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

A liquid rocket and engine technology, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc. It can solve problems such as poor starting quality, inability to reuse engines, and high spin-up power

Active Publication Date: 2021-04-09
XIAN AEROSPACE PROPULSION INST
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  • 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 requir

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

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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-consumption semi-self-starting method thereof, and aims to solve the problems that an existing liquid rocket engine starting mode is poor in starting quality, the required swirling power is large, and the repeated use of the engine cannot be achieved. The engine comprises a gas system, an oxidant supply system, a fuel supply system and a starting system, wherein the starting system comprises a first high-pressure gas driving pipeline and a second high-pressure gas driving pipeline, an inlet of the the first high-pressure gas driving pipeline is connected with a high-pressure air source, an outlet of the first high-pressure gas driving pipeline is connected with an inlet of a first main turbine, an inlet of the the second high-pressure gas driving pipeline is connected with the high-pressure air source, an outlet of the second high-pressure gas driving pipeline is connected with an inlet of a second main turbine, an outlet of an oxygen pump is connected with an inlet of an oxygen preloading turbine, an outlet of the oxygen preloading turbine is connected with an inlet of the oxygen pump, an outlet of a fuel pump or an outlet of a thrust chamber cooling pipeline is connected with an inlet of a fuel preloading turbine, and an outlet of the fuel preloading turbine is connected with an 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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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
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