Aircraft starting power supply and gas source control system based on gas turbine power station power supply

Abstract

The utility model provides an aircraft starting power supply and gas source control system based on gas turbine power station power supply, and belongs to the technical field of aircraft starting power supply and gas source control. The technical problem to be solved is to provide an aircraft starting power supply based on gas turbine power station power supply and improvement of a gas source control system hardware structure. According to the technical scheme, a miniature aero-engine, a permanent magnet generator and a controller are arranged on a trailer chassis, the miniature aero-engine is composed of a single-stage centrifugal compressor, an annular combustion chamber and a radial turbine, and a rotor of the radial turbine and a motor rotor of the permanent magnet generator are coaxially arranged; an air entraining device is arranged at the air entraining end of a low-pressure cabin of the micro aero-engine, a measurement control system is arranged in the air entraining device, the output end of the air entraining device is externally connected with an air entraining hose, and the air outlet end of the air entraining hose directly faces a deicing operation area of an airport aircraft. The device is applied to guarantee and maintenance of airport airplanes.

Description

Technical Field

[0001] The utility model provides an aircraft starting power supply and gas source control system based on gas turbine power station power supply, belonging to the technical field of aircraft starting power supply and gas source control. Background Art

[0002] Currently, aviation ground support equipment is used to support and maintain aircraft at airports. The support equipment mainly includes power supply vehicles and static power supplies, which control their output AC 115V / 400Hz and DC 28V power. After passing through the power distribution and control circuits, they are used for aircraft starting and power-on inspection.

[0003] However, this type of support equipment has the following operational flaws, mainly manifested in:

[0004] Poor security and convenience: Traditional power supply vehicles or gas source vehicles are large in size and mass, with low power density, making them inconvenient to move;

[0005] Poor security flexibility: The static variable power supply used must rely on the power grid for power supply, and cannot provide independent security or field security, requiring the support of other equipment and facilities;

[0006] Incomplete protection: Since the power supply and gas source used for maintenance are separated, integrated gas and electricity protection cannot be achieved;

[0007] In view of the above defects, it is necessary to improve the structure of the power supply and gas source control system used in the existing airport aircraft support and maintenance. Utility Model Content

[0008] In order to overcome the deficiencies in the prior art, the utility model aims to solve the technical problem of providing an improvement in the hardware structure of an aircraft starting power supply and an air source control system based on a gas turbine power station.

[0009] In order to solve the above technical problems, the technical solution adopted by the utility model is as follows: an aircraft starting power supply and gas source control system based on gas turbine power station power supply includes a trailer chassis, on which a micro aircraft engine, a permanent magnet generator, and a controller are installed. The micro aircraft engine consists of a single-stage centrifugal compressor, an annular combustion chamber, and a radial turbine. The rotor of the radial turbine is coaxially arranged with the motor rotor of the permanent magnet generator;

[0010] The low-pressure cabin air bleed end of the micro-aeroengine is provided with an air bleed device, the air bleed device is internally provided with a measurement and control system, the measurement and control system includes a pressure regulating valve, a flow control valve, and an air flow parameter sensor, the output end of the air bleed device is externally connected to an air bleed hose, and the air outlet end of the air bleed hose is arranged facing the de-icing operation area of ​​the airport aircraft;

[0011] The permanent magnet generator is composed of a stator casing, a coil winding, and a magnetic steel rotor. The coil winding is wound on the stator casing. The magnetic steel rotor is coaxially arranged with the motor rotor of the permanent magnet generator. The output end of the coil winding is connected to a voltage converter and a contactor and then connected to the output end of the starting power supply.

[0012] The controller is connected to the control ends of the micro-aero engine, the permanent magnet generator and the air induction device respectively through communication cables.

[0013] The trailer chassis is arranged on the airport power supply vehicle so that the trailer chassis can be towed by itself.

[0014] The specifications of the output power of the starting power output end of the permanent magnet generator are AC115V 400Hz and DC28V.

[0015] The air induction device specifically outputs compressed air with a pressure of 0.2-0.32 MPa, a flow rate of 6-25 kg / min, and a temperature of 60°C.

[0016] The airflow parameter sensor specifically detects the flow rate, temperature, and pressure parameters of the output airflow.

[0017] The controller model used to control the micro-aero engine and permanent magnet generator is DSP28335, and the controller model used for the external circuit and its protection system is STM32F103.

[0018] The beneficial effects of the present invention compared with the existing technology are as follows: the aircraft ground starting power supply and air source provided by the present invention have the advantages of convenient and flexible support compared with the existing ground support equipment. Compared with traditional power supply vehicles or air source vehicles, the control system provided by the present invention has a small volume and mass, high power density, can be transported by air, and can be flexibly deployed. Compared with static variable power supplies, the control system does not need to rely on power grid power supply, can achieve independent support and field support, and does not require the support of other equipment and facilities; the present invention can provide gas-electric integrated support functions. The control system uses a micro-aerospace engine to drive a high-speed permanent magnet generator to generate AC and DC power, while drawing compressed hot air from a micro-compressor for helicopter de-icing operations. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The present invention will be further described below with reference to the accompanying drawings:

[0020] Figure 1 It is a structural diagram of the utility model;

[0021] Figure 2 It is a structural schematic diagram of an embodiment of the present utility model. DETAILED DESCRIPTION

[0022] like Figure 1and Figure 2 As shown, the utility model provides an aircraft ground starting power supply and aircraft ground starting air source control solution based on gas turbine power station power supply. The power supply and air source control system provided can meet the electricity and air demand during aircraft support and maintenance, and solve the problems of existing aircraft starting power supply and air source separation, large volume, few supported aircraft models, poor maneuverability, etc.; the utility model adopts a micro-aeroengine as a power source, and utilizes its high speed characteristics to enable it to provide power far exceeding that of ordinary fuel engines under the same volume and mass. Under the premise of unchanged power, the volume of the engine and generator is reduced, so that it has the characteristics of high power density and miniaturization of equipment, and can be loaded onto an aircraft carrier platform to meet the requirements of rapid movement, flexible deployment, field maneuverability, and support.

[0023] In order to achieve the above technical effects, the aircraft starting power supply and air source control system structure provided by the present invention is as follows:

[0024] The trailer chassis comprises a micro-aero engine, a permanent magnet generator, and a controller. The micro-aero engine is composed of a single-stage centrifugal compressor, an annular combustion chamber, and a radial turbine. The rotor of the radial turbine is coaxially arranged with the motor rotor of the permanent magnet generator.

[0025] The low-pressure cabin air bleed end of the micro-aeroengine is provided with an air bleed device, the air bleed device is internally provided with a measurement and control system, the measurement and control system includes a pressure regulating valve, a flow control valve, and an air flow parameter sensor, the output end of the air bleed device is externally connected to an air bleed hose, and the air outlet end of the air bleed hose is arranged facing the de-icing operation area of ​​the airport aircraft;

[0026] The permanent magnet generator is composed of a stator casing, a coil winding, and a magnetic steel rotor. The coil winding is wound on the stator casing. The magnetic steel rotor is coaxially arranged with the motor rotor of the permanent magnet generator. The output end of the coil winding is connected to a voltage converter and a contactor and then connected to the output end of the starting power supply.

[0027] The controller is connected to the control ends of the micro-aero engine, the permanent magnet generator and the air induction device respectively through communication cables.

[0028] The trailer chassis is arranged on the airport power supply vehicle so that the trailer chassis can be towed by itself.

[0029] The controller model used to control the micro-aero engine and permanent magnet generator is DSP28335, and the controller model used for the external circuit and its protection system is STM32F103.

[0030] The control system mainly includes a trailer chassis, a micro-aero engine, a high-speed permanent magnet generator, an air induction device, and a control system. The trailer chassis is equipped with a self-propelled drive device, which can achieve short-distance self-traction and has a certain degree of maneuverability. It also provides corresponding storage space for accessories such as starting cables and air hoses.

[0031] The micro-aero engine consists of a single-stage centrifugal compressor, an annular combustion chamber, and a radial turbine. The rotor main shaft is coaxial with the motor rotor and supported by two bearings. The intake casing is designed with axial air intake, which forces heat dissipation from the outer wall of the motor stator as air flows into the intake duct. During operation, air is drawn into the compressor, pressurized, and sent into the combustion chamber. There, the air mixes with fuel and burns to form high-temperature, high-pressure combustion gas. This combustion gas then expands in the turbine, generating work that drives the turbine rotor and the motor rotor at high speed.

[0032] The installed micro-aircraft engine is used to provide power output to drive the high-speed permanent magnet generator. By connecting to the air bleed end of the micro-aircraft engine, compressed air with a certain pressure (0.2-0.32Mpa), flow rate (6-25kg / min) and temperature (60°C) is drawn out, which is used for de-icing operations before aircraft take off at the airport.

[0033] The high-speed permanent magnet generator provided by the utility model is a core component for generating AC / DC power. The motor is designed as an integrated starting and generating unit, and has both the function of starting the combustion engine and the function of generating electricity. The component is mainly composed of a stator casing, a coil winding, a magnetic steel rotor, and a rotor main shaft connected to the combustion engine. When in use, the micro-aeroengine rotor main shaft and the permanent magnet generator rotor are coaxially arranged to drive the magnetic steel rotor to rotate, thereby generating current in the stator coil, and forming a stable power supply for the power distribution system after rectification.

[0034] The control system provided by the utility model includes a controller. After receiving the control signal, the controller transmits the signal to the unit controller (ECU) and the generator controller to realize the action and power generation control of the micro-aeroengine and the high-speed permanent magnet generator.

[0035] The utility model is further provided with a set of air source output components, specifically connecting the bleed air device to the bleed air end of the low-pressure compartment of the aircraft engine for de-icing operations of airport aircraft; the provided bleed air device is mainly composed of a bleed air control system, a measurement control system, a flow / temperature / pressure measuring device, a bleed air flow control valve and a flow-limiting venturi; when working, the bleed air device controls the pressure regulating / shutoff valve and the bleed air flow control valve through the measurement control system, and simultaneously measures, displays and records the flow, pressure and temperature of the air flow, and transmits the acquired parameters to the controller.

[0036] When in use, the utility model firstly utilizes a micro-aero engine to generate power, which is driven by a power shaft to drive a high-speed permanent magnet generator to generate power, thereby generating high-power AC / DC power (AC115V 400Hz, DC28V) required to protect airport aircraft, and relies on devices such as contactors for power output; secondly, part of the hot air is drawn out from the bleed device, and hot air (60°C) with a certain pressure (0.2-0.32Mpa) and flow rate (6-25kg / min) is output to the aircraft through the bleed device for de-icing the aircraft.

[0037] Regarding the specific structure of the present invention, it should be noted that the connection relationship between the various component modules adopted in the present invention is definite and feasible. Except for the special instructions in the embodiments, the specific connection relationship can bring about corresponding technical effects and solve the technical problems raised by the present invention without relying on the execution of the corresponding software program. The components, modules, models of specific components appearing in the present invention, the connection methods between each other, and the conventional usage methods and expected technical effects brought about by the above-mentioned technical features, except for the specific instructions, all belong to the disclosed contents in patents, journal articles, technical manuals, technical dictionaries, and textbooks that can be obtained by technical personnel in this field before the application date, or belong to the existing technologies such as conventional technology and common knowledge in this field, and there is no need to elaborate, so that the technical solution provided in this case is clear, complete, and feasible, and the corresponding physical products can be reproduced or obtained based on this technical means.

[0038] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. An aircraft starting power supply and gas source control system based on a gas turbine power station, including a trailer chassis, characterized by: The trailer chassis is provided with a micro-aero engine, a permanent magnet generator, and a controller. The micro-aero engine is composed of a single-stage centrifugal compressor, an annular combustion chamber, and a radial turbine. The rotor of the radial turbine is coaxially arranged with the motor rotor of the permanent magnet generator. The low-pressure cabin air bleed end of the micro-aeroengine is provided with an air bleed device, the air bleed device is internally provided with a measurement and control system, the measurement and control system includes a pressure regulating valve, a flow control valve, and an air flow parameter sensor, the output end of the air bleed device is externally connected to an air bleed hose, and the air outlet end of the air bleed hose is arranged facing the de-icing operation area of ​​the airport aircraft; The permanent magnet generator is composed of a stator casing, a coil winding, and a magnetic steel rotor. The coil winding is wound on the stator casing. The magnetic steel rotor is coaxially arranged with the motor rotor of the permanent magnet generator. The output end of the coil winding is connected to a voltage converter and a contactor and then connected to the output end of the starting power supply. The controller is connected to the control ends of the micro-aero engine, the permanent magnet generator and the air induction device respectively through communication cables.

2. The aircraft starting power supply and gas source control system based on gas turbine power station power supply according to claim 1 is characterized in that: The trailer chassis is arranged on the airport power supply vehicle so that the trailer chassis can be towed by itself.

3. The aircraft starting power supply and gas source control system based on gas turbine power station power supply according to claim 1, characterized in that: The specifications of the output power of the starting power output end of the permanent magnet generator are AC115V 400Hz and DC28V.

4. The aircraft starting power supply and gas source control system based on gas turbine power station power supply according to claim 1, characterized in that: The air induction device specifically outputs compressed air with a pressure of 0.2-0.32 MPa, a flow rate of 6-25 kg / min, and a temperature of 60°C.

5. The aircraft starting power supply and gas source control system based on gas turbine power station power supply according to claim 1, characterized in that: The airflow parameter sensor specifically detects the flow rate, temperature, and pressure parameters of the output airflow.

6. The aircraft starting power supply and gas source control system based on gas turbine power station power supply according to claim 1, characterized in that: The controller model used to control the micro-aero engine and permanent magnet generator is DSP28335, and the controller model used for the external circuit and its protection system is STM32F103.

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