Effects of propellants temperature in gas-gas injector inlet on combustion performance and wall temperature

Mao Li; Yushan Gao; Ping Jin; Guobiao Cai

Effects of propellants temperature in gas-gas injector inlet on combustion performance and wall temperature

Mao Li^*
, Yushan Gao
, Ping Jin
, Guobiao Cai

^*此作品的通讯作者

宇航学院

Beihang University

科研成果: 期刊稿件 › 文章 › 同行评审

2 引用（Scopus）

摘要

A combustor with a shear tricoaxial gas-gas injector was researched numerically and experimentally. The influence of propellants temperature in the injector inlet on the combustion performance and wall temperature was investigated and analyzed. The numerical simulation results show that the variable momentum ratio of fuel to oxidizer which brought by the variable propellants temperature is the main factor. The influence of the fuel temperature on the combustion performance and wall temperature is more obviously than the oxidizer temperature. The experimental results validate the numerical simulation results.

源语言	英语
页（从-至）	1091-1094+1099
期刊	Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics
卷	37
期	9
出版状态	已出版 - 9月 2011

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@article{55fef9109d104ddd862ae70ddcd6a6fe,

title = "Effects of propellants temperature in gas-gas injector inlet on combustion performance and wall temperature",

abstract = "A combustor with a shear tricoaxial gas-gas injector was researched numerically and experimentally. The influence of propellants temperature in the injector inlet on the combustion performance and wall temperature was investigated and analyzed. The numerical simulation results show that the variable momentum ratio of fuel to oxidizer which brought by the variable propellants temperature is the main factor. The influence of the fuel temperature on the combustion performance and wall temperature is more obviously than the oxidizer temperature. The experimental results validate the numerical simulation results.",

keywords = "Combustion performance, Experiment, Numerical simulation, Shear tricoaxial injector, Wall temperature",

author = "Mao Li and Yushan Gao and Ping Jin and Guobiao Cai",

year = "2011",

month = sep,

language = "英语",

volume = "37",

pages = "1091--1094+1099",

journal = "Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics",

issn = "1001-5965",

publisher = "Beijing University of Aeronautics and Astronautics (BUAA)",

number = "9",

}

TY - JOUR

T1 - Effects of propellants temperature in gas-gas injector inlet on combustion performance and wall temperature

AU - Li, Mao

AU - Gao, Yushan

AU - Jin, Ping

AU - Cai, Guobiao

PY - 2011/9

Y1 - 2011/9

N2 - A combustor with a shear tricoaxial gas-gas injector was researched numerically and experimentally. The influence of propellants temperature in the injector inlet on the combustion performance and wall temperature was investigated and analyzed. The numerical simulation results show that the variable momentum ratio of fuel to oxidizer which brought by the variable propellants temperature is the main factor. The influence of the fuel temperature on the combustion performance and wall temperature is more obviously than the oxidizer temperature. The experimental results validate the numerical simulation results.

AB - A combustor with a shear tricoaxial gas-gas injector was researched numerically and experimentally. The influence of propellants temperature in the injector inlet on the combustion performance and wall temperature was investigated and analyzed. The numerical simulation results show that the variable momentum ratio of fuel to oxidizer which brought by the variable propellants temperature is the main factor. The influence of the fuel temperature on the combustion performance and wall temperature is more obviously than the oxidizer temperature. The experimental results validate the numerical simulation results.

KW - Combustion performance

KW - Experiment

KW - Numerical simulation

KW - Shear tricoaxial injector

KW - Wall temperature

UR - https://www.scopus.com/pages/publications/80555135559

M3 - 文章

AN - SCOPUS:80555135559

SN - 1001-5965

VL - 37

SP - 1091-1094+1099

JO - Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics

JF - Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics

IS - 9

ER -

Effects of propellants temperature in gas-gas injector inlet on combustion performance and wall temperature

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