碳氢燃料超燃冲压发动机油气涡轮做功能力评估

推进技术 ›› 2013, Vol. 34 ›› Issue (12): 1708-1712.

碳氢燃料超燃冲压发动机油气涡轮做功能力评估

张铎¹,鲍文¹,秦江¹,黎林林²

哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150006;哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150006;哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150006;北京动力机械研究所,北京 100074

发布日期:2021-08-15
作者简介:张铎(1987—),男,博士生,研究领域为高超声速推进技术,发动机热防护,发动机热力循环。 E-mail:zhangduo198751@163.com

Evaluation of Fuel Vapor Turbine Capacity for Doing Work Onboard for a Hydrocarbon Fueled Scramjet

College of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150006, China;College of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150006, China;College of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150006, China;Beijing Power Machinery Institute, Beijing 100074, China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究油气涡轮泵燃油供给系统中,碳氢燃料裂解油气的做功能力,以正癸烷为替代燃料,基于其裂解后的实验组分分析,发展了基于Soave-Redlich-Kwong(SRK)状态方程的真实气体裂解混合物的等熵焓降计算方法,并对油气涡轮的做功能力进行了分析和评估。研究表明,当膨胀起始温度为950K,膨胀起始压力超过3MPa,膨胀比为2时,裂解混合物的等熵焓降可达110kJ/kg,具备较强的做功能力。 

关键词: 超燃冲压发动机;碳氢燃料;油气涡轮;等熵焓降 

Abstract: To evaluate the fuel vapor capacity for doing work in fuel vapor turbopumpfeeding system, n-decane was selected as surrogate fuel and experimental tests were firstly carried out to discover the components information of cracked fuel vapor at various thermophysical conditions. The thermophysical properties of real fuel vapor were then calculated by Soave-Redlich-Kwong (SRK) equation of state.At last, the isentropic enthalpy drop of real fuel vapor was calculated. With an initial temperature of 950K and an initial pressure over 3MPa, an isentropic enthalpy drop of 110kJ/kg is available when the expansion ratio is 2, which indicates that strong capacity for doing work can be achieved.

Key words: Scramjet; Hydrocarbon fuels; Fuel vapor turbine; Isentropic enthalpy drop

张铎,鲍文,秦江,黎林林. 碳氢燃料超燃冲压发动机油气涡轮做功能力评估[J]. 推进技术, 2013, 34(12): 1708-1712.

ZHANG Duo¹, BAO Wen¹, QIN Jiang¹, LI Lin-lin². Evaluation of Fuel Vapor Turbine Capacity for Doing Work Onboard for a Hydrocarbon Fueled Scramjet[J]. Journal of Propulsion Technology, 2013, 34(12): 1708-1712.

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