阅读说明：本技术 一种用于火箭发动机的燃料电池供给系统 (Fuel cell supply system for rocket engine ) 是由 秦江 郭发福 党朝磊 姬志行 章思龙 于 2019-10-23 设计创作，主要内容包括：一种用于火箭发动机的燃料电池供给系统,属于火箭发动机技术领域。本发明解决了现有的火箭发动机供给系统无法满足对小型运载火箭较短研发周期和较高灵活性要求的问题。电动燃料泵的入口与燃料罐连通,电动燃料泵的出口分别与若干冷却通道的入口连通,每个冷却通道的出口均与固体氧化物燃料电池的阳极入口及所述燃料喷射器连通；电动氧化剂泵的入口与氧化剂罐连通,电动氧化剂泵的出口分别与固体氧化物燃料电池的阴极入口及氧化剂喷射器连通,所述固体氧化物燃料电池与电能控制分配系统电联接,且电能控制分配系统分别与蓄电池及电动机电联接,所述电动机、所述电动氧化剂泵以及所述电动燃料泵同轴固接。(A fuel cell supply system for a rocket engine belongs to the technical field of rocket engines. The invention solves the problem that the existing rocket engine supply system can not meet the requirements of short research and development period and high flexibility of the small carrier rocket. The inlet of the electric fuel pump is communicated with the fuel tank, the outlet of the electric fuel pump is respectively communicated with the inlets of the plurality of cooling channels, and the outlet of each cooling channel is communicated with the anode inlet of the solid oxide fuel cell and the fuel injector; the inlet of the electric oxidant pump is communicated with the oxidant tank, the outlet of the electric oxidant pump is respectively communicated with the cathode inlet of the solid oxide fuel cell and the oxidant ejector, the solid oxide fuel cell is electrically connected with the electric energy control distribution system, the electric energy control distribution system is respectively electrically connected with the storage battery and the motor, the electric oxidant pump and the electric fuel pump are coaxially and fixedly connected.)

1. A fuel cell supply system for a rocket engine, characterized by: the fuel-saving and energy-saving combustion chamber comprises a fuel tank (1), an electric fuel pump (2), an oxidant tank (3), an electric oxidant pump (4), a solid oxide fuel cell (5), an electric energy control distribution system (6), a motor (7), a storage battery (8), a combustion chamber (9) and a main spray pipe (10), wherein a plurality of cooling channels (11) are arranged on the periphery of the outer wall of the main spray pipe (10), the combustion chamber (9) comprises a fuel injector and an oxidant injector,

the inlet of the electric fuel pump (2) is communicated with the fuel tank (1), the outlet of the electric fuel pump (2) is respectively communicated with the inlets of a plurality of cooling channels (11), and the outlet of each cooling channel (11) is communicated with the inlet of the anode (5-1) of the solid oxide fuel cell (5) and the fuel injector; the inlet of an electric oxidant pump (4) is communicated with an oxidant tank (3), the outlet of the electric oxidant pump (4) is respectively communicated with the inlet of a cathode (5-2) of a solid oxide fuel cell (5) and an oxidant ejector, the solid oxide fuel cell (5) is electrically connected with an electric energy control distribution system (6), the electric energy control distribution system (6) is respectively electrically connected with a storage battery (8) and an electric motor (7), and the electric motor (7), the electric oxidant pump (4) and the electric fuel pump (2) are coaxially and fixedly connected.

2. A fuel cell supply system for a rocket engine as recited in claim 1, wherein: the device also comprises a secondary spray pipe (12), and an anode (5-1) outlet and a cathode (5-2) outlet of the solid oxide fuel cell (5) are both communicated with the secondary spray pipe (12).