RU2548833C1 - Aircraft power supply system - Google Patents

Abstract

FIELD: electricity.

SUBSTANCE: system comprises accumulator batteries, control, adjustment and protection equipment, DC-AC converter, thermoelectric elements consisting of hot- and cold-junction heat exchangers, and a charge controller. The hot-junction heat exchangers are mounted at inner surfaces of combustion chambers, flame stabilisers, turbojet engine afterburner. The cold-junction heat exchangers are mounted at the aircraft outer skin. The charge controller is coupled to output of thermoelectric elements and to input of accumulator batteries as well to input of DC-AC converter. Outputs of DC-AC converter as well as DC-DC outputs are the device outputs. Output of the DC-AC converter is connected to input of the controlling, adjusting and protecting unit. Output of accumulator batteries is coupled to DC-DC input of the converter. Output of the DC-DC converter is coupled to the input of the controlling, adjusting and protecting unit. Output of the controlling, adjusting and protecting unit is coupled to input of the accumulator batteries.

EFFECT: providing power supply to consumers when generators are not available.

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Description

The invention relates to auxiliary power units for aircraft and can be used in any aircraft equipped with engines having combustion chambers or afterburners.

A known energy supply system for aircraft [RU 2405720 C2, 01/10/2009], which contains an engine, a fuel cell system that provides the aircraft with electricity. Disadvantages: it requires the presence of fuel tanks for fuel and oxidizer, which leads to a heavier aircraft structure.

A well-known mobile power source (see, for example, Skrebov N.N., Medvedkov Yu.V., Polyarush V.P. Means of providing energy. M: Military publishing house, 1995, p.12), containing a series-connected converter of mechanical energy into electrical energy, a frequency control device, a mechanical energy control device and a mechanical energy source, as well as a voltage control device, the output of which is connected to the second input of the electric energy source, and the input to the output of the electric source oh energy, which is the output of the device. Disadvantages: use only in ground conditions, design complexity.

Also known is the aircraft power supply system [SU 1817623 A1, 04.29.1991], comprising alternating and direct current generators (which are converters of mechanical energy into electrical energy), rectifier devices with protection and control units and buses, batteries and switching equipment. Disadvantages: it does not provide for the conversion of the thermal energy of the combustible fuel of the aircraft into electrical energy, the complexity of the design.

Closest to the technical nature of the claimed invention is a DC power supply system (see, for example, Aircraft, its equipment and weapons. A textbook edited by PI Chinaev. M .: Military Publishing House, 1976, p. 289), containing alternating and direct current generators driven by aircraft engines and which are the main sources of electrical energy; rechargeable batteries working in parallel with generators and being emergency sources of electrical energy; regulation, control and protection equipment; converters of direct current to alternating single-phase and three-phase current of constant frequency; step-up transformers with rectifiers for high-voltage direct current.

The disadvantage is the use of dynamic converters (generators) as the main sources of electrical energy, which leads to a complex system for transmitting power flows, the lack of a battery charge controller.

The technical result achieved by the proposed system is to provide aircraft consumers with electrical energy received from static converters of thermal energy of combustible fuel, simplifying the design, and incorporating the battery charge controller into the system.

To achieve the specified technical result, a system for providing electric energy to aircraft is proposed, comprising a turbojet engine, storage batteries, regulation, control and protection equipment, a direct current to alternating current converter, into which thermoelectric elements consisting of heat exchangers of hot and cold junctions are additionally introduced, at the heat exchangers of the hot junctions of thermoelectric devices are located on the inner surfaces of the combustion chambers, stabil a flame ditch, an afterburner of a turbojet engine, and cold junctions heat exchangers are located on the outer skin of the aircraft, the charge controller, the input of which is connected to the output of thermoelectric devices, and the output - to the first input of the batteries, the first output of which is connected to the input of the DC / AC converter current, the first outputs of which are the first outputs of the device, and the second output is the first input of the control, control and protection unit, the second output of the batteries is connected n with the input of the DC-DC converter, the first outputs of which are the second outputs of the device, and the second output is the second input of the control, control and protection unit, the output of which is the second input of the batteries.

Electric consumers are provided with thermoelectric devices installed on the internal surfaces of combustion chambers, flame stabilizers and afterburners of a turbojet engine. Structurally, thermoelectric devices consist of heat exchangers of hot junctions of thermoelectric devices located on the internal surfaces of combustion chambers, flame stabilizers, afterburners and heat exchangers of cold junctions located on the outer skin of the aircraft. The work of thermocouples on the conversion of thermal energy into electrical energy occurs due to the resulting temperature difference between the heat exchangers of the hot junctions and the heat exchangers of the cold junctions, detailed in the textbook [edited by G.S. Lamberg. Elementary Textbook of Physics, Volume II. M .: Nauka, 1975, p. 211-216].

Simplification of the design is achieved due to the fact that the conversion of thermal energy into electrical energy occurs due to the physical properties of thermoelements, which does not require the installation of dynamic elements in the system design, such as alternating and direct current generators, mechanical energy control devices (reduction gears), presented in the analogue .

The main advantages of using thermoelectric devices are: the absence of mechanical transmission elements for transmitting torque from a mechanical energy source to a device for converting into electrical energy and, as a consequence, the absence of a mechanical energy control device; the ability to convert the thermal energy of the gas stream into electrical energy to meet the energy needs of the aircraft.

The invention is illustrated by drawings, where:

figure 1 shows a structural diagram of the placement of thermoelectric devices in a turbojet engine, including the following elements: 1 - input device; 2 - multistage compressor; 3 - combustion chamber; 4 - flame stabilizer; 5 - afterburner; 6 - adjustable jet nozzle; 7 - thermoelectric devices;

figure 2 shows a schematic diagram of the distribution of electricity to consumers, where 7 are thermoelectric devices; 8 - charge controller; 9 - battery pack; 10 - block regulation, control and protection; 11 - DC to AC single-phase and three-phase constant frequency current; 12 - DC-DC converter.

Charge controller type NC05; NC15 made by Steca CmbH is designed for high-quality battery charging, as well as for protection against overload and reverse current. Rechargeable batteries of type 15СЦС-45Б [Skrebov N.N., Medvedkov Yu.V., Polyarush V.P. Means of providing energy. M .: Military publishing house, 1995, p.82] are intended for power supply: unit of regulation, control and protection; Aircraft electrical energy consumer with idle aircraft engines.

The consumers are supplied with electric energy by direct current through a DC-DC converter.

Aircraft are supplied with electrical energy by alternating current converters of direct current to alternating current single-phase and three-phase direct current.

The SKiiP 3 type regulation, control and protection unit is designed for automated control of the working processes of rechargeable batteries, a direct current to alternating current single-phase and three-phase direct current alternating current, and a DC-DC converter under normal and emergency conditions. Information about the state of the batteries is supplied to the control, control and protection unit, in which the quantity and method of connecting the batteries is determined to provide the required parameters for consumers according to the following principle:

a) the reference voltage value is the load voltage. The regulation, control and protection unit sequentially connects the storage batteries from the first to the reference value;

b) the reference current value is the load current. The regulation, control and protection unit connects the batteries to the circuit in parallel until the reference value is reached;

c) when emergency conditions occur, the control, control and protection unit disconnects the load from consumers.

The inventive system operates as follows. The air stream rushes into the inlet 1 of the turbojet engine and then enters the multi-stage compressor 2, where it is compressed and enters the combustion chamber 3. In the combustion chamber 3, the air-fuel mixture is formed by spraying the fuel through nozzles, mixing it with air and burning the mixture. The resulting gas stream, having high temperature and pressure, rushes through the flame stabilizer 4 into the afterburner 5 and is released into the environment through an adjustable jet nozzle 6. In this case, the gas stream transfers part of the thermal energy to the internal surfaces of the combustion chamber 3, flame stabilizer 4 and afterburner 5, on which the heat exchangers of the hot junctions of thermoelectric devices 7 are located, the heat exchangers of the cold junctions are located on the outer skin of the aircraft. The conversion of thermal energy into electrical energy occurs due to the physical properties of thermocouples described in [edited by G.S. Lamberg. Elementary Textbook of Physics, Volume II. M .: Nauka, 1975, pp. 211-216] and other sources.

After the conversion, electric energy through the charge controller 8 enters the battery unit 9. The regulation, control and protection unit 10 carries out general control of electrical parameters; generates control signals both to a DC-DC converter into alternating single-phase and three-phase currents of constant frequency 11, and to a DC-DC converter 12 for powering consumers, direct and alternating current based on load values, and when emergency conditions occur, disconnects the load from consumers.

The placement of hot junctions of thermoelectric devices on the inner surfaces of combustion chambers, flame stabilizers, afterburners in their weight and size parameters will not prevent the formation of a jet of gas, which is the driving force of the aircraft.

A comparative analysis of the presented solution with analogues allows us to conclude that the claimed invention differs from the known analogues by the combination of essential distinguishing features, meets the patentability conditions of “novelty” and industrial applicability.

Claims (1)

Aircraft electric power supply system comprising a turbojet engine, storage batteries, regulation, control and protection equipment, a direct current to alternating current converter, characterized in that thermoelectric elements consisting of hot and cold junctions heat exchangers are additionally introduced, while hot junctions heat exchangers thermoelectric devices are located on the inner surfaces of combustion chambers, flame stabilizers, afterburner turbojet engines the heater, and the cold junctions heat exchangers are located on the outer skin of the aircraft, the charge controller, the input of which is connected to the output of thermoelectric devices, and the output - to the first input of the batteries, the first output of which is connected to the input of the DC / AC converter, the first outputs of which are the first outputs of the device, and the second output is the first input of the control, control and protection unit, the second output of the batteries is connected to the input of the DC-DC converter, the first outputs of which are outputs of the second device and the second input a second output control unit, control and protection, the output of which is the second input of the batteries.

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