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利用反向热流法实验研究了弦向3排射流喷口,且中央喷口正对前缘驻点结构下射流冲击热气防冰系统前缘内表面的局部传热特性。重点研究了喷孔射流出口雷诺数Rej、笛形管相对于前缘的距离与孔径比Zn/d、射流冲击驻点区弦向弧长与孔径比r/d对冲击前缘靶面的局部传热性能分布的影响。实验中Rej范围为2.5×104~1×105,Zn/d范围为1.736~27.5,r/d范围为13.21~61.5。结果表明,局部传热性能分布曲线为从驻点开始向两侧衰减的钟形曲线,包括稳定段、下降段和结束段3部分,其中稳定段只受参数r/d的影响,而参数Rej、Zn/d和r/d均能够明显影响下降段的下降速率,参数r/d则几乎不会改变下降段的总下降幅度。总结了此类喷口结构下射流冲击前缘换热性能衰减分布曲线的通用实验关联式,以指导防冰系统的设计和热性能的评估。
The reverse heat flow method was used to study the local heat transfer characteristics of the chordwise 3-row jet nozzle with the central nozzle facing the inner surface of the front edge of the blast-impact hot gas anti-icing system under the stagnation point structure of the leading edge. Focusing on the Reynolds number Rej, the distance between the flute tube and the leading edge and the ratio of Zn / d, the arc-length and the aperture ratio r / d of the impinging jets in the impinging jet impingement on the part of the impact front target Effect of Heat Transfer Performance Distribution. In the experiment, Rej ranged from 2.5 × 104 to 1 × 105, Zn / d ranged from 1.736 to 27.5, and r / d ranged from 13.21 to 61.5. The results show that the distribution curve of local heat transfer is a bell-shaped curve that decays from stagnation point to both sides, including the stable section, the descending section and the ending section. The stable section is only affected by the parameter r / d, while the parameter Rej , Zn / d and r / d both can significantly affect the descending rate of descending stage, and the parameter r / d will hardly change the descending stage of descending stage. The general experimental correlation for the decay curve of heat transfer performance of jet impingement front at such nozzle structures is summarized to guide the design of ice protection system and the evaluation of thermal performance.