本文選題：超聲速射流 + 嘯聲��； 參考：《推進技術(shù)》2016年12期

【摘要】：為研究連續(xù)超聲速射流對撞誘導(dǎo)激波聚焦的機理,在噴口間距為70mm,不同入射壓力的條件下進行了自由射流對撞、二維凹面腔內(nèi)的射流對撞及三維凹面腔內(nèi)的射流對撞誘導(dǎo)激波聚焦實驗。通過對比自由射流對撞輻射嘯聲頻譜和凹面腔內(nèi)射流對撞中凹面腔底部的動態(tài)壓力頻譜,結(jié)合紋影照片對連續(xù)超聲速射流對撞誘導(dǎo)激波聚焦的機理進行了研究。結(jié)果表明,沿射流對撞面兩側(cè)的橢球形激波陣面的高頻拉鋸式振蕩是連續(xù)射流對撞誘導(dǎo)激波聚焦的本質(zhì)。當兩側(cè)的波陣面同時到達凹面腔底部發(fā)生碰撞時,激波聚焦得以完成;在一定的入射壓力范圍內(nèi),由于射流對撞面不穩(wěn)定,兩側(cè)橢球形激波陣面不能同時到達兩噴口中間的對稱面,因此在自由射流對撞的輻射噪聲頻譜上共存兩種模式的嘯聲。在凹面腔內(nèi)的射流對撞中,凹面腔底部的壓力脈動頻譜上也同時存在兩個頻率十分接近的峰值;隨著入射壓力的進一步提高,兩側(cè)的橢球形激波陣面經(jīng)過一段時間的協(xié)調(diào)同步后同時到達噴口中間的對稱面,輻射噪聲和壓力脈動頻譜中雙頻率值共存的現(xiàn)象消失,并統(tǒng)一為單一值。
[Abstract]:In order to study the mechanism of shock focusing induced by continuous supersonic jet collision, the free jet collision was carried out under the conditions of 70 mm nozzle spacing and different incident pressure. Two dimensional concave cavity jet collision and three dimensional concave cavity jet collision induced shock wave focusing experiment. The mechanism of shock focusing induced by continuous supersonic jet collision was studied by comparing the whistling sound spectrum of free jet collision and the dynamic pressure spectrum at the bottom of concave cavity. The results show that the high frequency saw oscillations along the ellipsoidal shock front along the two sides of the jet collision surface are the essence of the shock focusing induced by the continuous jet collision. When the wave front on both sides reaches the bottom of the concave cavity at the same time, the shock wave focus is completed, and in a certain range of incident pressure, the jet collision surface is unstable. The ellipsoid shock front on both sides cannot reach the symmetric surface between the two vents at the same time, so the whistling sound of the two modes can coexist on the radiation noise spectrum of the free jet collision. In the jet collision of concave cavity, there are also two peaks in the spectrum of pressure pulsation at the bottom of concave cavity, which are very close to each other. After a period of coordination and synchronization, the ellipsoidal shock front on both sides reaches the symmetrical plane in the middle of the nozzle simultaneously. The phenomenon of the coexistence of dual frequency values in the spectrum of radiation noise and pressure pulsation disappears and is unified into a single value.
【作者單位】： 空軍工程大學(xué)航空航天工程學(xué)院;陸航研究所;中國人民解放軍94710部隊;
【基金】：國家自然科學(xué)基金重大培育項目(91541109);國家自然科學(xué)基金(51406234) 陜西省自然科學(xué)基金(2015JQ5124)
【分類號】：V231

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本文編號：1989636