TY - JOUR
T1 - Effects of Panel Vibration on Performance of Combustor for Scramjet
AU - Ye, Kun
AU - Ye, Zheng Yin
AU - Qu, Zhan
N1 - Publisher Copyright:
© 2017, Editorial Department of Journal of Propulsion Technology. All right reserved.
PY - 2017/2/1
Y1 - 2017/2/1
N2 - In order to investigate the effects of panel vibration on the performance of combustor for scramjet, based on the improved JNAL model, through applying forced vibration respectively on upstream panel and downstream panel, the effects of vibration amplitude, frequency and wavelength on the combustion efficiency and total pressure loss ratio are studied. For the model in this paper, the calculation results show that: (1)The panel vibration has a significant influence on the performance of combustor, improving the combustion efficiency while the total pressure loss ratio increases.(2)For the panel vibration of upstream and downstream, the effects of amplitude and wavelength on the combustion performance are similar, combustion efficiency and total pressure loss ratio increase with the increase of the amplitude, the amplitude increment is about 40.52% and 55.74%, respectively. They increase with the decrease of the wavelength, and the combustion performance is sensitive for the relative small wavelength.(3)For the upstream panel vibration, with the increase of frequency, the combustion efficiency and total pressure loss ratio slightly decrease at first, and then increase monotonously. But for the downstream panel vibration, with the increase of frequency, the combustion efficiency and total pressure loss ratio decrease at first, and then increase, when the vibration frequency is close to the dominant frequency of pressure pulsation in the downstream flow field, the effects of panel vibration on the performance of the combustion chamber reach maximum, the increase amplitude of combustion efficiency and total pressure loss ratio is about 75.42% and 65.68%, respectively.
AB - In order to investigate the effects of panel vibration on the performance of combustor for scramjet, based on the improved JNAL model, through applying forced vibration respectively on upstream panel and downstream panel, the effects of vibration amplitude, frequency and wavelength on the combustion efficiency and total pressure loss ratio are studied. For the model in this paper, the calculation results show that: (1)The panel vibration has a significant influence on the performance of combustor, improving the combustion efficiency while the total pressure loss ratio increases.(2)For the panel vibration of upstream and downstream, the effects of amplitude and wavelength on the combustion performance are similar, combustion efficiency and total pressure loss ratio increase with the increase of the amplitude, the amplitude increment is about 40.52% and 55.74%, respectively. They increase with the decrease of the wavelength, and the combustion performance is sensitive for the relative small wavelength.(3)For the upstream panel vibration, with the increase of frequency, the combustion efficiency and total pressure loss ratio slightly decrease at first, and then increase monotonously. But for the downstream panel vibration, with the increase of frequency, the combustion efficiency and total pressure loss ratio decrease at first, and then increase, when the vibration frequency is close to the dominant frequency of pressure pulsation in the downstream flow field, the effects of panel vibration on the performance of the combustion chamber reach maximum, the increase amplitude of combustion efficiency and total pressure loss ratio is about 75.42% and 65.68%, respectively.
KW - Combustion efficiency
KW - Panel vibration
KW - Scramjet
KW - Supersonic combustion
KW - Total pressure loss ratio
UR - http://www.scopus.com/inward/record.url?scp=85019367438&partnerID=8YFLogxK
U2 - 10.13675/j.cnki.tjjs.2017.02.018
DO - 10.13675/j.cnki.tjjs.2017.02.018
M3 - 文章
AN - SCOPUS:85019367438
SN - 1001-4055
VL - 38
SP - 386
EP - 398
JO - Tuijin Jishu/Journal of Propulsion Technology
JF - Tuijin Jishu/Journal of Propulsion Technology
IS - 2
ER -