Numerical Simulation on A Reacting Flow of A Small Gas Turbine Combustor with Various Spray Conditions
According to the report, about 50％ of helicopters in Korea are manufactured more than 30 years ago. For this reason, the large project on the development of the helicopter is proposed. In this research, relationship between the atomization properties and the characteristics of the reacting flow field in a small gas turbine engine are studied. In general, researches on the development of an injector need a lot of experiments. But those experiments always have the risks of explosion and an emission of toxic gases. Recently computational studies on a chemical reacting flow are widely used as the speed of CPU becomes faster. A spray structure can be expressed in terms of droplet size distribution, break-up length, spray angle, and penetration distance. Among those, the characteristics of the reacting flow field in the gas turbine engine according to various droplet sizes are investigated. Combustion chamber is modeled with 1. 3 million hybrid grid and n-pentane is used for the fuel. With those setting, spray droplet trajectory and temperature distribution are compared. For the cases with three different droplets mean diameter, as the parcel size of the fuel decreases, reaction occurs faster in smaller area. But those small parcels cannot penetrate deeper, fuels is not equally distributed. Although heat transfer and diffusion occur, this inequality increases the pattern factor, important parameter on the combustor performance. Comparisons on the outlet temperature with two different sizes show that to get lower pattern factor, mean diameter of the spray parcels should be at least 80. This means that injection of smaller parcels than the specific value reduces overall performance of the engine. In this work, only the droplet size distribution and spray angle are considered There are lots of variables to affect the injection properties, more researches are planed and we work on some of these.
Gas Turbine Reacting Flow n-Pentane CFD-ACE(Numerical Simulation Subsonic
Kim Seihwan Jo Sungjohyun Jeung Inseuck Park Heeho Na Sangkwon
Interdisciplinary Program in Computational Science and Technology, Seoul National University, Seoul, Department of Mechanical and Aerospace Engineering, Seoul National University, Seoul, Korea Samsung Tech-win Co.,Ltd.,Gyeonggi,Korea Samsung Tech-win Co., Ltd., Gyeonggi, Korea
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
1160-1163
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）