Closed Brayton cycle-semiconductor temperature difference combined power generation system for aircraft

Abstract

The invention provides a closed Brayton cycle-semiconductor temperature difference combined power generation system for an aircraft. The system comprises a fuel tank, a fuel electric pump, a semiconductor temperature difference power generation device, a fuel heat exchanger, a high-temperature heat exchanger, a cooler, a gas compressor, a turbine and a power generator. The fuel electric pump is connected with the cold side inlet of the cooler, the cold side outlet is connected with the cold side inlet of the semiconductor thermoelectric power generation device, and the cold side outlet is connected with the inlet of the fuel heat exchanger. The outlet of the fuel heat exchanger is connected with a hot side inlet of the high-temperature heat exchanger, the hot-side outlet of the cooler is connected with the compressor, and the compressor is connected with the cold-side inlet of the high-temperature heat exchanger. The cold-side outlet is connected with the turbine, and the turbine is connected with the hot-side inlet of the cooler. The hot side outlet of the high-temperature heat exchanger is connected with the hot side inlet of the semiconductor thermoelectric power generation device, and the hot side outlet of the semiconductor thermoelectric power generation device is connected with the fuel injector. According to the present invention, the high-temperature heat energy of thehypersonic aircraft is fully converted into the electric energy through gradient utilization of energy.

Description

technical field [0001] The invention belongs to the field of aircraft thermal protection and power generation, and in particular relates to a closed Brayton cycle-semiconductor temperature difference combined power generation system for aircraft. Background technique [0002] Hypersonic aircraft is a new type of next-generation aviation / aerospace vehicle for hypersonic flight, which can be used in military, civil aviation, and space-to-earth travel, such as global rapid long-range strikes, intercontinental high-speed passenger / cargo transportation, and single / multi-stage The orbiting system has been highly valued by researchers at home and abroad, and represents an important development direction in the field of aircraft in the future. [0003] As the flight Mach number increases, the total temperature of the incoming flow increases, resulting in a significant increase in the heat flux density in the combustion chamber. The ensuing thermal protection problem has become one ...

AI Technical Summary

Problems solved by technology

The ramjet engine works at a high Mach number, canceling the compressor, turbine and rotating shaft, and the traditional airborne power generation system that takes power from the main shaft of the engine to drive the generator loses its applicability

However, the air turbine power generation method is limited by the difficulty of gas extraction at high Mach numbers and the thermal protection of the air turbine, and its application prospects are also very limited.

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