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Gas-gas nozzle with constriction section

A shrinking section and gas nozzle technology, which is applied in the field of liquid rocket engine nozzles, can solve the problems of small pressure drop of oxidant nozzles and affecting engine performance, etc.

Inactive Publication Date: 2010-06-16
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, if the coaxial shear nozzle with traditional structure is used, when the outlet velocity of the oxygen nozzle is too small, the pressure drop of the oxidizer nozzle will be too small, and the pressure fluctuation of the combustion chamber will be transmitted to the head chamber of the oxygen nozzle, which will affect the working performance of the engine

Method used

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Embodiment Construction

[0012] The invention proposes a gas-gas nozzle with a constricted section for the first time, which can prevent the pressure fluctuation of the combustion chamber from being transmitted into the head cavity, and make the propellant achieve high combustion efficiency. The gas-gas nozzle with a contraction section and its design method are provided, which can ensure efficient and stable combustion of the propellant, and the design method is simple and effective.

[0013] Such as figure 1 The shown gas-gas nozzle with converging section includes nozzle inlet short (1), converging section (2), outlet section (3) and fuel nozzle (6). The inlet section of the nozzle is cylindrical, and its area is 1.5 to 2 times the area of ​​the contracting section; the length of the inlet section is 5 to 10 mm; the contracting section and the inlet section adopt a tapered transition, and the angle is 90 to 120 degrees. Through the selected pressure drop and flow coefficient of the oxidant nozzle,...

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Abstract

The invention relates to a gas-gas nozzle with a constriction section. A constriction section is additionally arranged in an oxidant channel. The nozzle with the constriction section comprises an inlet section (1), a constriction section (2) and a nozzle outlet section (3). A propellant is used for forming a certain inlet pressure drop at the head part of a combustion chamber to reduce the speed of an oxidant outlet and the pressure drop of a fuel nozzle. The speed of the oxidant outlet is reduced so as to be beneficial to the combustion of the propellant in the combustion chamber, the design of an engine supply system and the improvement of the combustion efficiency of the propellant.

Description

【Technical field】 [0001] The invention relates to a liquid rocket engine nozzle, in particular to a coaxial shear gas-gas nozzle with an oxidizer and a constricted section. 【Background technique】 [0002] The nozzle is an important part of the liquid rocket engine. Its function is to introduce the propellant into the combustion chamber, organize the combustion of the propellant, make the ratio of fuel and oxidizer in the mixture proper, and distribute the components evenly along the cross-section of the combustion chamber. [0003] A liquid rocket engine is an engine in which the propellant is liquid, however, in some types of liquid rocket engines, the fuel and oxidant have been converted into a gaseous state before being injected into the combustion chamber for mixing and combustion, so research on gas-gas nozzle technology is required . For example, in a full-flow afterburning cycle liquid rocket engine, the liquid propellant at all flows first enters the oxygen-enriched...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/52
Inventor 蔡国飙杜正刚汪小卫
Owner BEIHANG UNIV
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