A turboprop-high temperature fuel cell hybrid propulsion and energy integration system for aircraft

Abstract

The invention discloses a turboprop-high temperature fuel cell hybrid propulsion and energy integration system for aircraft, which belongs to the field of aircraft propulsion and energy. The integrated system of the present invention includes a supply system, a partial oxidation reformer, a metal-supported solid oxide fuel cell system, and an aircraft propulsion system. The aircraft propulsion system includes a propeller fan, a high-pressure compressor, a low-pressure compressor, a combustion chamber, and a high-pressure turbine. Low-pressure turbine and power turbine; supply system includes fuel delivery channel, air delivery channel, gas delivery channel, return flow delivery channel and fuel delivery pump. The invention solves the problems of high fuel consumption rate of the traditional aero-engine, low power generation efficiency of the turbine engine, poor stability under variable working conditions, and the like. The integrated system of the present invention is applicable to aircraft.

Description

technical field [0001] The invention relates to a novel turboprop-high temperature fuel cell hybrid propulsion and energy integration system for aircraft, which belongs to the field of aircraft propulsion and energy. Background technique [0002] At present, aircraft power generation systems and propulsion systems generally have problems of low thermal efficiency and high pollutant emissions. With the increase in the power of airborne equipment on aircraft (airships, military drones, military manned aircraft, and passenger aircraft), there are strict requirements on carbon emissions and pollutant emissions from aircraft in various countries. Therefore, there is an urgent need for an aircraft integrated propulsion energy system with high electric power ratio, high efficiency, and low emission. [0003] This issue has been extensively studied at home and abroad. It has been proposed that aircraft use clean fuels such as biomass, hydrogen, and alcohols. However, such fuels n...

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Problems solved by technology

[0004] In order to overcome the problems of low thermal efficiency, low power generation efficiency, and poor performance under variable working conditions of the existing aircraft propulsion system, which lead to limited flight time and difficulty in meeting long-duration missions under high electric power ratio, the present invention provides a For the new turboprop-high temperature fuel cell hybrid propulsion and energy integration system of the aircraft, this system can be used in the aircraft, and the technical solution adopted is:

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