CN116025468A - Multifunctional power device and control method thereof - Google Patents

Abstract

The invention relates to a multifunctional power device and a control method thereof. Comprising the following steps: the device comprises a gas compressor, a combustion chamber air inlet valve, an air entraining regulating valve, a three-mode combustion chamber, an oxygen storage tank, an oxygen supply shutoff valve, a catalytic reactor, a fuel tank and a fuel solenoid valve; the first inlet of the tri-modal combustion chamber is connected with the outlet pipeline of the air compressor through the inlet valve of the combustion chamber; the second inlet of the tri-mode combustion chamber is connected with a pipeline for engine bleed air through a bleed air regulating valve; the third inlet of the tri-mode combustion chamber is connected with the oxygen storage tank through the oxygen supply shutoff valve; the fuel tank is connected with the catalytic reactor through the fuel electromagnetic valve, and the fourth inlet of the three-mode combustion chamber is connected with the outlet of the catalytic reactor; the maximum ignition height is improved through the oxygen supplementing device, and the high-altitude ignition combustion performance is improved; the device is used for independently providing an emergency high-temperature high-pressure air source driving device to do work, so that the use requirement of emergency power generation is met.

Description

Multifunctional power device and control method thereof

Technical Field

The invention relates to the field of aviation, in particular to a multifunctional power device and a control method thereof.

Background

The aviation onboard system is the fundamental guarantee for realizing main functions and ensuring flight safety of the airplane, and forms three main components of the airplane together with an airplane body and an engine. The aircraft electromechanical system is one of important components of an airborne system, is a generic term of all aircraft systems which perform a guarantee function, and mainly comprises electric power, hydraulic pressure, fuel oil, environmental control, landing gear, protection and lifesaving, oxygen, anti-icing, anti-extinguishing, secondary power, air drop and the like. The second power and environmental control system is a core product form of energy supply and heat dissipation guarantee of an electromechanical system, and mainly executes the tasks of ground starting engine, ground maintenance power supply, cooling air supply, air power generation and emergency power supply, and provides basic guarantee for an aircraft platform. The conventional secondary power and environmental control system comprises an auxiliary power device, an emergency power device, an air circulation cooling device, a combined power device and other product forms. Compared with a discrete auxiliary power device, an emergency power device and an air circulation refrigerating device, the power device has the advantages of being integrated with a compressor, a gear box and generating electricity due to high integration, has obvious advantages in product weight, simultaneously uniformly distributes electric power supply and heat dissipation, and can realize the comprehensive management function of airborne energy and heat.

CN114837814a discloses a thermal management type combined power device, which comprises a power subsystem, a power generation subsystem, a refrigeration subsystem and an oil subsystem, wherein one end of a gas compressor is connected with the power subsystem in a shaft way, and the other end of the gas compressor is connected with the power generation subsystem and the refrigeration subsystem in a shaft way; the engine can be started on the ground, works in the air for a long time, has refrigeration and power supply capability, and in an emergency state, the air is sucked into the combustion chamber by the air suction of the air compressor to ignite and burn, so that the power subsystem is driven to work, and then the power generation subsystem is driven to work. However, the thermal management type combined power device still has the defects under specific working scenes, and specifically comprises the following steps: 1) Due to the limitation of high air pressure, the autonomous compressed air of the air compressor cannot meet the high-altitude ignition requirement of more than 11km, so that the emergency ignition height is insufficient; 2) Because the device with the emergency fuel is not provided, emergency power supply can not be carried out through an emergency state when the high-altitude engine with the height of more than 18km fails, and only the height can be reduced to be below 18km, and then the air entraining driving power supply can be carried out; 3) The heat radiation capacity of the refrigeration component part cannot be adaptively regulated and controlled in different scenes, so that power waste can be caused under specific working conditions, and the efficiency of the device is reduced.

Disclosure of Invention

The invention aims to overcome the defects of the technology, and provides a multifunctional power device and a control method thereof for solving the problem that high-altitude ignition and emergency power supply cannot be realized.

In a first aspect, the present invention provides a multi-function power plant comprising: the device comprises a gas compressor, a combustion chamber air inlet valve, an air entraining regulating valve, a three-mode combustion chamber, an oxygen storage tank, an oxygen supply shutoff valve, a catalytic reactor, a fuel tank and a fuel solenoid valve; the first inlet of the tri-modal combustion chamber is connected with the outlet pipeline of the air compressor through the combustion chamber air inlet valve; the second inlet of the tri-modal combustion chamber is connected with a pipeline for engine bleed air through the bleed air regulating valve; the third inlet of the tri-mode combustion chamber is connected with the oxygen storage tank through the oxygen supply shutoff valve; the fuel tank is connected with the catalytic reactor through the fuel electromagnetic valve, and the fourth inlet of the three-mode combustion chamber is connected with the outlet of the catalytic reactor.

In some embodiments, the multi-function power plant further comprises: the device comprises a speed regulating motor, a fuel pump, a fuel tank, a fuel filter, a fuel solenoid valve and a shunt; the speed regulating motor is in shaft connection with the fuel pump; the oil way inlet of the fuel pump is connected with the fuel tank; the oil way outlet of the fuel pump is connected with the shunt through the oil filter and the fuel electromagnetic valve in sequence; the flow divider comprises two paths of outlets which are respectively connected with a fifth inlet and a sixth inlet of the tri-mode combustion chamber.

In some embodiments, the multi-function power plant further comprises: a controller; the controller controls the rotating speed of the speed regulating motor through an electric signal so as to control the oil supply flow of the fuel pump; the controller controls the opening of the bleed air regulating valve through an electric signal so as to control the air source pressure and flow of the engine bleed air entering the tri-mode combustion chamber; the controller controls the on-off state of the oxygen supply shutoff valve through an electric signal so as to control the oxygen supplementing time; the controller controls the on-off state of the fuel electromagnetic valve through an electric signal, so as to control the time of emergency fuel supply; the function switching of the multifunctional power device is realized through the controller, and the functions comprise: autonomous air-suction combustion power generation function, engine air-entraining combustion power generation function, high-altitude oxygen supplementing autonomous air-suction combustion power generation function and catalytic cracking driving power generation function.

In some embodiments, the multi-function power plant further comprises: the cooling turbine, the refrigeration control shutoff valve, the cooling heat exchanger and the three-way heat exchanger; the outlet of the cooling turbine is one way for supplying to electronic equipment and a cabin air circuit, the other way of the outlet of the cooling turbine is connected with the cold end inlet of the cooling heat exchanger through the refrigeration control shutoff valve, the cold end outlet of the cooling heat exchanger is connected with the cold end inlet of the three-way heat exchanger, and the cold end outlet of the three-way heat exchanger is connected with an aircraft exhaust passage.

In some embodiments, the controller controls the on-off state of the refrigeration control shut-off valve through an electric signal, and cools the liquid cooling electronic equipment as required to realize self-adaptive regulation and control.

In a second aspect, the present invention also provides an application scenario of the multifunctional power device according to the first aspect, where the multifunctional power device is applied to five working scenarios of ground start engine, ground maintenance power supply and air supply, air power supply and refrigeration, high-altitude emergency start engine and high-altitude emergency power supply.

In a third aspect, the present invention further provides a control method for a multifunctional power device in the second aspect under the working scenario of air power supply and refrigeration, wherein the control method controls the opening of the high-flow shutoff valve and the bleed air regulating valve; controlling an air inlet door, a small flow regulating valve and a combustion chamber air inlet valve to be closed; controlling a bleed air regulating valve to enable the bleed air of the engine to enter a tri-modal combustion chamber after pressure regulation, and then enter a centripetal power turbine and an axial flow power turbine to expand and do work; and controlling the air compressor to independently suck air under the drive of shaft work, enabling an air source to flow through the three-way heat exchanger for cooling after being pressurized and heated, and enabling the air source to enter the cooling turbine for expansion refrigeration through the high-flow shutoff valve so as to supply to electronic equipment and a cabin.

In the embodiment, when high-power equipment is required to be cooled, the refrigeration control shutoff valve is controlled to be opened, cooling gas flows through the cooling heat exchanger and the three-way heat exchanger as a heat sink and is discharged to the outside of the machine, and the cold end of the cooling heat exchanger is connected with antifreeze for cooling electronic equipment; when the power is insufficient, the controller controls the speed regulating motor to drive the fuel pump to pump fuel from the fuel tank, the fuel enters the tri-modal combustion chamber through the small flow channels in the fuel filter, the fuel solenoid valve and the flow divider, and is mixed with engine bleed air, and the mixture is combusted after the igniter ignites, so that the temperature of turbine working gas is increased, the power turbine is further increased to function, and the power generation capacity of the starting and generating integrated motor is increased.

In a fourth aspect, the present invention further provides a control method of the multifunctional power device in the working scene of the high-altitude emergency starting engine in the second aspect, and the opening of an air inlet door and an air inlet valve of the combustion chamber is controlled; the bleed air regulating valve, the small flow regulating valve, the large flow shutoff valve and the refrigeration control shutoff valve are controlled to be closed; controlling the air compressor to suck air autonomously, and enabling an air source to enter the three-mode combustion chamber through the air-entraining regulating valve after being pressurized and warmed; controlling a speed regulating motor to drive a fuel pump to pump fuel oil from the fuel tank, and enabling the fuel oil to enter a tri-modal combustion chamber through small flow passages in the fuel oil filter, the fuel oil electromagnetic valve and the flow divider in sequence; when the flying height exceeds 11km, the controller controls the oxygen supply shutoff valve to be opened, oxygen in the oxygen storage tank is mixed with fuel oil and a heating and pressurizing air source, and the mixture is combusted after ignition of the igniter to form high-temperature and high-pressure fuel gas, and the high-temperature and high-pressure fuel gas sequentially enters the centripetal power turbine and the axial flow power turbine to expand and do work; the rotation speed is monitored by a rotation speed sensor and is transmitted back to the controller, and the closed-loop control of the rotation speed is realized through fuel regulation.

In a fifth aspect, the present invention further provides a control method for a multifunctional power device in the high-altitude emergency power supply working scenario of the second aspect, when the flying height exceeds 18km, the air inlet door, the air inlet valve of the combustion chamber, the air inlet regulating valve, the small flow regulating valve, the large flow shutoff valve and the refrigeration control shutoff valve are controlled to be closed; controlling the fuel electromagnetic valve to be opened; hydrazine fuel in the fuel tank enters the catalytic reactor for catalytic pyrolysis to form micromolecular gas, the micromolecular gas enters the tri-modal combustion chamber, and the micromolecular gas expands and works in the centripetal power turbine and the axial flow power turbine to drive the integrated motor to generate electricity and is supplied to on-board emergency equipment.

The technical scheme provided by the invention has the following beneficial effects:

1. according to the invention, the nozzle outer ring of the tri-mode combustion chamber is connected with the third inlet of the tri-mode combustion chamber, the oxygen storage tank and the oxygen supply shutoff valve supply oxygen through the third inlet of the tri-mode combustion chamber, when the high-altitude ignition is insufficient in inspiration, oxygen enters the combustion chamber through the nozzle outer ring to be mixed with fuel for combustion, so that the high-altitude ignition requirement is met, the oxygen supplementing component is added to supplement oxygen at the high altitude of more than 11km, the maximum ignition height is increased from 11km to 18km, the high-altitude ignition combustion performance is improved, and the engine can be started quickly when the high altitude of the engine fails.

2. According to the invention, the fourth inlet of the three-mode combustion chamber is connected with the emergency fuel supply device, the fuel tank is loaded with hydrazine fuel, the hydrazine fuel enters the catalytic reactor for catalytic reaction under the control of the fuel electromagnetic valve, and can be directly catalytically cracked into micromolecular gas without depending on oxygen, and then enters the centripetal power turbine and the axial flow power turbine for driving work, and the power output is realized without depending on the automatic pressurization of the compressor and the external air source of the engine, so that the high-altitude emergency power generation function is met, the emergency fuel supply device is increased, and when the engine fails and cannot automatically inhale, the emergency high-temperature high-pressure air source driving device is provided for doing work to supply emergency power for the aircraft platform.

3. According to the invention, the refrigerating control shutoff valve is arranged on one path of the three-way interface of the cooling turbine outlet, when the high-power equipment is not used, the refrigerating control shutoff valve is closed, so that the air flow in a loop can be effectively reduced, the load of the air compressor is reduced, the power generation capacity of the starting and generating integrated motor can be improved, the bleed air of the engine can be reduced, the fuel oil compensation of an airplane can be reduced, the on-demand regulation and control function of on-board energy heat is realized, the refrigerating regulation device is added, the high-power refrigerating equipment can be directly isolated, the electric load and the refrigerating load are regulated, the on-board energy heat regulation and control can be realized as required, and the high-efficiency operation of the system can be ensured in different operation scenes.

4. The invention is simplified in structure, the hot end outlet of the three-way heat exchanger does not enter the air compressor to form semi-closed air circulation, on one hand, closed-loop control of a loop is reduced, so that control is simplified, on the other hand, the air inflow of the air compressor is directly reduced, the load of the air compressor is reduced, redundant power can directly drive the starting and generating integrated motor, the power generating capacity of the power device is improved, the simplified refrigerating loop does not execute the semi-closed air circulation through the air compressor, the load of the air compressor is reduced, and the power generating power is improved by 150% (from 40kW to 100 kW) by matching with the afterburning of a combustion chamber.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention as claimed.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the disclosure and together with the description, serve to explain the principles of the disclosure.

Fig. 1 shows a schematic diagram of the structure of the multifunctional power device of the invention.

Detailed Description

The disclosure will now be discussed with reference to several exemplary embodiments. It should be understood that these embodiments are discussed only to enable those of ordinary skill in the art to better understand and thus practice the present disclosure, and are not meant to imply any limitation on the scope of the present disclosure.

As used herein, the term "comprising" and variants thereof are to be interpreted as meaning "including but not limited to" open-ended terms. The term "based on" is to be interpreted as "based at least in part on". The terms "one embodiment" and "an embodiment" are to be interpreted as "at least one embodiment. The term "another embodiment" is to be interpreted as "at least one other embodiment".

The aviation onboard system mainly comprises electric power, hydraulic pressure, fuel oil, environmental control, landing gear, protection and lifesaving, oxygen, anti-icing/deicing, anti-icing/fire extinguishing, second power, air drop and the like. The second power and environmental control system is a core product form of energy supply and heat dissipation guarantee of an electromechanical system, and mainly executes the tasks of ground starting engine, ground maintenance power supply, cooling air supply, air power generation and emergency power supply, and provides basic guarantee for an aircraft platform. Compared with a discrete auxiliary power device, an emergency power device and an air circulation refrigerating device, the power device has the advantages of being integrated with a compressor, a gear box and generating electricity due to high integration, has obvious advantages in product weight, simultaneously uniformly distributes electric power supply and heat dissipation, and can realize the comprehensive management function of airborne energy and heat.

At present, the related power device still has the defects under the specific working scene, which comprises the following steps: due to the limitation of high air pressure, the autonomous compressed air of the air compressor cannot meet the high-altitude ignition requirement of more than 11km, so that the emergency ignition height is insufficient; when the high-altitude engine above 18km fails, emergency power supply cannot be carried out through an emergency state, and only the height can be reduced below 18km, and then air entraining driving power supply can be carried out; the heat radiation capacity of the refrigeration component part cannot be adaptively regulated and controlled in different scenes, so that power waste can be caused under specific working conditions, and the efficiency of the device is reduced.

Example 1

The embodiment of the invention discloses a multifunctional power device, as shown in fig. 1, the multifunctional power device can comprise: the device comprises a gas compressor 1, a combustion chamber gas inlet valve 26, a bleed air regulating valve, a three-mode combustion chamber 4, an oxygen storage tank 24, an oxygen supply shutoff valve 25, a catalytic reactor 29, a fuel tank 30 and a fuel solenoid valve 31; the first inlet of the tri-modal combustion chamber 4 is connected with the outlet pipeline of the compressor 1 through a combustion chamber air inlet valve 26; the second inlet of the tri-modal combustion chamber 4 is connected with a pipeline for engine bleed air through a bleed air regulating valve; the third inlet of the tri-modal combustion chamber 4 is connected with the oxygen storage tank 24 through the oxygen supply shutoff valve 25; the fuel tank 30 is connected to the catalytic reactor 29 by a fuel solenoid valve 31, and the fourth inlet of the trimodal combustion chamber 4 is connected to the outlet of the catalytic reactor 29.

In some embodiments, the multi-function power plant may further comprise: a speed regulating motor 17, a fuel pump 19, a fuel tank 18, a fuel filter 20, a fuel solenoid valve 22 and a shunt 23; the speed regulating motor 17 is in shaft connection with the fuel pump 19; the oil way inlet of the fuel pump 19 is connected with the fuel tank 18; the oil way outlet of the fuel pump 19 is connected with a shunt 23 through an oil filter 20 and a fuel electromagnetic valve 22 in sequence; the flow divider 23 comprises two outlets which are connected to the fifth inlet and the sixth inlet of the trimodal combustion chamber 4, respectively.

The structure mainly executes the shaft work output function of the power device; on the one hand, after the air compressor 1 is pressurized or a high-temperature high-pressure air source led out from an engine induction port enters the three-mode combustion chamber 4, the high-temperature high-pressure air enters the centripetal power turbine 2 and the axial flow power turbine 3 to drive to do work through the igniter 27 for ignition combustion, and the oxygen supplementing assembly formed by the oxygen storage tank 24 and the oxygen supply shutoff valve 25 can provide proper oxygen for assisting combustion when oxygen is insufficient. On the other hand, when the compressor 1 and the engine cannot provide high-temperature and high-pressure air sources, the fuel tank 30 provides catalytic reaction fuel for the catalytic reactor 29 through the fuel electromagnetic valve 31, and the micromolecular gas with high temperature and high pressure is formed to enter the centripetal power turbine 2 and the axial flow power turbine 3 to drive and do work, so that an emergency function is achieved.

In some embodiments, the multi-function power plant may further comprise: a controller 7; the controller 7 controls the rotating speed of the speed regulating motor 17 through an electric signal, so as to control the oil supply flow of the fuel pump 19; the controller 7 controls the opening degree of the bleed air regulating valve through an electric signal, so as to control the air source pressure and flow of the bleed air of the engine entering the tri-mode combustion chamber 4; the controller 7 controls the opening and closing state of the oxygen supply shutoff valve 25 through an electric signal, so as to control the oxygen supplementing time; the controller 7 controls the opening and closing states of the fuel solenoid valve 31 through an electric signal, thereby controlling the timing of emergency fuel supply; the function switching of the multifunctional power device is realized through the controller 7, and the functions comprise: autonomous air-suction combustion power generation function, engine air-entraining combustion power generation function, high-altitude oxygen supplementing autonomous air-suction combustion power generation function and catalytic cracking driving power generation function.

In some embodiments, the multi-function power plant may further comprise: a cooling turbine 5, a refrigeration control shut-off valve 35, a cooling heat exchanger 15 and a three-way heat exchanger 10; one path of the outlet of the cooling turbine 5 is supplied to electronic equipment and a cabin air path, the other path of the outlet of the cooling turbine 5 is connected with the cold end inlet of the cooling heat exchanger 15 through a refrigeration control shutoff valve 35, the cold end outlet of the cooling heat exchanger 15 is connected with the cold end inlet of the three-way heat exchanger 10, and the cold end outlet of the three-way heat exchanger 10 is connected with an aircraft exhaust passage.

In some embodiments, the controller 7 controls the on-off state of the refrigeration control shut-off valve 35 through an electric signal, and cools the liquid cooling electronic device as required, so as to realize self-adaptive regulation.

Example 2

The embodiment of the invention discloses a multifunctional power device, which can comprise: the engine comprises a gas compressor 1, a centripetal power turbine 2, an axial flow power turbine 3, a three-mode combustion chamber 4, a cooling turbine 5, an integrated starting motor 6, a controller 7, a super capacitor 8, a lubricating oil cavity 9, a three-way heat exchanger 10, a small flow regulating valve 11, a large flow shutoff valve 12, a lubricating oil component 13, a lubricating oil heat exchanger 14, a cooling heat exchanger 15, an air inlet door 16, a speed regulating motor 17, a fuel tank 18, a fuel pump 19, an oil filter 20, a fuel pressure difference sensor 21, a fuel electromagnetic valve 22, a shunt 23, an oxygen storage tank 24, an oxygen supply shutoff valve 25, a combustion chamber air inlet valve 26, an igniter 27, a bleed air pressure regulating valve 28, a catalytic reactor 29, a fuel tank 30, a fuel electromagnetic valve 31, an exhaust temperature sensor 32, a rotation speed sensor 33, a cold air pressure sensor 34 and a refrigeration control shutoff valve 35.

In this embodiment, the cooling turbine 5, the integral starting motor 6, the air compressor 1, the centripetal turbine and the axial turbine are sequentially connected in an axial-flow mode to form a heat energy management component of the power device, wherein the air compressor 1 plays a role in air source pressurization, the centripetal turbine and the axial-flow turbine utilize high-temperature high-pressure air sources to expand and apply work to the heat energy management component to provide shaft power, the cooling turbine 5 expands the medium-low-temperature high-pressure air sources to remove low-temperature air for cooling, and meanwhile provides certain shaft power for the heat energy management component, the integral starting motor 6 can provide shaft power for the heat energy management component by utilizing an electric function on one hand, can utilize shaft work of the heat energy management component to generate electricity on the other hand, and the lubricating oil cavity 9 is an oil cavity 9 body inside the component and is used for lubricating and cooling a bearing. The oil supply pump in the lubricating oil component 13 is connected with the hot end inlet of the lubricating oil heat exchanger 14, the hot end outlet of the lubricating oil heat exchanger 14 is respectively connected with the inlets of the three lubricating oil cavities 9, and the outlet of the lubricating oil cavity 9 is connected with the oil return pump in the lubricating oil component 13. The oil assembly 13 supplies cooling oil to the oil chamber 9 in the thermal energy management assembly. The super capacitor 8 is connected with the starting integrated motor 6 through a cable, so that the charging and discharging functions are realized.

In this embodiment, the air inlet damper 16 is connected to the inlet of the air compressor 1, the outlet of the air compressor 1 is connected to a three-way pipeline, one way is connected to the hot end inlet of the three-way heat exchanger 10, the hot end outlet of the three-way heat exchanger 10 is connected to the inlet of the cooling turbine 5 through the three-way pipeline through the small flow regulating valve 11 and the large flow shutoff valve 12, the outlet of the cooling turbine 5 is supplied to the electronic equipment and the cabin air circuit through one way of the three-way pipe, the other way is connected to the cold end inlet of the cooling heat exchanger 15 through the refrigeration control shutoff valve 35, the cold end outlet of the cooling heat exchanger 15 is connected to the cold end inlet of the three-way heat exchanger 10, and the cold end outlet of the three-way heat exchanger 10 is connected to the aircraft exhaust passage.

The above structure mainly performs the refrigerating function of the power plant. The high-temperature high-pressure air after the pressurization of the air compressor 1 enters the three-way heat exchanger 10 to be cooled and then enters the cooling turbine 5 to be expanded and refrigerated, so that on one hand, the electronic equipment and the cabin can be cooled in a cold air form, and on the other hand, a cold source can be provided for the cooling heat exchanger 15, and further, the high-power electronic equipment can be cooled.

In some embodiments, the multifunctional power device can also control the rotation speed of the oil supply pump and the oil return pump of the oil slide assembly 13 through an electric signal, so as to control the oil supply and return state in the oil slide cavity 9. The opening and closing state of the air inlet door 16 is controlled by an electric signal, and thus the air suction state of the compressor 1 is controlled. The starting and generating integrated motor 6 is controlled by an electric signal, so that the starting and generating state and the charging and discharging state of the super capacitor 8 are controlled. The opening degree of the small flow regulating valve 11 and the opening and closing state of the large flow shutoff valve 12 are controlled through electric signals, so that the air source flow entering the cooling turbine 5 is controlled, the refrigerating capacity is controlled, and the cold air pressure sensor 34 serves as feedback to transmit signals back to the controller 7. The switch state of the refrigeration control shutoff valve 35 is controlled by an electric signal, so that whether the high-power liquid cooling equipment provides cooling or not is controlled. The exhaust temperature signal returned by the exhaust temperature sensor 32 enters the controller 7 to monitor the exhaust temperature in real time so as to prevent the exhaust from exceeding the threshold temperature, thereby causing the device to malfunction or the service life to decline.

Example 3

The multifunctional power device is applied to five working scenes of ground starting engines, ground maintenance power supply and air supply, air power supply and refrigeration, high-altitude emergency starting engines and high-altitude emergency power supply.

In some embodiments, under the ground starting engine scene working scene, the controller 7 controls the opening of the air inlet air door 16 and the combustion chamber air inlet valve 26 through an electric signal, the air-entraining regulating valve 28, the small-flow regulating valve 11, the large-flow shutoff valve 12 and the refrigeration control shutoff valve 35 are closed, the starting integrated motor 6 is in an electric state to provide initial power for a shafting, the air compressor 1 independently sucks air, an air source enters the three-mode combustion chamber 4 through the air-entraining regulating valve after being pressurized and heated, the controller 7 controls the speed regulating motor 17 to drive the fuel pump 19 to suck fuel from the fuel tank 18, enters the three-mode combustion chamber 4 through small flow passages in the oil filter 20, the fuel electromagnetic valve 22 and the shunt 23, is mixed with a heating and pressurizing air source, is combusted after being ignited by the igniter 27, high-temperature and high-pressure fuel gas is formed, and sequentially enters the centripetal power turbine 2 and the axial flow power turbine 3 to do expansion work, in the process, the rotation speed of the device is monitored by the rotation speed sensor 33 and returns to the controller 7, and the rotation speed closed-loop control is realized through the fuel regulation. At this time, the starting integrated motor 6 is converted into a power generation state to output electric power outwards, and then drives the starting generator of the engine to start the engine.

In some embodiments, in a ground maintenance power supply and air supply working scene, the controller 7 controls the opening of the air inlet door 16, the small flow regulating valve 11 and the combustion chamber air inlet valve 26 through electric signals, the air entraining regulating valve 28, the large flow shutoff valve 12 and the refrigeration control shutoff valve 35 to be closed, the air compressor 1 automatically sucks air, after the air source is pressurized and heated, part of the air source enters the trimodal combustion chamber 4 through the air entraining regulating valve, the controller 7 controls the speed regulating motor 17 to drive the fuel pump 19 to suck fuel from the fuel tank 18, the air enters the trimodal combustion chamber 4 through the small flow passages in the oil filter 20, the fuel oil electromagnetic valve 22 and the flow divider 23 to be mixed with the heated and pressurized air source, the air is combusted after the igniter 27 is ignited to form high-temperature compressed air, the compressed air sequentially enters the centripetal power turbine 2 and the axial flow power turbine 3 to be expanded and acted, the other part of the compressed air is cooled through the three-way heat exchanger 10 to be cooled, the small flow regulating valve 11 is expanded and cooled, the air is supplied to the electronic equipment and the cabin, the rotating speed of the device is monitored by the rotating speed sensor 33 and is returned to the controller 7, the refrigerating pressure is returned to the controller 7 through the cold air pressure sensor 34, and the rotating speed of the device is closed-loop control is realized through the rotating speed regulation and the fuel speed and the closed loop control. At this time, the integral starter motor 6 is in a power generation state to output electric power outwards, and when the power remains, electric energy can be stored in the super capacitor 8.

In some embodiments, in an overhead power and refrigeration operating scenario, the shut-off valve and bleed air regulating valve are controlled to open; controlling the intake damper 16, the small flow rate regulating valve 11 and the combustion chamber intake valve 26 to be closed; controlling a bleed air regulating valve to enable engine bleed air to enter a tri-modal combustion chamber 4 after pressure regulation, and then enter a centripetal power turbine 2 and an axial flow power turbine to expand and do work; the compressor 1 is controlled to independently suck air under the drive of shaft work, the air source is pressurized and heated, then flows through the three-way heat exchanger 10 to be cooled, and enters the cooling turbine 5 to be expanded and cooled through the high-flow shutoff valve 12 to be supplied to electronic equipment and cabins.

In this embodiment, when the high-power equipment needs to be cooled, the refrigeration control shutoff valve 35 is controlled to be opened, the cooling gas flows through the cooling heat exchanger 15 and the three-way heat exchanger 10 as a heat sink and is discharged to the outside of the machine, the cold end of the cooling heat exchanger 15 is connected with the antifreeze for cooling the electronic equipment, in the process, the rotation speed of the device is monitored by the rotation speed sensor 33 and is transmitted back to the controller 7, and the closed-loop control of the rotation speed is realized through the pressure regulation of the bleed-air pressure regulating valve 28. At this time, the integral starter motor 6 is in a power generation state and outputs electric power to the outside.

In this embodiment, when the power is insufficient, the controller 7 controls the speed regulating motor 17 to drive the fuel pump 19 to pump fuel from the fuel tank 18, the fuel enters the trimodal combustion chamber 4 through the small flow channels in the fuel filter 20, the fuel solenoid valve 22 and the flow divider 23, and is mixed with engine bleed air, the mixture is ignited by the igniter 27 and combusted, the temperature of turbine working gas is increased, the power turbine is further increased to function, the power generation capacity of the power generation integrated motor 6 is increased, in the process, the bleed air pressure regulating valve 28 is fully opened, the rotating speed of the device is monitored by the rotating speed sensor 33 and is returned to the controller 7, and the rotating speed closed-loop control is realized through the fuel regulation.

In some embodiments, in a high-altitude emergency start engine operating scenario, the intake damper 16 and the combustion chamber intake valve 26 are controlled to open; the bleed air regulating valve, the small flow regulating valve 11, the large flow shutoff valve 12 and the refrigeration control shutoff valve 35 are controlled to be closed; the air compressor 1 is controlled to automatically suck air, and an air source enters the three-mode combustion chamber 4 through the air-entraining regulating valve after being pressurized and warmed; the speed regulating motor 17 is controlled to drive the fuel pump 19 to pump fuel from the fuel tank 18, and the fuel sequentially passes through the small flow passages in the fuel filter 20, the fuel solenoid valve 22 and the flow divider 23 to enter the tri-modal combustion chamber 4; when the flying height exceeds 11km, the controller 7 controls the oxygen supply shutoff valve 25 to be opened, oxygen in the oxygen storage tank 24 is mixed with fuel oil and a heating and pressurizing air source, and the mixture is combusted after the igniter 27 is ignited to form high-temperature and high-pressure fuel gas, and the high-temperature and high-pressure fuel gas sequentially enters the centripetal power turbine 2 and the axial flow power turbine to expand and do work; the rotation speed sensor 33 monitors and transmits the rotation speed back to the controller 7, the closed-loop control of the rotation speed is realized through the adjustment of fuel, and at the moment, the starting integrated motor 6 is in a power generation state to output electric power outwards, so that the starting generator of the engine is driven, and the engine is started.

In some embodiments, in a high altitude emergency power operation scenario, when the flying height exceeds 18km, the intake damper 16, the combustion chamber intake valve 26, the bleed air regulating valve, the small flow regulating valve 11, the large flow shutoff valve 12 and the refrigeration control shutoff valve 35 are controlled to be closed; controlling the fuel solenoid valve 31 to open; the hydrazine fuel in the fuel tank 30 enters the catalytic reactor 29 for catalytic pyrolysis to form micromolecular gas, the micromolecular gas enters the tri-modal combustion chamber 4, and the micromolecular gas expands and works in the centripetal power turbine 2 and the axial flow power turbine to drive the integrated generator 6 to generate electricity and supply the electricity to on-board emergency equipment.

In the above five working scenarios, the lubricating oil component 13 supplies lubricating oil, the lubricating oil enters the lubricating oil cavity 9 after being cooled by the lubricating oil heat exchanger 14, and the lubricating oil is pumped back by the oil return pump to lubricate and cool the rotor. The exhaust temperature sensor 32 and the fuel pressure difference sensor 21 transmit the collected signals back to the controller 7, and the exhaust temperature and the blocking state of the fuel filter 20 are monitored at any time, so that the safe and stable operation of the device is ensured.

It is understood that the term "plurality" in this disclosure means two or more, and other adjectives are similar thereto. "and/or", describes an association relationship of an association object, and indicates that there may be three relationships, for example, a and/or B, and may indicate: a exists alone, A and B exist together, and B exists alone. The character "/" generally indicates that the context-dependent object is an "or" relationship. The singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.

It is further understood that the terms "first," "second," and the like are used to describe various information, but such information should not be limited to these terms. These terms are only used to distinguish one type of information from another and do not denote a particular order or importance. Indeed, the expressions "first", "second", etc. may be used entirely interchangeably. For example, first information may also be referred to as second information, and similarly, second information may also be referred to as first information, without departing from the scope of the present disclosure.

It will be further understood that the terms "center," "longitudinal," "transverse," "front," "rear," "upper," "lower," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like, as used herein, refer to an orientation or positional relationship based on that shown in the drawings, merely for convenience in describing the present embodiments and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operate in a particular orientation.

It will be further understood that "connected" includes both direct connection where no other member is present and indirect connection where other element is present, unless specifically stated otherwise.

It will be further understood that although operations are depicted in the drawings in a particular order, this should not be understood as requiring that such operations be performed in the particular order shown or in sequential order, or that all illustrated operations be performed, to achieve desirable results. In certain circumstances, multitasking and parallel processing may be advantageous.

Other embodiments of the disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the disclosure disclosed herein. This disclosure is intended to cover any adaptations, uses, or adaptations of the disclosure following the general principles of the disclosure and including such departures from the present disclosure as come within known or customary practice within the art to which the disclosure pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the disclosure being indicated by the following claims.

It is to be understood that the present disclosure is not limited to the precise arrangements and instrumentalities shown in the drawings, and that various modifications and changes may be effected without departing from the scope thereof. The scope of the present disclosure is limited only by the appended claims.

Claims (10)

1. A multi-functional power device, characterized in that the multi-functional power device comprises: the device comprises a gas compressor, a combustion chamber air inlet valve, an air entraining regulating valve, a three-mode combustion chamber, an oxygen storage tank, an oxygen supply shutoff valve, a catalytic reactor, a fuel tank and a fuel solenoid valve; the first inlet of the tri-modal combustion chamber is connected with the outlet pipeline of the air compressor through the combustion chamber air inlet valve; the second inlet of the tri-modal combustion chamber is connected with a pipeline for engine bleed air through the bleed air regulating valve; the third inlet of the tri-mode combustion chamber is connected with the oxygen storage tank through the oxygen supply shutoff valve; the fuel tank is connected with the catalytic reactor through the fuel electromagnetic valve, and the fourth inlet of the three-mode combustion chamber is connected with the outlet of the catalytic reactor.

2. The multi-function power device of claim 1, further comprising: the device comprises a speed regulating motor, a fuel pump, a fuel tank, a fuel filter, a fuel solenoid valve and a shunt; the speed regulating motor is in shaft connection with the fuel pump; the oil way inlet of the fuel pump is connected with the fuel tank; the oil way outlet of the fuel pump is connected with the shunt through the oil filter and the fuel electromagnetic valve in sequence; the flow divider comprises two paths of outlets which are respectively connected with a fifth inlet and a sixth inlet of the tri-mode combustion chamber.

3. The multi-function power device of claim 2, further comprising: a controller; the controller controls the rotating speed of the speed regulating motor through an electric signal so as to control the oil supply flow of the fuel pump; the controller controls the opening of the bleed air regulating valve through an electric signal so as to control the air source pressure and flow of the engine bleed air entering the tri-mode combustion chamber; the controller controls the on-off state of the oxygen supply shutoff valve through an electric signal so as to control the oxygen supplementing time; the controller controls the on-off state of the fuel electromagnetic valve through an electric signal, so as to control the time of emergency fuel supply; the function switching of the multifunctional power device is realized through the controller, and the functions comprise: autonomous air-suction combustion power generation function, engine air-entraining combustion power generation function, high-altitude oxygen supplementing autonomous air-suction combustion power generation function and catalytic cracking driving power generation function.

4. A multi-function power plant as claimed in claim 3, further comprising: the cooling turbine, the refrigeration control shutoff valve, the cooling heat exchanger and the three-way heat exchanger; the outlet of the cooling turbine is one way for supplying to electronic equipment and a cabin air circuit, the other way of the outlet of the cooling turbine is connected with the cold end inlet of the cooling heat exchanger through the refrigeration control shutoff valve, the cold end outlet of the cooling heat exchanger is connected with the cold end inlet of the three-way heat exchanger, and the cold end outlet of the three-way heat exchanger is connected with an aircraft exhaust passage.

5. The multifunctional power device according to claim 4, wherein the controller controls the on-off state of the refrigeration control shut-off valve through an electric signal, and cools the liquid cooling electronic equipment according to the need, so as to realize self-adaptive regulation.

6. A multi-functional power device according to any one of claims 1-5, wherein the multi-functional power device is applied in five working scenarios of ground start engine, ground maintenance power supply and air supply, air power supply and refrigeration, high altitude emergency start engine and high altitude emergency power supply.

7. A method of controlling a multi-function power plant in an overhead power and refrigeration operating scenario as claimed in claim 6, wherein the shut-off valve and bleed air regulating valve are controlled to open; controlling an air inlet door, a small flow regulating valve and a combustion chamber air inlet valve to be closed; controlling a bleed air regulating valve to enable the bleed air of the engine to enter a tri-modal combustion chamber after pressure regulation, and then enter a centripetal power turbine and an axial flow power turbine to expand and do work; and controlling the air compressor to independently suck air under the drive of shaft work, enabling an air source to flow through the three-way heat exchanger for cooling after being pressurized and heated, and enabling the air source to enter the cooling turbine for expansion refrigeration through the high-flow shutoff valve so as to supply to electronic equipment and a cabin.

8. The control method of a multifunctional power plant according to claim 7, wherein when the high-power equipment is required to be cooled, the refrigeration control shutoff valve is controlled to be opened, cooling gas flows through the cooling heat exchanger and the three-way heat exchanger as a heat sink and is discharged to the outside of the machine, and the cold end of the cooling heat exchanger is connected with antifreeze for cooling the electronic equipment; when the power is insufficient, the controller controls the speed regulating motor to drive the fuel pump to pump fuel from the fuel tank, the fuel enters the tri-modal combustion chamber through the small flow channels in the fuel filter, the fuel solenoid valve and the flow divider, and is mixed with engine bleed air, and the mixture is combusted after the igniter ignites, so that the temperature of turbine working gas is increased, the power turbine is further increased to function, and the power generation capacity of the starting and generating integrated motor is increased.

9. A method of controlling a multi-function power plant in the high-altitude emergency start engine operating scenario of claim 6, wherein an intake damper and the combustion chamber intake valve are controlled to open; the bleed air regulating valve, the small flow regulating valve, the large flow shutoff valve and the refrigeration control shutoff valve are controlled to be closed; controlling the air compressor to suck air autonomously, and enabling an air source to enter the three-mode combustion chamber through the air-entraining regulating valve after being pressurized and warmed; controlling a speed regulating motor to drive a fuel pump to pump fuel oil from the fuel tank, and enabling the fuel oil to enter a tri-modal combustion chamber through small flow passages in the fuel oil filter, the fuel oil electromagnetic valve and the flow divider in sequence; when the flying height exceeds 11km, the controller controls the oxygen supply shutoff valve to be opened, oxygen in the oxygen storage tank is mixed with fuel oil and a heating and pressurizing air source, and the mixture is combusted after ignition of the igniter to form high-temperature and high-pressure fuel gas, and the high-temperature and high-pressure fuel gas sequentially enters the centripetal power turbine and the axial flow power turbine to expand and do work; the rotation speed is monitored by a rotation speed sensor and is transmitted back to the controller, and the closed-loop control of the rotation speed is realized through fuel regulation.

10. A control method of a multifunctional power device in the high-altitude emergency power supply operation scene according to claim 6, characterized in that when the flying height exceeds 18km, an air inlet door, a combustion chamber air inlet valve, an air bleed regulating valve, a small flow regulating valve, a large flow shutoff valve and a refrigeration control shutoff valve are controlled to be closed; controlling the fuel electromagnetic valve to be opened; hydrazine fuel in the fuel tank enters the catalytic reactor for catalytic pyrolysis to form micromolecular gas, the micromolecular gas enters the tri-modal combustion chamber, and the micromolecular gas expands and works in the centripetal power turbine and the axial flow power turbine to drive the integrated motor to generate electricity and is supplied to on-board emergency equipment.

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