Super-conducting electromagnetic pump circulating system of liquid rocket engine

A circulation system and electromagnetic pump technology, which is applied in the direction of rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of low technical difficulty of the open circulation system, insufficient use of propellant, high cost of engine design and manufacturing, etc. Achieve the effects of strong reusability, low difficulty in design and manufacture, and light structure

Inactive Publication Date: 2010-04-14
BEIHANG UNIV
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Problems solved by technology

However, the afterburning cycle engine system is more complex, and because all components work under higher pressure, the engine structure is heavier
[0005] The technical difficulty of the open cycle system is small, the technology is mature, and the cost of engine design and manufacture is low, but due to the bypass lo

Method used

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  • Super-conducting electromagnetic pump circulating system of liquid rocket engine
  • Super-conducting electromagnetic pump circulating system of liquid rocket engine
  • Super-conducting electromagnetic pump circulating system of liquid rocket engine

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Embodiment Construction

[0015] The present invention will be further described below in conjunction with the accompanying drawings.

[0016] Before the engine is started, liquid hydrogen and liquid oxygen enter through the liquid hydrogen inlet 19 and the liquid oxygen inlet 20 to fill and pre-cool the entire engine system pipeline, and utilize the low temperature characteristics of liquid hydrogen and liquid oxygen to control the superconducting circuit 22, The liquid hydrogen superconducting electromagnetic pump 23, the liquid oxygen superconducting electromagnetic pump 24 and the magnetic fluid power generation part 28 are cooled, so that the superconducting circuit 22 in the system, the hydrogen circuit superconducting electromagnetic pump 23, the oxygen circuit superconducting electromagnetic pump 24, the magnetic The superconductor material in the fluid power generation component 28, as well as the superconductor material elsewhere in the system, all enter a superconducting state. Then the star...

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Abstract

A super-conducting electromagnetic pump circulating system of a liquid rocket engine is a pump-fed circulating system built on the basis of the super-conducting technique and the magnetofluid generator technique and applied to the liquid rocket engine utilizing cryogenic propellants. A magnetofluid component arranged at the throttle of a thrust chamber of the liquid rocket engine transforms one portion of heat energy of gas of the engine into electric energy, and then the electric energy is transmitted to a super-conducing electromagnetic pump. The super-conducting electromagnetic pump is driven by the electric energy, and an impeller thereof rotates in a high speed, thereby increasing pressure of fuel or oxidants. The super-conducting electromagnetic pump circulating system of a liquid rocket engine is high in performance and reliability and strong in reusability, and is easy to realize multiple starting.

Description

【Technical field】 [0001] The invention relates to a circulation system of a liquid rocket engine, which is a pump pressure circulation system different from a turbo pump circulation established on the basis of a magnetic fluid generator technology and a high temperature superconducting technology. 【Background technique】 [0002] At present, most of the circulation systems of large liquid rocket engines are turbo pump circulation systems, and the turbo pump circulation is divided into two types: open cycle and closed cycle. [0003] Gas generator cycle (Gas Generator cycle, GG) is the most common open cycle, and its system diagram is as follows figure 1 shown. The system includes a fuel pump 3 , an oxidant pump 4 , a gas generator 5 , a fuel turbine 6 , an oxidant turbine 7 , a thrust chamber 8 , and gas nozzles 9 and 10 after the turbine. The direction of the arrow in the figure represents the flow direction of the propellant in the pipeline. Fuel and oxidant enter from f...

Claims

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Application Information

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IPC IPC(8): F02K9/46
Inventor 郑力铭孙冰
Owner BEIHANG UNIV
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