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| 1 | Recent development of casing treatments for aeroengine compressors显示文摘Casing treatment is a mature stabilization technique which has been widely applied on aero-engines for modern aircrafts and turbo-chargers for automobiles. After the investigations of half century since the 1960 s, this technique has been well developed for various configurations with different effectiveness. From the perspective of stabilization mechanism, this paper roughly categorizes the configurations of casing treatment into two types: traditional ones which work by affecting the flow structure of blade tip region; a novel one named as Stall Precursor-Suppressed(SPS) casing treatment. The effectiveness of both types will be demonstrated for their applications on axial compressors and centrifugal compressors with uniform or distorted inlet. And the stabilization mechanism of casing treatments for regular types and SPS one will also be explained respectively. In addition, this review will summarize the methodologies of casing treatments with the numerical simulations for regular grooved configurations and the eigenvalue approach for SPS casing treatment.Looking forward to the future of compressor stabilization, casing treatment technique will still exist as a general and inexpensive option, and the exploration for its effectiveness and mechanism will be deeper with the development of computational fluid dynamics and advanced measurement techniques. | Xiaofeng SUN Xu DONG Dakun SUN | 2019 | Chinese Journal of Aeronautics2019，32，1： | 16 |
| 2 | Flow Stability Model for Fan/Compressors with Annular Duct and Novel Casing Treatment显示文摘A three-dimensional compressible flow stability model is presented in this paper, which focuses on stall inception of multi-stage axial flow compressors with a finite large radius annular duct configuration for the first time. It is shown that under some assumptions, the stability equation can be obtained yielding from a group of homogeneous equations. The stability can be judged by the non-dimensional imaginary part of the resultant complex frequency eigenvalue. Further more, based on the analysis of the unsteady phenomenon caused by casing treatment, the function of casing treatment has been modeled by a wall impedance condition which is included in the stability model through the eigenvalues and the corresponding eigenfunctions of the system. Finally, some experimental investigation and two numerical evaluation cases are conducted to validate this model and emphasis is placed on numerically studying the sensitivity of the setup of different boundary conditions on the stall inception of axial flow fan/compressors. A novel casing treatment which consists of a backchamber and a perforated plate is suggested, and it is noted that the open area ratio of the casing treatment is less than 10%, and is far smaller than conventional casing treatment with open area ratio of over 50%, which could result in stall margin improvement without obvious efficiency loss of fan/compressors. | LIU Xiaohua SUN Dakun SUN Xiaofeng WANG Xiaoyu | 2012 | Chinese Journal of Aeronautics2012，25，2： | 12 |
| 3 | 航空压气机流动稳定性预测研究进展显示文摘在航空压气机设计阶段,对其稳定裕度进行快速、准确评估,防患于未然,具有迫切需求和重要意义。首先评述了现有的压气机流动稳定性理论预测方法,并重点就近期发展起来的叶轮机流动稳定性通用理论做了系统的介绍。随后,汇总了叶轮机流动稳定性通用理论在亚声速、跨声速轴流压气机以及亚声速离心压气机等不同机型上的应用,从现有算例来看,该理论有能力对不同类型的压气机失速起始点做出准确的预测。进一步,综述了基于叶轮机流动稳定性通用理论所开展的针对压缩性、叶尖间隙以及三维叶片造型等因素的参数化研究工作。研究结果表明,该理论在定性层面上能够捕捉到这些因素的影响,然而,这些预测结果定量上尚未得到实验的验证,需要进一步开展相应的实验研究。目前,叶轮机流动稳定性通用理论只在单级或单转子压气机上得到应用,对于多级压气机,还需要在定常流场的计算方法、大规模矩阵特征值求解等方面开展更加深入的研究。 | 孙晓峰 何晨 刘小华 马云飞 孙大坤 | 2017 | 推进技术2017，38，10： | 8 |
| 4 | Influence of SPS casing treatment on axial flow compressor subjected to radial pressure distortion显示文摘The present work is about the stall margin enhancement ability of a kind of stall precursor-suppressed(SPS) casing treatment when fan/compressor suffers from a radial total pressure inlet distortion.Experimental researches are conducted on a low-speed compressor with and without SPS casing treatment under radial distorted inlet flow of different levels as well as uniform inlet flow.The distorted flow fields of different levels are generated by annular distortion flow generators of different heights.The characteristic curves under these conditions are measured and analyzed.The results show that the radial inlet distortion could cause a stall margin loss from 2%to30%under different distorted levels.The SPS casing treatment could remedy this stall margin loss under small distortion level and only partly make up the stall margin loss caused by distortion in large level without leading to perceptible additional efficiency loss and obvious change of characteristic curves.The pre-stall behavior of the compressor is investigated to reveal the mechanism of this stall margin improvement ability of the SPS casing treatment.The results do show that this casing treatment delays the occurrence of rotating stall by weakening the pressure perturbations and suppressing the nonlinear amplification of the stall precursor waves in the compression system. | Li Fanyu Li Jun Dong Xu Sun Dakun Sun Xiaofeng | 2017 | Chinese Journal of Aeronautics2017，30，2： | 8 |
| 5 | 进气畸变条件下新型机匣处理扩稳效果实验研究显示文摘为考察在总压进气畸变条件下对压气机流动稳定性的影响以及如何进行有效扩稳,开展了一种新型机匣处理扩大轴流风扇/压气机稳定裕度的实验研究。主要内容包括:进气畸变下的压气机流量压比特性实验,研究新型机匣处理的扩稳效果,并对压气机工作效率的影响进行了评估。实验结果表明:①进气畸变下,压气机压升一流量特性曲线失速边界向右下偏移,即压气机失速裕度变小,并且畸变程度越高,失速裕度损失越多;②新型机匣处理在进气畸变条件下对风扇/压气机有显著的扩稳效果,失速裕度可提高5%~8%;③较大(20%以上)进气畸变条件下,机匣处理会带来1%~2%左右的压气机效率损失,而较小(20%以内)进气畸变条件下,机匣处理在扩稳的同时,可以基本保持压气机工作效率不变。 | 熊珊 孙大坤 所秋玲 陈俊 孙晓峰 | 2013 | 航空学报2013，34，12： | 7 |
| 6 | A high-order model of rotating stall in axial compressors with inlet distortion显示文摘In this paper,a high-order distortion model is proposed for analyzing the rotating stall inception process induced by inlet distortion in axial compressors.A distortion-generating screen in the compressor inlet is considered.By assuming a quadratic function for the local flow total pressure-drop,the existing Mansoux model is extended to include the effects of static inlet distortion,and a new high-order distortion model is derived.To illustrate the effectiveness of the distortion model,numerical simulations are performed on an eighteenth-order model.It is demonstrated that long length-scale disturbances emerge out of the distorted background flow,and further induce the onset of rotating stall in advance.In addition,the circumferential non-uniform distribution and time evolution of the axial flow are also shown to be consistent with the existing features.It is thus shown that the high-order distortion model is capable of describing the transient behavior of stall inception and will contribute further to stall detection under inlet distortion. | Peng LIN Cong WANG Yong WANG | 2017 | Chinese Journal of Aeronautics2017，30，3： | 5 |
| 7 | Transfer element method with application to acoustic design of aeroengine nacelle显示文摘In the present survey, various methods for the acoustic design of aeroengine nacelle are first briefly introduced along with the comments on their advantages and disadvantages for practical application, and then detailed analysis and discussion focus on a kind of new method which is called ‘‘transfer element method''(TEM) with emphasis on its application in the following three problems: turbomachinery noise generations, sound transmission in ducts and radiation from the inlet and outlet of ducts, as well as the interaction between them. In the theoretical frame of the TEM, the solution of acoustic field in an infinite duct with stator sound source or liner is extended to that in a finite domain with all knows and unknowns on the interface plane, and the relevant acoustic field is solved by setting up matching equation. In addition, based on combining the TEM with the boundary element method(BEM) by establishing the pressure and its derivative continuum conditions on the inlet and outlet surface, the sound radiation from the inlet and outlet of ducts can also be investigated. Finally, the effects of various interactions between the sound source and acoustic treatment have been discussed in this survey. The numerical examples indicate that it is quite important to consider the effect of such interactions on sound attenuation during the acoustic design of aeroengine nacelle. | Wang Xiaoyu Sun Xiaofeng | 2015 | Chinese Journal of Aeronautics2015，28，2： | 5 |
| 8 | Experimental investigation on SPS casing treatment with bias flow显示文摘Generally, casing treatment(CT) is a passivity method to enhance the stall margin of fan/compressor. A novel casing treatment based on the small disturbance theory and vortex and wave interaction suggestion is a method combining passive control and active control, which has been proved effective at enhancing the stall margin of fan/compressor in experiment. In order to investigate the mechanism of this kind of casing treatment, an experimental investigation of a stall precursor-suppressed(SPS) casing treatment with air suction or blowing air is conducted in the present paper. The SPS casing treatment is designed to suppressing stall precursors to realize stall margin enhancement in turbomachinery. The experimental results show that the casing treatment with blowing air of small quantity can improve the stall margin by about 8% with about 1% efficiency loss. By contrast, the SPS casing treatment with micro-bias flow does not improve the stall margin much more than that without bias flow, even worse. Meanwhile, the present investigation has also attempted to reveal the mechanism of stall margin improvement with the casing treatment.It is found that the stall margin improvements vary with the modification of the unsteady shedding flow and the unsteady wall boundary impedance. The experimental results agree fairly well with the theoretical prediction using a flow stability model of rotating stall. | Dong Xu Liu Xiaohua Sun Dakun Sun Xiaofeng | 2014 | Chinese Journal of Aeronautics2014，27，6： | 5 |
| 9 | 失速先兆抑制型机匣处理研究进展显示文摘随着现代高负荷航空发动机推重比的不断提高,风扇/压气机流动稳定性问题日益突出,而机匣处理是目前最有效的扩稳技术措施之一。首先回顾了机匣处理扩稳设计的研究历程和所面临的技术困难,进而阐述了失速先兆抑制型(SPS)机匣处理的研究思路和基本原理。基于所发展的SPS机匣处理理论设计模型,针对亚声速风扇和跨声速压气机进行了扩稳效果评估,结果显示,可以使亚声速风扇TA36和跨声速压气机J69Stage的流量裕度分别提高7.6%和6.8%。然后通过实验验证了SPS机匣处理的有效性,亚声速风扇TA36和跨声速压气机J69Stage流量裕度分别提高5.5%和9.3%,综合失速裕度均能够达到12%以上。同时,SPS机匣处理在小穿孔率大背腔情况下能够保持压气机原有的压升特性、峰值效率以及叶片径向负荷分布。最后,通过对失速先兆演化过程的对比分析发现,SPS机匣处理基于波涡相互作用改变了动力系统的阻抗边界条件,抑制了流场中的失速先兆的非线性放大,从而抑制旋转失速的发生。SPS机匣处理扩稳技术明显有别于传统机匣处理力图改变压气机尖区流动结构的扩稳思路,也完全不同于主动控制技术对消失速先兆波的研究策略,该技术为风扇/压气机流动稳定性控制提供了一种可供选择的技术途径。 | 孙晓峰 孙大坤 | 2015 | 航空学报2015，36，8： | 4 |
| 10 | 特征值理论在稳定性预测中的应用研究进展显示文摘航空发动机三大主要部件风扇/压气机、燃烧室和涡轮的稳定工作范围直接决定了发动机整机的性能和稳定性,在追求高气动性能、高涡轮前温度和低排放的同时,主要部件的气动、气弹和燃烧稳定性问题变得尤为突出。基于经验的稳定性预估方法已不适用于现代航空发动机一体化的设计思想,发展快速、准确的稳定性评估方法和稳定性控制技术并将其纳入发动机设计流程具有重要的理论和工程价值。本文主要综述了基于小扰动方法和特征值理论发展的多种半解析模型的研究进展,该方法在设计阶段可以有效评估风扇/压气机气动稳定性、预测叶片颤振和主/加力燃烧室热声不稳定性,为进一步开展稳定性控制设计提供了基础,且为节约实验和数值成本,建立发动机一体化设计方法提供了可能。 | 孙晓峰 董旭 张光宇 王卓 孙大坤 | 2022 | 航空学报2022，43，10： | 4 |
| 11 | 旋转畸变条件下新型机匣处理扩稳效果试验显示文摘开展了一种新型机匣处理扩大轴流风扇/压气机稳定裕度的试验研究。在低速风扇试验台上模拟旋转进气畸变,分析此种畸变进气条件对压气机工作性能造成的影响,并且考察一种新型机匣处理的扩稳效果。旋转进气畸变下,压升-流量特性曲线失速边界向右下偏移,压气机失速裕度明显降低。新型机匣处理在旋转进气畸变条件下对风扇/压气机有显著的扩稳效果,较小畸变转速(200,500r/min)情况下,新型机匣处理能提高压气机稳定裕度10%~20%,同时并没有带来明显的效率损失;畸变转速为800r/min情况下,机匣处理的扩稳效果相比并不明显,但可以提高压气机工作效率1%~2%。较大畸变转速情况下,畸变方向不同,机匣处理扩稳效果有所差别:正向畸变时机匣处理提高压气机失速裕度3%~10%,提高效率1%左右;而反向畸变时,失速裕度均提高10%以上,甚至达到20%,但压气机效率损失在1%左右。 | 董旭 刘小华 孙大坤 孙晓峰 | 2014 | 航空学报2014，35，9： | 3 |
| 12 | Prediction of stall inception in multi-stage compressors based on an eigenvalue approach显示文摘A stability model for multi-stage compressor is developed on the basis of the eigenvalue approach.This model assumes that the unsteady flow field can be decomposed into pressure,vortex and entropy waves.Besides,a linear cascade of blades is modeled by three-dimensional semi-actuator disk theory and the characteristics of steady flow field are also considered in the present model.The connection between the analytical solution for stator,rotor and gap can be established by applying mode matching approach,the relevant stability equation can be expressed in the form of matrix,while the compressor system stability can be judged by the imaginary part of the matrix eigenvalue.The capacity of the stall inception model to predict the stall inception point of multi-stage compressor is assessed against the experimental data of National Aeronautics and Space Administration(NASA) two stage fan.The theoretical results show that this model can predict the stall onset points of a two-stage fan at different operating speeds with a reasonable accuracy. | CHENG FanJie SUN DaKun DONG Xu SUN XiaoFeng | 2017 | Science China(Technological Sciences)2017，60，8： | 3 |
| 13 | Effect of system response on partial surge initiated instability in a transonic axial flow compressor显示文摘Partial surge is a type of instability inception in transonic compressors and occurs in the form of axisymmetric low-frequency disturbances localized in the hub region.Previous studies illustrate that the frequency of partial surge is set by the Helmholtz frequency of the entire system,which motivates to propose a hypothesis that the system response performs an important role in the formation of partial surge.For further verification,a series of experiments are conducted to explore the link between the propagating of the partial surge and the system feedback in this study.In the first case,an additional test point is set on the wall of the plenum to detect the system response.Combining the flow behaviors inside the plenum with the disturbances in the rotor tip and stator hub/tip regions,the effects of the system feedback on the occurrence of the continuous disturbances and the rotating stall cells are illustrated.In the second case,a screen is mounted at the compressor outlet to prevent positive feedback from the plenum.The experimental results demonstrate that in the absence of system feedback,it is the occurrence of spike-type stall inception that leads to the flow instability instead of that of partial surge.In addition,three flow phenomena in the second case are discussed,including the occurrence of the single pulse,the unstable process during the stall evolution and the switch of instability inception. | Tianyu PAN Zhaoqi YAN Dakun SUN Simin LI Mengzong ZHENG Qiushi LI | 2022 | Chinese Journal of Aeronautics2022，35，2： | 2 |
| 14 | 紧连阀轴流压气机变转速过失速瞬态模型显示文摘为了给各种压气机喘振主动控制器提供验证平台,提出了一个新的旋转失速及喘振模型.该模型在Moore-Greitzer轴流压气机过失速瞬态模型的基础上,考虑了转子动态及旋转失速高阶谐波对压气机气动稳定性的影响,并且在模型中增加了紧连阀作为执行机构.仿真结果表明:随着压气机转速的增加,压气机的失稳行为由旋转失速转为喘振;压气机转速的变化作为系统内部扰动,可能使压气机在节流阀开度较大时便进入气动失稳状态;虽然压气机初始扰动仅含有1阶谐波,但随着旋转失速的发展,高阶谐波强度不断增长而变得不可忽略. | 黄伟 黄向华 | 2013 | 航空动力学报2013，28，7： | 1 |
| 15 | 多级压气机失速起始点预测方法的应用显示文摘本文基于所发展的多级压气机流动稳定性快速预测模型,首先应用激盘和半激盘模型对TA66低速实验台进行了失速起始点预测,并与实验结果对比,验证了模型的可靠性,讨论了不同径向模态与周向模态对预测结果的影响。进而用此模型预测了某型涡扇发动机的压气机稳定工作范围,为其稳定性设计提供依据,并逐级减少叶片排数量,观察系统稳定性变化,分析了多叶片排对系统稳定性带来的影响. | 鲍毅超 熊珊 程凡解 冀国锋 孙大坤 孙晓峰 | 2019 | 工程热物理学报2019，40，12： | 1 |
| 16 | 轴流压气机流线流动稳定性分析显示文摘本文基于叶轮机流动稳定性通用理论的理论架构,建立了压气机流线流动稳定性模型。利用所提出的稳定性模型及相关计算方法,对一典型轴流压气机开展了流动稳定性计算。计算结果表明,所发展的流线流动稳定性模型能够有效地捕捉到不同工况、不同展向位置流线的稳定性差异及变化规律。并从理论计算层面上证明了叶根和叶尖附近流动是压气机流动稳定性的薄弱环节,尤其是叶尖附近流动,决定了系统的稳定边界。此外,根据稳定性分析结果以及对不同工况、不同叶高位置流线流向速度分布的观察,将流向速度在前缘附近沿流线的分布归结为三种形式:单调减速、先加速后减速和单调加速。从稳定性角度看,最理想的速度分布是单调加速,其次是先加速后减速,而在前缘之前就开始减速的流线速度分布是对稳定性不利的。 | 何晨 许登科 孙大坤 孙晓峰 | 2018 | 工程热物理学报2018，39，11： | 0 |
| 17 | 旋转进气畸变下的两级压气机扩稳实验研究显示文摘针对旋转进气畸变诱发的流动稳定性问题,在两级压气机上开展了基于失速先兆抑制型(Stall-Precursor-Suppressed,SPS)机匣处理的气动扩稳实验研究。在两级低速压气机实验台上数模拟旋转畸变进气条件,研究不同的畸变程度下旋转畸变对两级压气机稳定性的影响,并考察在第一级转子前缘上方安装SPS机匣处理后的扩稳效果。在畸变转速小于600r/min时,压气机稳定边界向右移动,效率下降明显。畸变转速大于800r/min时,旋转畸变对两级压气机作用效果趋于改善,相对而言,反向畸变比正向畸变具有更好的延缓失速效果。SPS机匣处理在不同畸变程度下均具有扩稳作用,失速裕度改善可以达到2%~7.9%,并且带来的效率损失均小于1%。 | 李佳 孙大坤 董旭 顾本昊 李凡玉 孙晓峰 | 2020 | 工程热物理学报2020，41，6： | 0 |
| 18 | Calibration of S-duct Swirl Distortion Based on Vortex Identification Methods显示文摘The S-shape inlet has been widely used in advanced military aircraft due to their advantage of reducing radar signature.However,the curvature of the inlet usually causes different kinds of intake distortion at the aerodynamic interface plane(AIP).Among them,the swirl distortion has been seriously concerned because of its great impact on the performance and stability of aero-engines.There is still no universal criterion for assessing the stability of compressors in the condition of strong swirl distortion.As an approach of assessing the swirl intensity and pattern,vortex identification method may be used as an auxiliary method for stability analysis.In this paper,numerical and experimental investigations on different S-ducts were carried out.The axial vorticity component and g criterion were used to analyze the quantitative correlation between geometry and swirl intensity.It was found that there is a relatively strong correlation between the geometry,the axial vorticity component and the Q criterion.The present investigation may provide a quick reconstruction method to model the effect of S-ducts for compressor stability prediction. | SUN Dakun LI Zhenyu DONG Xu SUN Xiaofeng | 2022 | Journal of Thermal Science2022，31，1： | 0 |
| 19 | 体积力模型在模拟轴流压气机进气畸变中的应用显示文摘该文推导了跨声速轴流式压气机的周向平均体积力模型,并在商用软件Ansys CFX上搭建了数值计算平台。该平台将代替叶片对流体作用力和做功量的周向体积力模型以源项的形式添加到Ansys CFX的三维控制方程中,发展形成了一种更加高速有效的压气机进气畸变数值计算方法。采用该计算方法进行NASA Stage 37单级跨声速压气机全流道模拟,计算了在70%设计转速、均匀进气工况下的压气机性能特性和流场分布,并与实验结果进行对比分析。结果表明,两者能很好地吻合一致,验证了计算方法的可行性和计算结果的准确性。在此基础上,采用该计算方法对该压气机在周向进气畸变条件下的性能和流场进行了预测,模拟结果也很好地反映了畸变来流对压气机特性的影响。 | 刘震雄 刁恒之 | 2023 | 机械研究与应用2023，36，5： | 0 |
| 20 | 插板进气畸变对多级压气机性能及稳定性影响研究显示文摘为研究插板进气畸变对压气机的影响,本文发展了一种可以在进气畸变条件下对压气机进行稳定性预测的周向非均匀二维稳定性模型。该模型将压气机进行周向分区并假设各分区满足平行压气机模型,并在轴向将叶片排视为激盘,利用小扰动理论将稳定性问题转化为特征值问题进而进行稳定性分析。模型利用某型两级跨音风扇进行了相关验证证明了其准确性。针对插板进气畸变的模拟及稳定性预测结果主要得到以下结论:本文发展的模型能够比CFD更加准确地预测稳定边界;进气畸变使风扇稳定裕度大幅下降,且影响该风扇稳定裕度的主要因素为有无畸变,在有进气畸变的情况下,增大插板深度对稳定裕度的影响相对较小;本文模型在进气畸变条件下的预测结果较为保守。 | 张强 顾本昊 仵凯 张明 许登科 孙大坤 孙晓峰 | 2023 | 工程热物理学报2023，44，7： | 0 |
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