TY - GEN
T1 - Experimental study on effusion cooling with tangential air inlet
AU - Yu, Han
AU - Suo, Jianqin
AU - Liang, Hongxia
AU - Li, Ming
AU - Zheng, Longxi
N1 - Publisher Copyright:
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2016
Y1 - 2016
N2 - Tangential effusion cooling (TEC) scheme is proposed to satisfy the cooling requirement for advanced combustor. The experiments were conducted in a single flame tube combustor under reaction conditions, the inlet temperature, inlet pressure and fuel air ratio (FAR) is 489-800K, 0.49-2.1MPa, 0.0106-0.037 respectively. The liner wall temperature distribution along axial and circumferential direction was obtained, which indicate that FAR is the vital influence factor on wall temperature, the increase of burner inlet temperature lead to slightly increase of wall temperature. The highest wall temperature rise is 116K which achieved at 0.037 FAR. The calculation method for TEC is verified in this paper, the results show that it has an excellent accuracy for predicting the effusion cooling (TEC) combustor wall temperature.
AB - Tangential effusion cooling (TEC) scheme is proposed to satisfy the cooling requirement for advanced combustor. The experiments were conducted in a single flame tube combustor under reaction conditions, the inlet temperature, inlet pressure and fuel air ratio (FAR) is 489-800K, 0.49-2.1MPa, 0.0106-0.037 respectively. The liner wall temperature distribution along axial and circumferential direction was obtained, which indicate that FAR is the vital influence factor on wall temperature, the increase of burner inlet temperature lead to slightly increase of wall temperature. The highest wall temperature rise is 116K which achieved at 0.037 FAR. The calculation method for TEC is verified in this paper, the results show that it has an excellent accuracy for predicting the effusion cooling (TEC) combustor wall temperature.
UR - http://www.scopus.com/inward/record.url?scp=85086949642&partnerID=8YFLogxK
U2 - 10.2514/6.2016-5053
DO - 10.2514/6.2016-5053
M3 - 会议稿件
AN - SCOPUS:85086949642
SN - 9781624104060
T3 - 52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016
BT - 52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016
Y2 - 25 July 2016 through 27 July 2016
ER -