【摘要】：壓氣機旋轉失速等流動失穩(wěn)現象限制了航空發(fā)動機的穩(wěn)定工作范圍。壓氣機失速的形成和葉頂區(qū)域的流動具有密切的關系。作為一種被動流動控制方法,機匣處理能夠有效改善葉頂區(qū)域的流場,提高壓氣機的失速裕度。對于跨音壓氣機,機匣處理和葉頂泄漏渦、激波、邊界層分離之間的相互作用使葉頂流場極為復雜。目前,機匣處理的擴穩(wěn)機理和高效設計方法仍是跨音壓氣機研究領域的熱點問題。本文針對目前跨音壓氣機機匣處理研究方面需要進一步完善的問題開展了研究工作,研究內容包括：1.基于人工神經網絡代理模型對跨音壓氣機周向槽機匣處理進行了多目標優(yōu)化設計,獲得了能夠兼顧失速裕度和峰值效率的周向槽機匣處理方案,并通過對比模型預測結果和數值計算結果驗證了該方法可靠性。進一步通過分析周向槽和葉頂流場之間的相互作用,研究了優(yōu)化后的機匣處理方案對壓氣機性能的影響機理。2.通過正交試驗和極差分析方法對周向槽深、葉頂間隙和葉頂葉型安裝角對跨音壓氣機失速裕度和峰值效率的影響進行了綜合評估,得到了各設計變量的最優(yōu)取值和各設計變量影響壓氣機性能的主次順序,并對比分析了失速裕度最優(yōu)方案和峰值效率最優(yōu)方案對壓氣機葉頂流場和性能的影響。3.通過控制體方法對設計轉速和60%設計轉速下跨音壓氣機周向槽機匣處理的擴穩(wěn)機理進行了定量分析。根據周向槽對控制體所受軸向力沿軸向分布的影響,對不同軸向位置周向槽的擴穩(wěn)作用進行了評估。在此基礎上,篩選出了擴穩(wěn)作用較大的周向槽,并對移除了擴穩(wěn)作用較小的周向槽的機匣處理方案進行了分析,發(fā)現機匣處理的擴穩(wěn)效果并未因移除擴穩(wěn)作用較小的周向槽而發(fā)生顯著改變,驗證了該分析方法的合理性。4.通過非定常數值模擬研究了周向槽單槽軸向位置變化對壓氣機穩(wěn)定工作范圍和葉頂流場非定常性的影響規(guī)律,并分析了周向槽控制葉頂非定常波動的機理。結果表明,位于葉頂中前部的周向槽能夠有效降低葉頂泄漏流和主流的軸向動量比,并減弱葉頂泄漏渦引起的低壓區(qū)和堵塞對葉頂載荷的影響,使葉頂流場的非定常波動得到明顯抑制,擴穩(wěn)效果較好。5.研究了軸向傾斜縫機匣處理軸向位置對跨音壓氣機性能的影響。通過相對權重法得出影響軸向傾斜縫擴穩(wěn)效果的各因素的相對重要性排序為：縫內回流強度、葉頂載荷、葉頂進口軸向速度。研究表明,縫的上游端覆蓋泄漏渦起始位置并且下游端覆蓋激波后吸力面邊界層分離區(qū)域,縫上游端和下游端之間的壓差較大,縫內回流強度較大,能夠有效地緩解葉頂泄漏渦和吸力面邊界層分離引起的堵塞,有利于提高壓氣機的失速裕度。
[Abstract]:The steady operating range of the aeroengine is limited by the flow instability such as the rotary stall of the compressor. The formation of the compressor stall and the flow of the tip region have a close relationship. As a passive flow control method, the case treatment can effectively improve the flow field of the blade top area and improve the stall margin of the compressor. For transonic compressor, casing treatment and blade top leakage vortex, shock wave and boundary layer separation, the flow field of the blade tip is very complicated. At present, the expansion mechanism and high efficiency design method of casing treatment are still hot issues in the research field of transonic compressor. In this paper, the research work is carried out on the problems that need to be further improved in the research of the case processing of the transonic compressor case. The research contents include:1. The multi-objective optimization design of the circumferential groove casing treatment of the transonic compressor is carried out on the basis of the artificial neural network proxy model, and the circumferential groove casing treatment scheme which can balance the stall margin and the peak efficiency is obtained, And the reliability of the method is verified through the comparison model prediction result and the numerical result calculation result. The effect of the optimized casing treatment scheme on the performance of the compressor is also studied by analyzing the interaction between the circumferential groove and the blade top flow field. By means of the orthogonal test and the range analysis method, the influence of the circumferential groove depth, the blade top clearance and the blade tip type installation angle on the stall margin and the peak efficiency of the transonic compressor is comprehensively evaluated, and the optimal value of each design variable and the primary and secondary sequence of each design variable affecting the performance of the compressor are obtained, The effect of the optimal scheme of stall margin and peak efficiency on the flow field and performance of the compressor blade is compared and analyzed. The stability mechanism of the circumferential groove casing treatment of the transonic compressor at the design speed and the design speed of 60% is analyzed quantitatively by the control method. According to the influence of the axial force of the circumferential groove on the axial distribution of the control body, the stability of the circumferential groove in different axial positions is evaluated. On the basis of this, the circumferential groove with the larger stabilizing effect is selected, and the case processing scheme of the circumferential groove with the small expansion stability is analyzed, and it is found that the stabilization effect of the casing treatment is not changed significantly by removing the circumferential groove with smaller expansion stability, The rationality of the analysis method is verified. The effect of the axial position change of the circumferential groove on the steady working range of the compressor and the unsteady performance of the blade top flow field is studied by unsteady numerical simulation, and the mechanism of the unsteady fluctuation of the blade top in the circumferential groove is analyzed. The results show that the circumferential groove located in the front of the blade tip can effectively reduce the axial momentum ratio of the tip leakage flow and the main flow, and reduce the influence of the low pressure area and the blockage on the blade top load caused by the tip leakage vortex, so that the unsteady fluctuation of the blade top flow field is obviously restrained, and the stabilizing effect is good. The effect of axial position on the performance of transonic compressor is studied. The relative importance of the factors which influence the stability of the axial inclined joint is obtained by the relative weight method. The relative importance ranking of the factors is as follows: the internal reflux strength, the blade top load and the blade top inlet axial speed. the research shows that the upstream end of the slit covers the initial position of the leakage vortex and the downstream end covers the boundary layer separation area of the suction surface after the shock wave, Can effectively relieve the blockage caused by the separation of the blade top leakage vortex and the suction surface boundary layer, and is favorable for improving the stall margin of the compressor.
【學位授予單位】：中國科學院研究生院(工程熱物理研究所)
【學位級別】：博士
【學位授予年份】：2015
【分類號】：V233

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