TY - GEN
T1 - The effect of swirl intensity on spray characteristics in single element lean direct injection combustor
AU - Li, Le
AU - Suo, Jianqin
AU - Xu, Dinghuan
AU - Liang, Hongxia
AU - Zheng, Longxi
N1 - Publisher Copyright:
© 2019 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2019
Y1 - 2019
N2 - A single element lean direct injection (LDI) module with convergent outlet is proposed to improve the spray distribution and combustion performance for LDI combustor. The experiments of fuel spray characteristics were conducted under different swirl intensity (S32, S38, S45) and air flowrate (0g/s, 3.3g/s, 5.2g/s, 6.8g/s). The experimental results show that the nozzle flow number of the swirler S38 is larger than that of the swirler S32 and S45, and the nozzle flow number decrease slightly when air is added. With the increase of swirl intensity, the spray cone angle increased significantly. The drops size of spray is decreased with the increase of swirl intensity and air flowrate, and the effect of air flowrate on fuel atomization quality is much greater than swirl intensity.
AB - A single element lean direct injection (LDI) module with convergent outlet is proposed to improve the spray distribution and combustion performance for LDI combustor. The experiments of fuel spray characteristics were conducted under different swirl intensity (S32, S38, S45) and air flowrate (0g/s, 3.3g/s, 5.2g/s, 6.8g/s). The experimental results show that the nozzle flow number of the swirler S38 is larger than that of the swirler S32 and S45, and the nozzle flow number decrease slightly when air is added. With the increase of swirl intensity, the spray cone angle increased significantly. The drops size of spray is decreased with the increase of swirl intensity and air flowrate, and the effect of air flowrate on fuel atomization quality is much greater than swirl intensity.
UR - http://www.scopus.com/inward/record.url?scp=85095965089&partnerID=8YFLogxK
U2 - 10.2514/6.2019-4372
DO - 10.2514/6.2019-4372
M3 - 会议稿件
AN - SCOPUS:85095965089
SN - 9781624105906
T3 - AIAA Propulsion and Energy Forum and Exposition, 2019
BT - AIAA Propulsion and Energy Forum and Exposition, 2019
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Propulsion and Energy Forum and Exposition, 2019
Y2 - 19 August 2019 through 22 August 2019
ER -