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High-thrust liquid rocket engine and its low power consumption semi-self-starting method

A liquid rocket and engine technology, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc., can solve problems such as high spinning power, poor starting quality, and failure to realize engine reuse, so as to save starting gas consumption and reduce The effect of boost pressure

Active Publication Date: 2022-01-07
XIAN AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] The purpose of the present invention is to solve the problem that the starting quality of the existing liquid rocket engine is relatively poor, the required spin-up power is relatively large, or the engine cannot be reused, and a high-thrust liquid rocket engine and its low power are provided. self-starting method

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  • High-thrust liquid rocket engine and its low power consumption semi-self-starting method
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  • High-thrust liquid rocket engine and its low power consumption semi-self-starting method

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Embodiment Construction

[0107] In order to make the purpose, advantages and features of the present invention clearer, the high-thrust liquid rocket engine proposed by the present invention and its low-power semi-self-starting method will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0108] A high-thrust liquid rocket engine provided by the present invention includes two sets of main turbine pumps. The turbine works, and drives the oxygen pump (or fuel pump) to rotate. After the driving, the gas enters the thrust chamber through the pipeline, where further combustion reaction (supplementary combustion) occurs, and is ejected from the nozzle to generate thrust. Specific as figure 1 , figure 2 , image 3 As shown, the engine includes a gas system, an oxidant supply system, a fuel supply system and a starting system.

[0109] The gas system includes a thrust chamber 1, a first gas generator 2, a second gas generator 7, a first main tur...

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Abstract

The invention relates to a high-thrust liquid rocket engine and a low-power semi-autonomous starting method thereof to solve the problems that the existing liquid rocket engine starting methods have poor starting quality, relatively large spin-up power, and failure to realize repeated use of the engine. The engine includes a gas system, an oxidant supply system, a fuel supply system and a starting system, and the starting system includes a first high-pressure gas driving pipeline and a second high-pressure gas driving pipeline. The inlet of the first high-pressure gas driving pipeline is connected to the high-pressure gas source, and its outlet is connected to the inlet of the first main turbine; the inlet of the second high-pressure gas driving pipeline is connected to the high-pressure gas source, and its outlet is connected to the inlet of the second main turbine; the outlet of the oxygen pump is connected to the inlet of the second main turbine. The inlet of the oxygen pre-compression turbine is connected, the outlet of the oxygen pre-compression turbine is connected to the inlet of the oxygen pump; the outlet of the fuel pump or the outlet of the thrust chamber cooling pipeline is connected to the inlet of the fuel pre-compression turbine, and the outlet of the fuel pre-compression turbine is connected to the inlet of the fuel pump.

Description

technical field [0001] The invention relates to the field of liquid rocket engines, in particular to a high-thrust liquid rocket engine and a low-power semi-self-starting method thereof. Background technique [0002] The starting methods of liquid rocket engines mainly include self-starting and forced starting. [0003] The self-starting method needs to rely on the pressure of the storage tank and / or liquid column. For high-altitude propulsion devices, the pressure of the oxidant storage tank and fuel storage tank is usually very low. If the self-starting method is used, there is insufficient initial energy for starting under low inlet pressure. The problems caused by the turbo pump speed climb slowly, the pump is prone to cavitation, the overshoot of the gas temperature in the starting section is large, and the starting quality is poor. [0004] Therefore, the pump-pressed liquid rocket engines currently used for high-altitude propulsion (or need to be started at low inlet...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/46F02K9/56F02K9/58F02K9/62
CPCF02K9/46F02K9/56F02K9/58F02K9/563F02K9/62
Inventor 龚南妮徐浩海李春红王海燕武晓欣严俊峰张航
Owner XIAN AEROSPACE PROPULSION INST