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

Abstract

The invention discloses a novel turboprop-high temperature fuel cell hybrid propulsion and energy integration system for an aircraft, and belongs to the aircraft propulsion and energy field. The integration system of the present invention comprises a supply system, a partial oxidation reformer, a metal supported solid oxide fuel cell system and an aircraft propulsion system. The aircraft propulsion system comprises a paddle fan, a high pressure compressor, a low pressure compressor, a combustion chamber, a high pressure turbine, a low pressure turbine and a power turbine. The supply system includes a fuel delivery passage, an air delivery passage, a fuel gas delivery passage, a reflux delivery passage, and a fuel delivery pump. The present invention solves the problems of high fuel consumption rate in traditional aeroengines, low efficiency of engine driven power generation and poor stability of variable working condition in turbine engines. The integration system of the invention is suitable for use in an 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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