新型液氧/空气/异丁烷燃烧加热器研制及流场校测  

A New Liquid-Oxygen/Air/Isobutane Combustion Heater Development and Flow Field Calibration

作　　者：杨样[1] 晏至辉[2] 蒲旭阳[2] 曾令国[1] 马宏祥[2] 

机构地区：[1]中国空气动力研究与发展中心超高速所,四川绵阳621000 [2]中国空气动力研究与发展中心高超中心,四川绵阳621000

出　　处：《推进技术》2017年第12期2830-2835,共6页Journal of Propulsion Technology

摘　　要：为了发展高流场品质、安全可靠运行的高超声速高温风洞技术,研制了一种新型的液氧/空气/异丁烷燃烧加热器。该加热器采用"气液燃烧"模式组织燃烧,考虑了均匀流场设计,并利用空气-异丁烷火炬点火器实现点火。50kg/s量级燃烧加热器点火调试表明,主气流能实现快速点火,在火炬关闭后,继续维持稳定燃烧。利用Φ1m喷管,针对马赫数6,总压6.0MPa及5.2MPa开展流场校测,结果表明燃烧加热器在喷管出口直径80%的中心区域提供均匀气流,在流场均匀区内,马赫数均方根偏差在0.05以内,总温均方根偏差在20K以内,能支撑高超声速气动及推进试验。In order to advance hypersonic high-temperature tunnel techniques which could provide highquality flow field with safety and reliability, a liquid oxygen/air/isobutane combustion heater was developed.Combustion was realized by using ＇gas-oxidand and liquid-fuel combustion＇ mode in this heater. A new air/isobutane igniter torch was used to ignite main airflow. And uniform-flow techniques were elaborately considered in designing the heater. A heater with mass flow rate of about 50 kg/s was developed to perform ignition tests. These test results indicate that the heater can be promptly ignited and maintain stable combustion with low pressure fluctuation after the igniter was shut down. Moreover,flow field calibrations at a Mach number 6 and total pressure 6.0 MPa and 5.2 MPa were conducted with a nozzle of 1 m diameter. The calibration results confirm that the heater could provide uniform flow within 80-percent central area at the nozzle exit. In this zone,the root mean square errors of Mach number and total temperature were within 0.05 and 20 K,respectively. Therefore,the combustion heater can support hypersonic propulsion and aerodynamic experimental research effectively.

关 键 词：异丁烷 高温风洞 燃烧加热器 流场 校测 

分 类 号：V416.8[航空宇航科学与技术—航空宇航推进理论与工程]