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针对离心式压气机设计中存在流-热-固耦合的问题,文中进行离心式压气机的多学科设计优化研究,基于多学科可行方法,建立离心式压气机的多学科设计优化系统.利用非均匀有理B样条曲线和五次多项式,分别构建径流式叶片型线和扩压器叶片型线,通过特征造型技术,建立离心式压气机参数化模型.采用线性插值方法和网格重生成方法,完成对温度、气压和变形耦合信息传递.在压气机参数化建模和多学科耦合分析的基础上,以总压比、等熵效率和流量为优化目标,对某离心式压气机进行设计优化,实现其综合性能的改善.所建多学科设计优化系统可以推广到其他多场耦合系统的设计. 相似文献
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弯曲叶片是改善压气机近端壁流动的有效技术手段之一。为探索叶片弯曲对高负荷压气机叶栅流场的影响机理,在初始高负荷直列叶栅的基础上,设计了不同正/反弯曲水平的叶栅,并采用数值模拟方法对系列叶栅进行研究。研究发现:叶片正弯曲形成了中间静压低、两端静压高的"C"形静压分布,可有效改善压气机叶栅近端壁流场,显著抑制角区分离,使得端壁区域扩压能力提高;正弯曲可增大叶展中部区域负荷,恶化叶中流场,增大流动分离;叶片反弯曲形成了中间静压高、两端静压低的反"C"形静压分布,可显著恶化近端壁区流场,角区分离区增大,端壁区域扩压能力降低,叶中流场有所改善。 相似文献
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针对某型航空发动机压气机转子叶片尾缘出现的叶尖掉块问题,设计了两种叶片尾缘端削方案,并评估了两种端削方式对压气机级性能的影响,揭示了压气机的失速机理及端削对失速裕度的影响机理。结果表明,端削使压气机的压比裕度降低约0.5%,将压气机的流量裕度提升1%以上,整体上对压气机效率的影响较小;通过对流场的定量分析发现,压气机的失速由转子叶根附近叶片吸力面附面层的分离诱发;转子叶尖尾缘端削改变了整个叶高范围内流量的径向分布,并通过提高转子叶根附近的流量降低了附面层的分离程度,进而提升了压气机的流量裕度;采用叶片尾缘斜切的端削方式对压气机性能的影响更小,可以作为解决叶尖掉块的一种处理方法。 相似文献
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为了研究流固耦合场对叶片强度与振动参数的影响,采用流体动力学和有限元方法,对压气机叶片进行了单向流固耦合分析。通过软件之间的接口,实现压力场数据的传递,并对加载气动力后的计算模型进行强度分析和模态分析,得到压气机大小叶片的应力应变云图以及固有频率和相应的模态振型,计算比较了离心力、气动力对应力和固有频率的影响。计算结果表明,流固耦合对叶片的结构强度和模态振型影响较小。通过频率分析,找出了叶片的共振频率,从而为叶片的优化提供依据。 相似文献
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针对片上电泳分离的特点和需求,分析了片上电泳分离的机理,编制了电泳分离过程的数值计算程序,建立了面向片上电泳分离的电动流体计算平台。在不规则微通道内生成贴体同位网格,并用链导法对控制方程进行转换;采用有限体积法计算微通道内电场分布、缓冲溶液流场分布和电泳分离组分分布;对流场计算,采用动量插值方法解决求解过程中压力和速度失耦问题;采用QUICK格式离散组分传输的对流项,减小了数值耗散引起的“虚假区带增宽”。给出了微通道弯曲结构内电泳分离过程计算结果,验证了计算的有效性和可信性。 相似文献
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为深入理解液力变矩器这种典型旋转叶轮机械内部复杂三维流动现象,获取导轮叶片表面典型部位压力分布规律,提出一种定子叶片表面液体压力场测试方案,通过在导轮叶片压力面埋入微型动态压力传感器,对不同输入转速和速比工况下的导轮叶片表面典型部位压力进行试验测试并进行流场数值模拟对比。结果表明,测试数据与模拟结果高度吻合,较准确地描述了叶片表面压力场的变化趋势,叶片表面压力脉动频率与旋转叶轮转速及叶片数有关。这种压力测试方法不仅能对流场数值模拟进行有效性验证,同时也能为叶轮动态性能设计提供参考依据。 相似文献
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以某型航空发动机压气机转子系统为研究对象,建立了单级叶盘的三维结构及流场模型。通过对滑移网格(sliding mesh,简称SM)方法与运动坐标系(moving reference frame,简称MRF)方法在计算耗时和收敛性方面的比较,证明了运动坐标系方法的准确性和高效性。考虑前一级静叶尾迹的影响,求解压气机内部在不同时刻的流动特性,得到静叶尾迹对动叶流场的非定常干扰情况。经过对压气机叶顶和轮毂、动叶压力面和吸力面非定常气动载荷的分析发现:在动叶流场的前缘形成了较主流区压力和速度较低的不均匀流场,且在动叶前缘叶顶位置受到的气动载荷最为显著;动叶压力面和吸力面气动载荷的分布规律相反,从叶顶至轮毂、前缘至尾缘,压力面非定常气动载荷的大小和波动幅度逐步递减,而吸力面却与其相反,呈现出逐步递增的趋势。该研究为某型航空发动机压气机叶盘转子系统的动力学设计提供了理论依据。 相似文献
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以某型航空发动机压气机转子为研究对象,考虑叶盘间动静干涉的影响,对压气机叶盘转子内部的三维流场进行了模拟。通过静频试验引入叶片失谐量,基于Kriging模型完成了耦合界面载荷数据的传递,分析了压气机转子叶片表面非定常气动载荷的分布规律,并讨论了失谐和气动载荷对压气机转子叶盘系统振动特性的影响。结果表明:压气机叶片受到的气动载荷为非定常脉动压力,主导频率为动静干涉频率f0的倍频;在干涉周期T内,压力面和吸力面气动载荷的变化呈相反趋势,且压力面气动载荷的非定常性明显大于吸力面气动载荷的非定常性;失谐和气动载荷的作用加剧了叶盘系统的振动。研究结果为压气机叶盘转子系统的动力学设计提供了理论依据。 相似文献
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Mahdi Nili-Ahmadabadi Farzad Poursadegh 《Journal of Mechanical Science and Technology》2013,27(11):3319-3330
This paper focuses on performance improvement of a centrifugal compressor. An inverse design method for 3D design approaches is formulated to address this concern. The design procedure encompasses two major steps. First, with the use of ball spine algorithm, which is an inverse design algorithm, on the meridional plane of impeller, the hub and shroud of impeller are computed based on a modified pressure distribution along them. Second, an original and progressive algorithm is developed for design of blade camber line profile on the blade-to-blade planes of impeller based on blade loading improvement. Full 3D analysis of the current and designed compressor is accomplished by using a Reynolds-averaged Navier-Stokes equations solver. A comparison between the analysis results of the current and designed compressor shows that the total-to-total isentropic efficiency and pressure ratio of the designed compressor under the same operating conditions are enhanced by more than 4.5% and 5%, respectively. 相似文献
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《机械工程学报(英文版)》2010,(5)
Inlet recirculation is proved as an effective way for centrifugal compressor surge margin extension,and is successively used in some engineering applications.Unfortunately its working mechanism is still not being well understood,which leads to redesigning of inlet recirculation mostly by experience.Also,most study about inlet recirculation is steady to date.It is necessary to study surge margin extension mechanism about inlet recirculation.To expose the mechanism in detail,steady and unsteady numerical simulations were performed on a centrifugal compressor with and without inlet recirculation.The results showed that,with inlet recirculation,the inlet axial velocity is augmented,relative Mach number around blade tip leading edge area is significantly reduced and so is the flow angle.As the flow angle decreased,the incidence angle reduced which greatly improves the flow field inside the impeller.Moreover,inlet recirculation changes the blade loading around blade tip and restrains the flow separation on the blade suction side at the leading edge area.The unsteady results of static pressure around blade surface,entropy at inlet crossflow section and vorticity distributions at near tip span surface indicated that,at near stall condition,strong fluctuation exists in the vicinity of tip area due to the interaction between tip leakage flow and core flow.By inlet recirculation these strong flow fluctuations are eliminated so the flow stability is greatly enhanced.All these improvements mentioned above are the reason for inlet recirculation delays compressor stall.This research reveals the surge margin extension reason of inlet recirculation from an unsteady flow viewpoint and provides important reference for inlet recirculation structure design. 相似文献
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Multi-objective optimization of an axial compressor blade 总被引:2,自引:0,他引:2
Numerical optimization with multiple objectives is carried out for design of an axial compressor blade. Two conflicting objectives,
total pressure ratio and adiabatic efficiency, are optimized with three design variables concerning sweep, lean and skew of
blade stacking line. Single objective optimizations have been also performed. At the data points generated by D-optimal design,
the objectives are calculated by three-dimensional Reynolds-averaged Navier-Stokes analysis. A second-order polynomial based
response surface model is generated, and the optimal point is searched by sequential quadratic programming method for single
objective optimization. Elitist non-dominated sorting of genetic algorithm (NSGA-II) with ε-constraint local search strategy
is used for multi-objective optimization. Both objective function values are found to be improved as compared to the reference
one by multi-objective optimization. The flow analysis results show the mechanism for the improvement of blade performance. 相似文献
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为了控制航空发动机压气机叶片损伤继续发展,通常采用孔探打磨进行修理。为研究其带来的影响,选取跨声速压气机Rotor37为研究对象,构建了不同叶高的叶片前缘打磨修理模型,采用数值模拟方法,研究了打磨修理对跨声速压气机气动性能的影响,结果表明:叶片前缘打磨修理使压气机整体性能下降,压比减小,效率降低,使堵塞点流量减小,而对失速流量点基本没有影响;不同叶高的打磨修理中心对压气机气动性能影响趋势一致影响幅度相当,但打磨叶高的不同造成压气机内部流场变化;叶片前缘打磨后,打磨处激波前马赫数增加,激波强度增大,影响效果随着叶高的增加而增加;压气机进口因为叶片打磨而造成相对动能在叶片打磨处附近降低。 相似文献
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将叶片和蜗室作为一个整体,对单流道泵内部三维非定常流动特性进行研究,经分析提出了单流道泵内部三维非定常势流流动和三维非定常湍流流动的数值模拟方法,分别计算了单流道泵内部的速度场、压力场和叶片表面的压力分布,对进一步研究单流道泵内部流动具有重要意义。在此基础上计算了叶轮所受的径向力及其变化趋势,为提高单流道泵运行稳定性提供了理论依据。此外还计算了扬程、平均水功率和效率,并与试验值作对比。尽管忽略粘性使得势流计算得到的速度场在蜗壳的局部区域出现反方向流动,从而导致叶片压力面压力沿展向波动变化,但其性能曲线与试验值变化趋势一致,粘性计算结果与试验值相比,精度较高。 相似文献