A solid oxide fuel cell gas turbine distributed hybrid propulsion system for aircraft

Abstract

The invention provides a solid oxide fuel cell fuel gas turbine distributed hybrid propulsion system for an aircraft, and belongs to the technical field of aircraft propulsion systems. The propulsionsystem is applied to the field of aircraft manufacturing, and specifically comprises a substance supply system, a main propulsion system and an auxiliary propulsion system. According to the propulsionsystem, different from an existing turbine engine or an internal combustion engine, a core separation distributed propulsion system is adopted. The propulsion system solves the problem that an existing aircraft propulsion system cannot meet the high-speed long-time navigation requirement, the cost is reduced, the noise is reduced, the emission of nitrogen oxides is reduced, and the aircraft voyage, aircraft variable working condition capability and other characteristics are improved; and meanwhile, compared with an existing Boeing 737 aircraft, the system can reduce 80% of oil consumption.

Description

technical field [0001] The invention relates to a solid oxide fuel cell gas turbine distributed hybrid propulsion system for aircraft, belonging to the technical field of aircraft propulsion systems. Background technique [0002] Most aircraft today are propelled by a single or two engines. Such an engine arrangement for an aircraft will result in a poor match between thrust, lift, drag, and gravity. This further leads to low propulsion efficiency of the aircraft, making it difficult to further increase the speed, load, and range of the aircraft. Such status quo limits the further development of aircraft. Few adopt four, six or eight engines to propel the aircraft. Due to the simple superposition of a turbine engine or an internal combustion engine. Although the thrust, lift, drag, and weight matching have been improved, the reasons for the low thermal efficiency of the engine have not been fundamentally resolved. [0003] Therefore, various airlines and scientific rese...

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Problems solved by technology

[0004] In order to solve the technical problems of the unreasonable layout of the propulsion system of the existing aircraft, the high cost of maintaining the lift-drag balance, and the inability to meet the requirements of low noise, low fuel consumption, and low pollutant discharge of the aircraft, the present invention proposes a solid oxidizer for the aircraft. The distributed hybrid propulsion system of bio-fuel cell gas turbine adopts the following technical solutions:

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