摘要
为研究航空发动机燃烧室机匣发生烧穿时射流火焰的温度、热流密度分布,建立机匣烧穿试验系统,采用单一变量法,研究了喷嘴孔径、油气质量比、外侧空气流速、燃烧室内部压力对射流火焰在轴向上的温度、热流密度分布的影响。结果表明:射流火焰在轴向上的热流密度衰减迅速,在127~254 mm内,热流密度衰减最多,可达81%;喷嘴孔径对于火焰形态、温度、热流密度影响最大;燃烧室内部压力对火焰温度影响可达675℃/MPa;外侧空气流速主要影响火焰轴向254~508 mm区间温度分布;油气质量比对火焰轴向温度影响达18.6%。航空发动机设计时应当考虑在燃烧室机匣薄弱点法线方向外侧254 mm范围内设置挡火板,以防止可能出现的机匣烧穿带来的危害。
[Objective]With the development of airworthiness certification for domestic commercial aeroengines,research in domestic civil aviation has continued to deepen.As one of the core components of the aeroengine,the combustor case has been subjected to long-term testing using high-temperature and high-pressure flames.The safety of the aircraft would be compromised if the combustor case is burned-through.The Federal Aviation Administration(FAA)has included burn-through safety as one of the criteria for engine airworthiness certification in its regulations.From the perspective of simulation and experimentation,foreign scholars have conducted a series of studies on the combustor case burn-through phenomenon.However,few relevant studies have been conducted in China.[Methods]The development of a set of jet flame test bench systems is presented in this paper.The system is designed to simulate the emitted flame from the combustion hole after the combustor case is burned.The test bench system can meet the following specifications:First,the temperature of the generated jet flame at the nozzle should not be below 1648℃.Second,the internal pressure of the burner must be 0.74 MPa based on the standard operating conditions.The effects of the nozzle aperture,oil-gas mass ratio,outer air velocity,and internal pressure on the axial temperature and heat flux distribution of the jet fire are studied using the system through the single variable method.[Results]Experimental results are as follows:(1)The jet flame takes on a concentrated form,revealing a rapid decrease in the temperature and heat flow in the axial direction.(2)The oil-gas mass ratio notably affects flame temperature and heat flux,demonstrating a positive correlation.Specifically,at distances of 127 mm,the increases in temperature of 18.6%and heat flux of 13.0%are observed when the oil-gas mass ratio increases from 0.035 to 0.050.(3)The flame temperature and heat flux are also affected by the outside air flow rate.The temperature and heat flux have a considerable impact
作者
徐翔
陈龙
李松阳
万羽翼
XU Xiang;CHEN Long;LI Songyang;WAN Yuyi(Certification Center,The Second Research Institute of CAAC,Chengdu 610207,China;Department of Advanced Technology,AECC Commercial Aircraft Engine Co.,Ltd.,Shanghai 200241,China;Key Laboratory of Aviation Fuel and Chemical Airworthiness and Green Development,CAAC,Chengdu 610207,China;State Key Laboratory of Fire Science,University of Science and Technology of China,Hefei 230026,China)
出处
《清华大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2024年第6期984-991,共8页
Journal of Tsinghua University(Science and Technology)
基金
国家科技重大专项(J2019-Ⅷ-0010-0171)。
关键词
机匣烧穿
射流火
温度
热流密度
火焰
combustor case burn-through
jet fire
temperature
heat flux density
flame
