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A gas-oxygen/kerosene vortex cooling combustor

A combustion chamber and kerosene technology, which is applied in the aerospace field, can solve the problems of low combustion efficiency, carbon deposition on the wall and nozzle outlet, and small structure size, and achieves the effects of reliable ignition, reliable thermal protection, and effective thermal protection.

Active Publication Date: 2020-09-15
XIAN AEROSPACE PROPULSION INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the small size of the gas-oxygen / kerosene attitude control engine, if kerosene tissue cooling is used, it will cause serious carbon deposits on the wall and nozzle outlets. Although the film cooling method achieves the purpose of eliminating carbon deposits, the combustion efficiency is low

Method used

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  • A gas-oxygen/kerosene vortex cooling combustor
  • A gas-oxygen/kerosene vortex cooling combustor
  • A gas-oxygen/kerosene vortex cooling combustor

Examples

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Embodiment

[0043] Taking 150N gas-oxygen / kerosene vortex cooling combustion chamber as an implementation case, the combustion chamber structure can be obtained through reasonable combustion chamber structure parameter matching. figure 1 Shown. Compressible ideal gas, balanced non-adiabatic PDF (probability density model) non-premixed combustion model, RNG k-ε turbulence model and discrete atomization model are used for simulation calculation verification.

[0044] The axial velocity and streamline distribution in the vortex cooling combustion chamber are as follows: figure 2 with image 3 Shown. The axial velocity in the cylindrical section of the thrust chamber has a reverse interface, which indicates that an inner and outer double vortex structure is formed in the thrust chamber; a stable low-speed recirculation zone is formed on both sides of the injection panel of the combustion chamber, which is conducive to propellant mixing and reliability Ignition, flame stability and increase comb...

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Abstract

A gas oxygen / kerosene swirl cooled combustion chamber include a head base, body, nozzle, oxygen and kerosene systems, A main body of that head, a body and a nozzle are fixedly connecte from the top tothe bottom to form an integral structure, a combustion chamber cavity is arrange in the body, oxygen is tangentially injected into the combustion chamber cavity by a gas-oxygen system to form a double-swirling airflow structure of an outer swirl current and an inner swirl current, a kerosene system is connecte to the head, and kerosene is injected into the combustion chamber cavity and oxygen inthe inner swirl region to realize mixed combustion. The invention limits the mixing combustion process of the bipropellant to the central region of the combustion chamber, and achieves the purpose ofcooling the wall surface and preventing carbon deposition through the outer oxygen swirling flow. An open centrifugal nozzle and a rotary adjusting sleeve are designed at the head of the combustion chamber. After the fuel is atomized, the internal swirl region and oxygen are mixed to form a stable recirculation zone near the kerosene nozzle outlet, which ensures the reliable ignition and stable combustion of the propellant. The combustor has simple structure, no cooling, good maintenance performance and low cost.

Description

Technical field [0001] The invention relates to a gas-oxygen / kerosene swirl-cooled combustion chamber, in particular to a gas-liquid propellant combined swirl-cooled combustion chamber, belonging to the field of aerospace. Background technique [0002] The main power system of the new-generation launch vehicle adopts non-toxic liquid oxygen / hydrogen and liquid oxygen / kerosene engines, while the auxiliary power system currently uses hydrazine propellants. Therefore, in order to achieve the integration of full-arrow propellants, non-toxic , Research on non-polluting rocket auxiliary power and its key technologies. Relevant scientific research units have carried out the research and development of the carrier rocket's gas-oxygen / kerosene attitude control engine, and have overcome many key technologies, but the problems of engine cooling and kerosene coking have not been solved. Due to the small size of the gas-oxygen / kerosene attitude control engine, the use of kerosene tissue cool...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/38F02K9/52F02K9/66
CPCF02K9/52F02K9/66F23R3/38
Inventor 王勇王储杨伟东
Owner XIAN AEROSPACE PROPULSION INST
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