the pressurized and heated gas enters the three-loop heat exchanger 12 for cooling, and a small part of the gas enters the motor 6 cooling channel to take away the heat generated by the motor 6, the gas cooled by the three-loop heat exchanger 12 enters the second air compressor 7 for further pressurization and heating, wherein the second air compressor 7 is driven by the motor 6, and the rotating speed is continuously adjustable, a part of the gas pressurized and heated by the second air compressor 7 enters the ejector 13 after the first flow regulating valve 9, in the ground preparation stage, since the cooling air source 10 has no ram air available, the first flow regulating valve 9 is opened, and the external environment air of the cooling air source 10 enters the cold end of the three-loop heat exchanger 12 through the second flow regulating valve 11, to realize the cooling heat exchange of the three-loop heat exchanger 12 in the ground state, in the high-altitude flight stage, the cooling air source 10 realizes the supply of the cold end gas source of the three-loop heat exchanger 12 by the ram air of the external environment generated by the flight speed, and the first flow regulating valve 9 is closed.

[0043] The gas pressurized and heated by the second air compressor 7 enters the three-loop heat exchanger 12 for cooling heat exchange in the ground state or in the high-altitude state, the cooled and cooled gas enters the second filter 15 for further removal of impurities, and then enters the ozone converter 16 to remove the trace ozone contained in the gas, and then in the air separation device 19, the oxygen is separated from the air by the principle that the oxygen and nitrogen have different permeation rates of the hollow fiber membrane, to form the oxygen-rich gas which flows to the external environment through the discharge device 14, and the remaining nitrogen-rich gas is sent into the fuel tank 28 through the third flow regulating valve 22, the one-way valve 23 and the flame arrestor 24, to reduce the oxygen volume fraction in the upper gas phase space of the fuel tank 28, so that the inerting state of the fuel tank 28 is realized.

[0044] When some components of the present application fail, for example, the heat exchanger 12 fails to normally exchange heat, the air inlet gas temperature of the air separation device 19 is too high, so that the air separation device 19 is damaged, in addition, when the internal temperature of the second air compressor 7 is too high, or the outlet pressure of the second air compressor 7 is too high, a fault occurs, in order to avoid this situation, the present application further designs a high-temperature protection mode as follows:

[0045] As shown in the figure, Figure 1As shown, the temperature of the gas at the outlet of the second compressor 7 is monitored by the first temperature sensor 8. When the temperature information monitored by the first temperature sensor 8 exceeds the first temperature preset value for a certain period of time, the controller 29 sends a control command to the motor 6 to reduce the speed of the motor 6 driving the second compressor 7.

[0046] The second temperature sensor 17 and the second pressure sensor 18 monitor the temperature and pressure information at the inlet of the air separator 19, respectively. When the temperature information monitored by the second temperature sensor 17 exceeds the second preset temperature value or the pressure information monitored by the second pressure sensor 18 exceeds the preset pressure value, the controller 29 sends a control command to the motor 6 to reduce the speed of the motor 6 driving the second compressor 7. When the temperature information monitored by the second temperature sensor 17 or the pressure information monitored by the second pressure sensor 18 still exceeds the second preset temperature value and the preset pressure value within a preset time, the controller 29 sends a control command to open the shut-off valve 4, and then the controller 29 sends a control command to shut down the motor 6, and the system enters the high temperature protection mode.

[0047] The adaptive adjustment process of this invention is as follows:

[0048] like Figure 2 As shown, a real-time adaptive adjustment method for an adaptively adjustable electric drive inertia system includes the following steps:

[0049] a. The controller 29 receives ambient temperature and pressure information from the aircraft's central computer, as well as pressure, temperature, and oxygen concentration information from the fuel tank 28 monitored by the third pressure sensor 25, the third temperature sensor 26, and the second oxygen concentration sensor 27.

[0050] b. The controller 29 analyzes the relationship between the flow rate and concentration of nitrogen-rich gas generated by the air separator and calculates the flow rate of nitrogen-rich gas required for the fuel tank 28 to reach the inert state based on the internal calculation program of the controller 29.

[0051] c. The controller 29 determines whether the expected value of the nitrogen-rich gas flow rate is the same as the nitrogen-rich gas flow rate at the outlet of the air separator 19 monitored by the current flow sensor 21. If they are the same, the controller 29 does not make any adjustments to the system and proceeds to the next moment for calculation and evaluation. If they are different, the controller 29 sends a control command at the signal output terminal to adjust the speed of the motor 6 and the opening of the third flow regulating valve 22 to achieve the expected nitrogen-rich gas flow rate, and then proceeds to the next moment for calculation and evaluation.

[0052] The above examples are only used to illustrate the technical solutions of the present application, but not to limit the present application; although the present application has been described in detail with reference to the foregoing examples, it should be understood by those skilled in the art that the technical solutions recorded in the foregoing examples can be modified, or some technical features can be replaced by equivalent replacements; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application, and should be included in the protection scope of the present application.

Claims

1. An electrically driven self-adjustable inerting system, characterized in that, It comprises: air source (1), muffler (2), first filter (3), cut-off valve (4), first air compressor (5), motor (6), second air compressor (7), first temperature sensor (8), first flow regulating valve (9), cooling air source (10), second flow regulating valve (11), three-loop heat exchanger (12), ejector (13), exhaust device (14), second filter (15), ozone converter (16), second temperature sensor (17), second pressure sensor (18), air separation device (19), first oxygen concentration sensor (20), flow sensor (21), third flow regulating valve (22), check valve (23), flame arrester (24), third pressure sensor (25), third temperature sensor (26), second oxygen concentration sensor (27) and fuel tank (28); wherein: air source (1) and muffler (2), first filter (3), cut-off valve (4), first air compressor (5) inlet are connected in turn through pipeline; motor (6) is double output shaft motor, the power end of first air compressor (5) is connected with the output shaft of motor (6), and the other output shaft of motor (6) is connected with second air compressor (7); the outlet of first air compressor (5) is connected with the first hot end loop inlet of three-loop heat exchanger (12) and the cooling channel of motor (6) respectively; wherein, three-loop heat exchanger (12) comprises first hot end loop inlet, first hot end loop outlet, second hot end loop inlet, second hot end loop outlet, cold end inlet and cold end outlet; air source (1) can be air from cargo hold, passenger cabin or external environment; the first hot end loop outlet of three-loop heat exchanger (12) is connected with the inlet of second air compressor (7) through pipeline, the outlet of second air compressor (7) is divided into two ways through three-way pipe, one of which is connected with the inlet of first flow regulating valve (9), and the other is connected with the second hot end loop inlet of three-loop heat exchanger (12); the outlet of first flow regulating valve (9) is connected with the bypass inlet end of ejector (13) through pipeline;The first temperature sensor (8) is installed on the pipeline between the second air compressor (7) and the three-way pipe, and the first flow regulating valve (9) is used to make part of the high pressure gas at the outlet of the second air compressor (7) to be discharged to the external environment through the exhaust device; cooling air source (10), second flow regulating valve (11) and cold end inlet of three-loop heat exchanger (12) are connected in turn through pipeline, cold end outlet of three-loop heat exchanger (12) is connected with the inlet of ejector (13) through pipeline, and the outlet of ejector (13) is connected with the exhaust device (14) through pipeline; the second hot end loop outlet of three-loop heat exchanger (12) is connected with the air inlet of second filter (15), ozone converter (16) and air separation device (19) in turn through pipeline, the oxygen-enriched gas outlet of air separation device (19) is connected with the exhaust device (14) through pipeline, which is used to discharge oxygen-enriched gas outside the machine; The air separation device (19) nitrogen-rich gas outlet is connected with the third flow regulating valve (22), the one-way valve (23), the flame inhibitor (24), and the fuel tank (28) gas inlet through pipes in sequence; the first oxygen concentration sensor (20) and the flow sensor (21) are arranged on the pipeline between the air separation device (19) and the third flow regulating valve (22); the third pressure sensor (25), the third temperature sensor (26), and the second oxygen concentration sensor (27) are arranged in the fuel tank (28).

2. The self-adjusting electrically driven inerting system of claim 1, wherein, During the pre-flight preparation stage, the ejector (13) is connected with the high-pressure gas flow from the second compressor (7) outlet through the exhaust device (14), and the external environment of the cooling air source (10) is driven into the three-loop heat exchanger (12) under the action of the ejector, so that the three-loop heat exchanger (12) realizes cooling heat exchange in the ground state; during the flight process, the ram air source is continuously generated into the three-loop heat exchanger (12) cold end by relying on the flight speed.

3. The self-adjusting electrically driven inerting system of claim 1, wherein, The air separation device (19) comprises an air inlet, a nitrogen-rich gas outlet, and an oxygen-rich gas outlet; the second temperature sensor (17) and the second pressure sensor (18) are arranged on the pipeline between the ozone converter (16) and the air separation device (19); wherein the second filter (15) is used for fine filtering the gas outlet from the second hot end of the three-loop heat exchanger (12).

4. The self-adjusting electrically driven inerting system of claim 1, wherein, The system further comprises a controller (29), the controller (29) comprising a signal input end and a signal output end, the first temperature sensor (8), the second temperature sensor (17), the second pressure sensor (18), the first oxygen concentration sensor (20), the flow sensor (21), the third pressure sensor (25), the third temperature sensor (26), and the second oxygen concentration sensor (27) are connected with the signal input end of the controller (29) through cables; the cut-off valve (4), the motor (6), the first flow regulating valve (9), the second flow regulating valve (11), and the third flow regulating valve (22) are connected with the signal output end of the controller (29) through cables.

5. The self-adjusting electrically driven inerting system of claim 1, wherein, The first oxygen concentration sensor (20) is used to monitor the oxygen volume fraction of the air separation device (19) outlet gas, and the air separation device (19) separation performance is calculated in combination with the flow data of the flow sensor (21) and the second oxygen concentration sensor (27) monitoring the oxygen volume fraction data of the gas phase space inside the fuel tank (28) at a certain working temperature, pressure, to judge whether the air separation device (19) needs to be maintained or replaced; The flow sensor (21) monitors the flow of nitrogen-rich gas at the outlet of the air separation device (19), which is one of the data for judging the separation performance of the air separation device (19); The required nitrogen-rich gas flow is calculated according to the temperature, pressure and oxygen volume fraction of the gas phase space in the fuel tank, and the third flow regulating valve (22) is adjusted by the flow sensor (21) to achieve the required nitrogen-rich gas flow; The second oxygen concentration sensor (27) is used to monitor the oxygen volume fraction of the gas phase space inside the fuel tank (28), and provides the oxygen volume fraction data of the gas phase space in the fuel tank (28) for the controller (29).

6. The self-adjusting electrically powered inerting system of claim 1, wherein, The normal working mode of the system is: Under the action of the first air compressor (5) driven by the motor (6), the air of the air source (1) passes through the silencer (2), the first filter (3), and the cut-off valve (4) in turn, and after the impurities in the air are preliminarily filtered, the air enters the first air compressor (5) to be pressurized and heated. Most of the pressurized and heated gas enters the three-loop heat exchanger (12) for cooling, and part of the gas enters the cooling channel of the motor (6) to carry away the heat generated by the operation of the motor (6). The gas cooled by the three-loop heat exchanger (12) is further pressurized and heated by the second air compressor (7). Part of the pressurized and heated gas by the second air compressor (7) enters the ejector (13) after passing through the first flow regulating valve (9). During the ground preparation stage, the first flow regulating valve (9) is opened, and the high-temperature and high-pressure gas at the outlet of the second air compressor (7) drives the external environment air of the cooling air source (10) to enter the cold end of the three-loop heat exchanger (12) through the second flow regulating valve (11), realizing the cooling and heat exchange of the three-loop heat exchanger (12) in the ground state. During the high-altitude flight stage, the cooling air source (10) relies on the ram air generated by the flight speed to supply the cold end gas source of the three-loop heat exchanger (12), and the first flow regulating valve (9) is closed at this time. The second compressor (7) pressurizes and heats the gas, which enters the three-loop heat exchanger (12) to exchange heat under ground conditions or all under high altitude conditions. The cooled gas enters the second filter (15) to further remove impurities, and then enters the ozone converter (16) to remove trace amounts of ozone in the gas. Then, in the air separation device (19), the oxygen is separated from the air to form an oxygen-rich gas using the principle that the oxygen and nitrogen have different permeation rates, and the oxygen-rich gas is discharged to the outside environment through the discharge device (14). The remaining nitrogen-rich gas passes through the third flow regulating valve (22), the one-way valve (23) and the flame arrestor (24) and is sent to the fuel tank (28), thereby reducing the oxygen volume fraction in the upper gas phase space of the fuel tank (28), and achieving the inert state of the fuel tank (28).

7. The self-adjusting electrically driven inerting system of claim 1, wherein, The high-temperature protection mode of the system is: When the temperature information monitored by the first temperature sensor (8) exceeds the first temperature preset value for a certain period of time, the controller (29) sends a control instruction to the motor (6) to reduce the speed of the second compressor (7) driven by the motor (6); When the temperature information monitored by the second temperature sensor (17) exceeds the second temperature preset value or the pressure information monitored by the second pressure sensor (18) exceeds the pressure preset value, the controller (29) sends a control instruction to the motor (6) to reduce the speed of the second compressor (7) driven by the motor (6). When the temperature information monitored by the second temperature sensor (17) still exceeds the second temperature preset value or the pressure information monitored by the second pressure sensor (18) still exceeds the pressure preset value within a preset time, the controller (29) sends a control instruction to open the shut-off valve (4), and then the controller (29) sends a control instruction to turn off the motor (6), and the system enters the high-temperature protection mode.

8. A method of real-time adaptive adjustment of the self-adaptable electrically driven inerting system according to any one of claims 1 to 7, characterized in that, The steps include: The controller (29) receives the ambient temperature and pressure information sent by the aircraft central computer, as well as the pressure of the fuel tank (28) monitored by the third pressure sensor (25), the temperature of the fuel tank (28) monitored by the third temperature sensor (26), and the oxygen concentration information of the fuel tank (28) monitored by the second oxygen concentration sensor (27); The controller (29) analyzes the relationship between the flow and concentration of the nitrogen-rich gas produced by the air separation device, and calculates the required flow of the nitrogen-rich gas to achieve the inert state of the fuel tank (28) according to the internal calculation program of the controller (29); The controller (29) judges whether the desired value of the nitrogen-enriched gas flow rate is the same as the nitrogen-enriched gas flow rate monitored by the current flow sensor (21) at the outlet of the air separation device (19). If they are the same, the controller (29) does not make any adjustment to the system and enters the calculation of the next moment. If they are not the same, the controller (29) transmits a control instruction to the signal output end to adjust the rotating speed of the motor (6) and the opening of the third flow regulating valve (22) to achieve the desired nitrogen-enriched gas flow rate, and then enters the calculation of the next moment.

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