Dual concentric gas-gas nozzle

A dual-coaxial, gas-nozzle technology, applied in jet propulsion devices, rocket engine devices, machines/engines, etc., can solve the problems of propellant incombustibility and combustion efficiency reduction

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 a coaxial shear nozzle with a traditional structure is used, when the flow rate of a single nozzle is greatly increased, the propellant cannot be completely combusted in the combustion chamber, resulting in a decrease in combustion efficiency

Method used

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Examples

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Embodiment Construction

[0015] The invention firstly proposes a double coaxial gas-gas nozzle, which can realize high combustion efficiency under the condition of large flow. The invention provides a double-coaxial gas-gas nozzle and a design method thereof, which can ensure efficient and stable combustion of the propellant, and the design method is simple and effective. The engine with double coaxial nozzles can greatly reduce the number of nozzles in the head.

[0016] Such as figure 1 , 2 , the double-coaxial air-gas nozzle shown in 3, comprises nozzle main body (1) and cylindrical sleeve (2), and nozzle main body (1) is cylindrical, by the upper section (4), middle section (5) of decreasing outer diameter Composed of the lower section (6), the side wall of the cylindrical sleeve is provided with a plurality of through holes (3), and one end of the cylindrical sleeve (2) is connected to the shoulder (7) between the upper section and the middle section of the nozzle body (1) to form a Integral, ...

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Abstract

The invention relates to a dual concentric gas-gas nozzle, which ensures that a propellant forms a 'fuel-oxidant-fuel' distribution form in a motor combustor to increase contact area of the fuel and the oxidant so as to form an inner annular combustion surface and an outer annular combustion surface in the combustor. The nozzle comprises a nozzle main body (1) and a cylinder sleeve (2), wherein the side wall of the cylinder sleeve is provided with a plurality of through holes (3); the nozzle main body and the cylinder sleeve are connected into a whole; an annular cavity (8) is formed between the cylinder sleeve and the nozzle main body; a central spray orifice (9) and an annular spray orifice (10) are formed in the nozzle main body; the side of the nozzle main body is provided with a radial hole (11) to ensure that the central spray orifice (9) is communicated with the annular cavity (8); and the upper end face of the nozzle main body is provided with a fluid channel (12) communicated with the annular spray orifice (10). The dual concentric gas-gas nozzle can accelerate combustion process and shorten combustion length, can ensure that the propellant realizes high combustion efficiency under a working condition of large flow, and can greatly reduce the quantity of head nozzles so as to reduce structural complexity and manufacturing cost.

Description

【Technical field】 [0001] The invention relates to a liquid rocket engine nozzle, in particular to a double-coaxial gas-gas nozzle which forms a "fuel-oxidant-fuel" propellant distribution in a combustion chamber. 【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 al...

Claims

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Application Information

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IPC IPC(8): F02K9/52
Inventor 蔡国飙杜正刚高玉闪
Owner BEIHANG UNIV
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