EXPERIMENT ON THE PERFORMANCES OF A MODEL INFRARED SUPPRESSOR WITH SMALL TABS
An experiment was conducted in this paper to study the infrared suppression effects of the small tabs which were fixed on the exit of a model infrared suppressor for helicopter. The pressure at the main nozzle inlet was atmospheric pressure. The main flow velocity was subsonic with a Mach number 0.2. The temperature of the main flow was about 610℃. The downwash flow velocity at 480mm downstream of the blower was about 11 m/s. The results showed that by comparison with the baseline structure without tabs, the highest and the averaged exhaust temperatures at the exit decreased by 3.3％ and 1.5％,respectively, and the total pressure loss increased by 0.4％,when four tabs were fixed. By increasing the size of the tabs the infrared suppression effect was improved but the total pressure loss was increased.
ZHU Ying HUANG Yong
School of Jet Propulsion, National Key Laboratory on Aero-Engines,Beijing University of Aeronautics and Astronautics, 100083
国际会议
昆明
英文
118-121
2006-09-18（万方平台首次上网日期，不代表论文的发表时间）