本文選題：軸流壓氣機(jī) + 氣動穩(wěn)定性　； 參考：《南京航空航天大學(xué)》2015年碩士論文

【摘要】：壓氣機(jī)流動失穩(wěn)現(xiàn)象的發(fā)生極大地限制了燃?xì)鉁u輪發(fā)動機(jī)的工作范圍,因此壓氣機(jī)的設(shè)計(jì)必須預(yù)留足夠的穩(wěn)定裕度以確保發(fā)動機(jī)工作時(shí)不發(fā)生失穩(wěn)。然而,進(jìn)氣畸變的存在會使壓氣機(jī)更容易發(fā)生流動失穩(wěn),對于多軸發(fā)動機(jī),如果上游壓氣機(jī)出現(xiàn)了旋轉(zhuǎn)失速現(xiàn)象,那么下游壓氣機(jī)將工作在周向旋轉(zhuǎn)的低壓區(qū)的影響下,即旋轉(zhuǎn)進(jìn)氣畸變。本文將探究旋轉(zhuǎn)進(jìn)氣畸變對壓氣機(jī)穩(wěn)定邊界的影響規(guī)律,分析其影響機(jī)理。在M-G模型基礎(chǔ)上發(fā)展的二維不可壓縮模型可計(jì)算均勻、非均勻進(jìn)氣條件下軸流壓縮系統(tǒng)的動態(tài)失速特性,本文在模型中加入了方波形式的旋轉(zhuǎn)進(jìn)氣畸變流場,定量分析了不同畸變轉(zhuǎn)速、畸變幅值和畸變角對壓縮系統(tǒng)穩(wěn)定性的影響。設(shè)計(jì)了一臺可變畸變角的旋轉(zhuǎn)進(jìn)氣畸變發(fā)生裝置,在二級低速軸流壓氣機(jī)上開展了90°、30°、15°畸變角的各個(gè)畸變轉(zhuǎn)速對壓氣機(jī)氣動穩(wěn)定性影響的實(shí)驗(yàn)。實(shí)驗(yàn)結(jié)果表明:旋轉(zhuǎn)進(jìn)氣畸變的轉(zhuǎn)速對壓氣機(jī)氣動穩(wěn)定性存在很大的影響,當(dāng)畸變以某轉(zhuǎn)速旋轉(zhuǎn)時(shí)壓氣機(jī)的穩(wěn)定裕度損失最大,稱此轉(zhuǎn)速為“危險(xiǎn)轉(zhuǎn)速”,并且此轉(zhuǎn)速接近于完全發(fā)展的失速團(tuán)傳播速度。旋轉(zhuǎn)進(jìn)氣畸變角的改變不會使“危險(xiǎn)轉(zhuǎn)速”產(chǎn)生變化,只是“危險(xiǎn)轉(zhuǎn)速”附近的邊界點(diǎn)流量系數(shù)隨著畸變角的減小而減小,而對其余轉(zhuǎn)速下的邊界點(diǎn)影響不大。結(jié)合模型計(jì)算和實(shí)驗(yàn)研究的結(jié)果,提出了旋轉(zhuǎn)進(jìn)氣畸變對壓氣機(jī)穩(wěn)定性影響機(jī)理的模型,該模型較好地解釋了畸變以“危險(xiǎn)轉(zhuǎn)速”旋轉(zhuǎn)時(shí)比其他轉(zhuǎn)速下對壓氣機(jī)穩(wěn)定性影響更大的原因。
[Abstract]:The phenomenon of compressor flow instability greatly limits the working range of gas turbine engine, so the compressor design must reserve enough stability margin to ensure that the engine does not lose stability.However, the presence of inlet distortion will make the compressor more prone to flow instability. For a multi-axle engine, if the upstream compressor has a rotating stall, the downstream compressor will work under the influence of the circumferential rotating low pressure region.That is, the rotation of the air intake distortion.In this paper, the influence of rotating inlet distortion on compressor stability boundary is studied and its influence mechanism is analyzed.The two-dimensional incompressible model developed on the basis of M-G model can calculate the dynamic stall characteristics of the axial flow compression system under uniform and inhomogeneous inlet conditions. In this paper, the distorted flow field in the form of square wave is added to the model.The effects of different distortion speed, distortion amplitude and distortion angle on the stability of compression system are quantitatively analyzed.A rotating air intake distortion generator with variable distortion angle was designed. Experiments were carried out on a two-stage low speed axial compressor with different distortion speeds of 90 擄to 30 擄and 15 擄distortion angle on the aerodynamic stability of the compressor.The experimental results show that the rotational speed of rotating inlet distortion has a great influence on the compressor aerodynamic stability. When the distortion occurs at a certain rotational speed, the compressor has the greatest loss of stability margin, which is called "dangerous speed".The speed is close to that of the fully developed stall group.The change of the distortion angle of the air inlet will not change the "dangerous speed", but the flow coefficient of the boundary point near the "dangerous speed" decreases with the decrease of the distortion angle, but has little effect on the boundary points at the other rotational speeds.Based on the results of model calculation and experimental study, a model of the influence mechanism of rotating inlet distortion on compressor stability is proposed.The model can explain why the distortion has more influence on the compressor stability when the distortion rotates at "dangerous speed" than at other rotational speeds.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：V235.1

【相似文獻(xiàn)】

相關(guān)期刊論文 前10條

1 張環(huán),胡駿,李傳鵬,王英鋒;軸向間距對壓氣機(jī)氣動穩(wěn)定性的影響[J];航空動力學(xué)報(bào);2005年01期

2 陳英;葉巍;周志文;王彥青;;一種用于提高發(fā)動機(jī)氣動穩(wěn)定性的控制策略[J];燃?xì)鉁u輪試驗(yàn)與研究;2012年03期

3 王碧s，

本文編號：1770076