|Table of Contents|

Effect of heater fuel on simulated incoming flow of ramjet(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2019年06期
Page:
45-52
Research Field:
研究与技术
Publishing date:

Info

Title:
Effect of heater fuel on simulated incoming flow of ramjet
Author(s):
LI Xiaoping1;  TANG Min2;  XIAO Hong2
(1.Northwest Poly-technology University, Xi’an 710072, China; 2.Xi’an Aerospace Propulsion Institute, Xi’an 710100, China)
Keywords:
ramjet;  ground test;  heater;  simulated incoming flow;  fuel selection
PACS:
V439
DOI:
-
Abstract:
Based on the ground test simulation problem of typical state of ramjet engine, the ground test system can only provide the hot air with high temperature, high pressure and large flow rate by burning chemical fuel directly in heater.In order to study the effect of heater fuel on the simulated incoming flow characteristics in the engine test, the effect of heater fuel on the simulated airflow composition with/without oxygen supplement were compared and analyzed through the thermodynamic calculation of five kinds of heater fuel.The results show that the specific heat ratio of simulated gas generated by commonly used fuels is less than the true value under the conditions of oxygen supplementation and no oxygen supplementation.When the Mach number is 2.5～3, the molecular weight of simulated gas generated by alcohol or isobutane is close to the true value, while the Mach number is 3.5～4, the alcohol is selected to be close to the true value.The heater with oxygen-supplement can significantly reduce the pollution components in the simulated gas.

References:

[1] 李小平, 葛李虎, 栾希亭.加热器在冲压发动机试验技术中的应用研究[J].火箭推进, 2007, 33(3):14-19.LI X P, GE L H, LUAN X T.Applications of gas generator in ramjet direct-connect test facility[J].Journal of Rocket Propulsion, 2007, 33(3):14-19.
[2] 田宪科, 唐硕, 田宪长.超燃冲压发动机性能影响因素分析[J].航空计算技术, 2015, 45(5):15-19.
[3] FOTIA M L, DRISCOLL J F.Isolator-combustor interactions in a direct-connect ramjet-scramjet experiment[J].Journal of Propulsion and Power, 2012, 28(1):83-95.
[4] ROUX J A, CHOI J, SHAKYA N.Parametric scramjet cycle analysis for nonideal mass flow rate[J].Journal of Thermophysics and Heat Transfer, 2014, 28(1):166-171.
[5] 王雷雷.碳氢燃料超临界压力流/固/热耦合数值模拟研究[D].杭州:浙江大学, 2013.
[6] 张亚.直联式超燃试验台燃气取样系统设计与分析[D].上海:上海交通大学, 2013.
[7] JEFFREY S,STEPPHEN H, HARVIN F.The NASA langley research center 8-ft high temperature tunnel[J].Progress in Astronautics and Aeronautics,2002(198):405-425.
[8] 刘敬华.超燃冲压发动机试验研究的国外动态[J].飞航导弹, 2002(3):46-48.
[9] 冯军红.高焓高压空气加热器数值仿真与试验研究[D].长沙:国防科学技术大学, 2011.
[10] 张贵田.高压补燃液氧煤油发动机[M].北京:国防工业出版社, 2005.
[11] 马翰英.火箭用煤油基本物性参数[Z].1992.
[12] 马庆芳,方荣生.实用热物理性质手册[M].北京:中国农业机械出版社,1986.
[13] 中华人民共和国军用标准.北半球标准大气:GJB365.1-1987[S].北京:国防科学技术工业委员会,1987.
[14] 于守志.飞航导弹动力装置试验技术[M].北京:宇航出版社, 1990.
[15] 航空发动机设计用材料数据手册编委会.航空发动机设计用材料数据手册(第五册)[M].北京:航空工业出版社, 2000.
[16] 陈延辉.日本的高超声速吸气式发动机试验设备及试验技术[J].飞航导弹, 2006(2):41-48.

Memo

Memo:
-
Last Update: 2019-12-20