本文選題：S彎進(jìn)氣道 + 二次流��； 參考：《南京航空航天大學(xué)》2016年碩士論文

【摘要】：基于飛行器對(duì)隱身性能及重量的要求,雙S彎進(jìn)氣道往往設(shè)計(jì)成偏距較大,長(zhǎng)度較短的形狀。然而大偏距、短擴(kuò)壓式雙S彎進(jìn)氣道由于彎度較大,產(chǎn)生的二次流強(qiáng)度較強(qiáng),容易引起附面層分離,這將嚴(yán)重影響航空發(fā)動(dòng)機(jī)的穩(wěn)定性。針對(duì)這一問題,本文展開了以下幾個(gè)方面的研究:(1)研究了雙S彎進(jìn)氣道造型特點(diǎn),參考國(guó)內(nèi)外復(fù)雜截面進(jìn)口形狀進(jìn)氣道的設(shè)計(jì)方法,采用半徑過渡的方法實(shí)現(xiàn)了雙S彎進(jìn)氣道三維造型的參數(shù)化設(shè)計(jì)。(2)分析了雙S彎進(jìn)氣道內(nèi)二次流生成機(jī)理以及二次流的發(fā)展,研究了中心線變化規(guī)率、面積變化規(guī)律以及雙S彎進(jìn)氣道第一、二S彎長(zhǎng)度比例對(duì)進(jìn)氣道氣動(dòng)性能的影響。通過數(shù)值模擬分析得出,中心線變化規(guī)律、面積變化規(guī)律以及雙S彎進(jìn)氣道第一、二S彎長(zhǎng)度比例都是通過影響進(jìn)氣道壁面沿程壓力梯度分布來影響進(jìn)氣道氣動(dòng)性能;中心線變化規(guī)律選取緩急相當(dāng)與緩急相當(dāng)配合,面積變化規(guī)律選取前急后緩與前緩后急的配合,第一、二S彎比例選取0.77,雙S彎進(jìn)氣道的氣動(dòng)性能最佳。(3)在傳統(tǒng)雙S彎進(jìn)氣道設(shè)計(jì)的基礎(chǔ)上,本文著重研究了雙S彎進(jìn)氣道第一、二S彎進(jìn)氣道的交界面形狀對(duì)進(jìn)氣道內(nèi)二次流的影響,并提出通過優(yōu)化設(shè)計(jì)交界面形狀來削弱雙S彎進(jìn)氣道內(nèi)二次流強(qiáng)度,抑制附面層分離的設(shè)計(jì)方法。通過分析得出,在保證雙S彎進(jìn)氣道交界面面積相同條件下,交界面高度選取進(jìn)氣道進(jìn)口高度,形狀選用帶倒圓矩形形狀能夠有效削弱交界面處二次流強(qiáng)度,抑制附面層分離。(4)分析了飛行器飛行Ma、攻角、側(cè)滑角以及發(fā)動(dòng)機(jī)流量變化對(duì)雙S彎進(jìn)氣道氣動(dòng)性能的影響。通過數(shù)值仿真分析得出,飛行器飛行Ma、攻角、側(cè)滑角通過影響進(jìn)氣道進(jìn)氣品質(zhì)影響進(jìn)氣道性能,發(fā)動(dòng)機(jī)流量變化則是通過影響進(jìn)氣道內(nèi)流動(dòng)速度影響進(jìn)氣道氣動(dòng)性能。(5)研究了脈沖射流射流頻率、射流流量對(duì)進(jìn)氣道附面層分離控制效果的影響,應(yīng)用FFT方法分析了脈沖射流控制機(jī)理,并對(duì)比了脈沖射流與定常射流的控制效果。通過數(shù)值模擬分析得出,在射流頻率與脫落渦頻率相同時(shí),射流控制效果最好。射流流量影響著脈沖射流控制效果,射流流量增加到一定程度時(shí),脈沖射流對(duì)總壓恢復(fù)系數(shù)的提升逐漸減小。
[Abstract]:Based on the requirements of stealth performance and weight of aircraft, the double S curved inlet is usually designed into a shape with large distance and short length. However, due to the large deviation and short diffuser double S-bend inlet, the secondary flow intensity is stronger and the boundary layer is easy to be separated, which will seriously affect the stability of the aero-engine. In order to solve this problem, the following aspects are studied in this paper: (1) the modeling characteristics of double S curved inlet are studied, and the design method of inlet with complex cross section at home and abroad is referred to. The parametric design of three dimensional modeling of double S curved inlet is realized by using the method of radius transition. (2) the mechanism of secondary flow generation and the development of secondary flow in double S curved inlet are analyzed, and the variation gauge rate of center line is studied. The effect of area variation and the ratio of the first and second S-bending length on the aerodynamic performance of the inlet. Through numerical simulation analysis, it is concluded that the variation law of center line, the law of area change and the ratio of the first and second S-bending length of the double S-bend inlet affect the aerodynamic performance of the inlet by influencing the pressure gradient distribution along the inlet wall. The law of change of the center line selects the matching between the priority and the priority, and the law of area change selects the cooperation between the front and the back and the front and the back. First, When the ratio of two S-bending is 0.77, the aerodynamic performance of double-S-bend inlet is the best. (3) based on the traditional design of double-S-bend inlet, this paper focuses on the study of the first double-S-bend inlet. The influence of the interface shape of the two-S-bend inlet on the secondary flow in the inlet is discussed. The design method of reducing the intensity of the secondary flow and restraining the separation of the boundary layer by optimizing the shape of the interface is put forward. Through analysis, it is concluded that under the condition that the interface area of double S curved inlet is the same, the inlet height is chosen as the interface height and the rectangular shape with inverted circle can effectively weaken the secondary flow intensity at the interface. Suppression of boundary layer separation. (4) the effects of flight angle, attack angle, side slip angle and engine flow rate on the aerodynamic performance of double S curved inlet are analyzed. The numerical simulation results show that the performance of the inlet is affected by the influence of the inlet quality on the flight MaA, attack angle and sideslip angle of the aircraft. The change of engine flow rate affects the aerodynamic performance of the inlet by influencing the flow velocity in the inlet. (5) the influence of the frequency of the pulse jet and the flow rate of the jet on the control effect of the inlet boundary layer separation is studied. The control mechanism of pulse jet is analyzed by FFT method, and the control effect between pulse jet and steady jet is compared. The numerical simulation results show that the jet control effect is the best when the frequency of jet is the same as the frequency of shedding vortex. The jet flow rate affects the control effect of the pulse jet. When the jet flow rate increases to a certain extent, the increase of the total pressure recovery coefficient of the pulse jet decreases gradually.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類號(hào)】：V279

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