本文關(guān)鍵詞：軸流壓氣機(jī)葉尖間隙影響失速的機(jī)理及周向單槽機(jī)匣處理擴(kuò)穩(wěn)研究　出處：《西北工業(yè)大學(xué)》2015年博士論文　論文類型：學(xué)位論文

  更多相關(guān)文章： 軸流壓氣機(jī) 失速 葉尖間隙 動態(tài)壓力測量 周向槽

【摘要】：結(jié)合本課題組國家自然科學(xué)基金項(xiàng)目的開展,以西北工業(yè)大學(xué)孤立轉(zhuǎn)子為研究對象,進(jìn)行亞聲速壓氣機(jī)失速實(shí)驗(yàn)研究。在此基礎(chǔ)上利用數(shù)值模擬方法,對壓氣機(jī)失速機(jī)理、葉尖間隙變化對失速的影響以及周向單槽耦機(jī)匣處理擴(kuò)穩(wěn)研究。就上述問題,本文還對跨聲速壓氣機(jī)rotor37進(jìn)行研究,探討亞聲速和跨聲速壓氣機(jī)在上述問題的異同。對亞聲速壓氣機(jī)進(jìn)行了失速實(shí)驗(yàn)研究,亞聲速壓氣機(jī)實(shí)驗(yàn)測量結(jié)果表明,葉尖流場具有明顯的非定常性。對葉片通過頻率進(jìn)行研究,發(fā)現(xiàn)效率峰值工況下葉片通過頻率壓力脈動幅度最大;而在近失速工況下,通過頻率壓力脈動幅值急劇下降;失速后,通過頻率壓力脈動幅度再次被增大。這一特點(diǎn)對于失速監(jiān)測具有重要意義,可以設(shè)置葉片通過頻率壓力脈動幅度閾值。如果葉片通過頻率壓力脈動幅度突然小于閾值,意味著壓氣機(jī)進(jìn)入失速邊界。監(jiān)測通過頻率壓力脈動幅值,可以有效地監(jiān)控壓氣機(jī)工作狀況,為失速的主動控制提前預(yù)警,具有一定的工程應(yīng)用價值。通過非定常數(shù)值仿真計(jì)算,發(fā)現(xiàn)所研究亞聲速壓氣機(jī),在由近失速到失速過程中,存在明顯的前溢后返現(xiàn)象。結(jié)合流場分析,認(rèn)為“前溢后返”是葉尖間隙泄漏流與來流軸向動量相互作用的結(jié)果。為了便于定量研究葉尖間隙泄漏流與來流軸向動量的相互作用,提出用單位面積的葉尖間隙泄漏流動量與單位面積的來流動量比(Ba)作為葉尖間隙泄漏流與來流相交面的表征。發(fā)現(xiàn)所研究的壓氣機(jī)當(dāng)Ba小于0.5時,壓氣機(jī)處于穩(wěn)定工作區(qū)域;當(dāng)Ba大于0.5時,壓氣機(jī)進(jìn)入非穩(wěn)定工況。本文還對跨聲速轉(zhuǎn)子rotor 37進(jìn)行數(shù)值仿真,通過對流場分析,認(rèn)為泄漏流與主流軸向動量的相互作用是引發(fā)跨聲速壓氣機(jī)失速的根本原因。研究跨聲速壓氣機(jī)葉尖間隙泄漏流與來流軸向動量比對壓氣機(jī)工作的影響,發(fā)現(xiàn)近失速工況下Ba值小于0.5。葉尖間隙變化可以誘導(dǎo)不同的失速機(jī)理,對壓氣機(jī)穩(wěn)定工作范圍有重要影響。無論是亞聲速壓氣機(jī)還是跨聲速壓氣機(jī),隨著葉尖間隙的增大,葉尖間隙泄漏流與來流的交界面不斷前移,當(dāng)葉尖間隙足夠大時,在近失速工況下就表現(xiàn)出從前緣的溢出。葉尖間隙變化對Ba有影響。隨著葉尖間隙的減小,Ba增加的趨勢變緩。壓氣機(jī)穩(wěn)定運(yùn)行下,其Ba值不超過0.5;在壓氣機(jī)失速機(jī)理不改變的前提下,存在Ba值越小壓氣機(jī)穩(wěn)定性越好的趨勢。但是葉尖間隙減小到一定程度,失速機(jī)理會發(fā)生變化,致使Ba尚不能準(zhǔn)確描述最佳間隙。周向單槽降低了局部位置葉片壓力面、吸力面之間的壓差,但在其下游方向,葉片壓力面、吸力面之間的壓差又一次增大,這種壓差變化的現(xiàn)象對周向單槽的擴(kuò)穩(wěn)效果產(chǎn)生影響。葉尖間隙與周向單槽耦合研究發(fā)現(xiàn),在小間隙下,無論周向單槽位于葉片前緣還是中間,穩(wěn)定裕度都得到大幅改善,可以實(shí)現(xiàn)效率、壓比不降低的同時,大幅提高壓氣機(jī)穩(wěn)定裕度的目標(biāo);而在大間隙下,壓氣機(jī)的效率、壓比、穩(wěn)定裕度均有惡化。從機(jī)理角度,這是由于小葉尖間隙可抑制周向單槽機(jī)匣處理后葉片表面壓差的變化現(xiàn)象。在上述研究的基礎(chǔ)上,進(jìn)一步探索葉尖小間隙下單槽槽深對壓氣機(jī)性能的影響,發(fā)現(xiàn)槽深過大會引起槽內(nèi)渦流產(chǎn)生多余的能量損失。有效控制槽深既起到徑向抽吸的作用,又要盡量避免多余的能量損失,是提高機(jī)匣處理效率的重要途徑。
[Abstract]:According to the research group of National Natural Science Fund project carried out by Northwestern Polytechnical University rotor as the research object, for subsonic compressor stall experiment. Based on the numerical simulation method of compressor stall mechanism, variation of tip clearance effects on the stall and single circumferential groove casing treatment is the steady expansion research. In this paper, also studied the transonic compressor rotor37, to discuss the similarities and differences of the subsonic and transonic compressor in the above problems. The subsonic compressor was studied subsonic compressor stall, the experimental measurement results show that the tip flow field is unsteady obviously. The blade was studied by the blade frequency, peak efficiency under the condition of the frequency of pressure pulsation amplitude; while in the near stall condition, the frequency of the pressure fluctuation amplitude decreased sharply after the stall, the frequency; The rate of amplitude of pressure fluctuation was again increased. This feature is of great significance for the stall monitoring, you can set the blade passing frequency pressure fluctuation amplitude threshold. If the blade passing frequency sudden pressure pulsation amplitude is less than the threshold, means that the compressor enters the stall boundary. Through monitoring the frequency of pressure pulsation amplitude, can effectively monitor the working condition of the compressor, the initiative in advance stall warning control, has a certain value in engineering. By unsteady numerical simulation, it was found that the subsonic compressor, to stall process from near stall, there was before the spill phenomenon. After combining with flow field analysis, that "before the spill is to return" flow and axial momentum interaction leakage Ye Jian gap results. In order to facilitate the interaction of quantitative research Ye Jian leakage flow and flow axial momentum, the unit area of Ye Jian Flow and unit area leakage gap to flow momentum ratio (Ba) as the tip leakage flow and flow intersection surface characterization. The study found that the compressor when Ba is less than 0.5, the compressor in a stable working area; when Ba is greater than 0.5, the compressor enters the unsteady condition. This paper also on transonic rotor rotor 37 numerical simulation based on flow field analysis, that leakage interaction and main flow of axial momentum is the fundamental cause of transonic compressor stall. The influence of transonic compressor tip clearance leakage flow and flow ratio on the axial momentum compressor work, found near stall condition Ba value is less than 0.5. of tip clearance changes can stall different mechanisms of induction, has an important influence on the stable working range of the compressor. Both subsonic compressor or transonic compressor, with the increase of the tip clearance, the tip clearance leakage Flow and flow interface continuously forward, when the tip clearance is large enough, at near stall condition showed from the leading edge of the overflow. The tip clearance changes affect Ba. With the decrease of the tip clearance, Ba increased slowly. The compressor stable operation, the Ba value of not more than 0.5; in do not change the premise of the stall mechanism, there is Ba smaller compressor stability good trend. But the tip clearance is reduced to a certain extent, stall mechanism will change, resulting in Ba cannot accurately describe the optimum clearance. Single circumferential groove reduces the local position of the pressure surface of the blade suction surface, the pressure difference between, but in in the downstream direction, the pressure surface of the blade suction surface, the pressure difference between again increased, this will affect the change of pressure difference phenomenon of single circumferential groove stability enhancement effect. The tip clearance and circumferential groove coupling study found that in small gaps, regardless of the week To the single slot in the leading edge of the blade or in the middle, the stability margin has been greatly improved, can realize the efficiency, pressure ratio does not decrease at the same time, a substantial increase in the compressor stability margin target; and in the large gap, compressor pressure ratio, efficiency, stability margin has deteriorated. From the theoretical point of view, this is because the phenomenon of change of small tip clearance can inhibit the single circumferential groove casing treatment after the blade surface pressure difference. On the basis of the above research, to further explore the tip gap single groove deep influence on the compressor performance, found that the groove depth will cause the tank eddy current loss of energy excess. Effective control of groove depth is the radial suction effect, but also to avoid unnecessary loss of energy, is an important way to improve the efficiency of casing treatment.

【學(xué)位授予單位】：西北工業(yè)大學(xué)
【學(xué)位級別】：博士
【學(xué)位授予年份】：2015
【分類號】：TH453

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