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| 1 | 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 |
| 2 | 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 |
| 3 | Mitigating self-excited flame pulsating and thermoacoustic oscillations using perforated liners显示文摘Open-loop control of self-excited flame pulsating oscillations and thermo-acoustic instability is considered in this work.The performance of the control strategy is numerically evaluated in a 2 D Rij ke-type combustor with a perfo rated pipe implemented.It is found that approximately 38 dB sound pressure level(SPL)reduction can be achieved by actively tuning the cooling flow through the perforated pipe.Furthermore,the vorticity-induced damping performance is contributing to the breaking up of flame-acoustics coupling.However,the shedding of vortices is not uniformly distributed along the perforated pipe.To apply the control strategy in practice and to validate the findings,experimental studies are performed on a customerdesigned Rij ke-type combustor with a perfo rated liner implemented.To mimic practical engines,a cooling flow generated by a centrifugal pump is provided to pass through the perforated pipe.Properly tuning the cooling flow rate is found to lead to the unstable combustor being successfully stabilized.SPL is red uced by approximately 35 dB at ω1/2π≈245 Hz,and harmonic thermoacoustic modes are completely attenuating.Further study is conducted by suddenly re moving the perforated pipe section.The combustion system is found to be associated with not only classical thermo-acoustic limit cycle oscillations with a dominant mode at 2.45 × 102 Hz,but also beating oscillations at 1.4 × 1 00 Hz.It is revealed that increasing acoustic losses by implementing the perforated pipe is another critical mechanism contributing to attenuating flame pulsating instability.The present work opens up an applicable means to attenuate both selfexcited high-frequency thermoacoustic and low-frequency flame pulsating oscillations. | Dan Zhao Ephraim Gutmark Arne Reinecke | 2019 | Science Bulletin2019，64，13： | 3 |
| 4 | 电场作用下火焰中离子对燃烧反应速率的数值模拟研究显示文摘本文针对甲烷-空气预混火焰中离子对火焰化学动力学特性的影响开展了理论模拟研究。在不同外加电场作用条件下,分析了离子从火焰面区域迁移到低温预热区时对当地化学反应的影响规律。研究表明,低温区内(~800 K)离子对反应速率的影响较大,甚至反应时间可减少65%,而对于1200 K以上高温区该影响则可忽略。实验结果进一步揭示了电场对旋流火焰的影响主要是通过离子风效应改变了火焰面位置和形状而造成的。 | 崔巍 杨君宇 任翊华 李水清 | 2018 | 工程热物理学报2018，39，6： | 3 |
| 5 | 局域共振薄膜结构的管腔热声耦合振荡抑制研究显示文摘针对不稳定热释放与声场耦合而产生的热声振荡现象,严重影响燃烧系统的稳定性和振动噪声水平的问题,本文提出一种有效的热声耦合振荡抑制策略。本文基于能量原理和声压连续条件建立了周期分布局域共振薄膜结构-管腔-火焰耦合模型,研究了薄膜结构对管腔热声耦合系统热、声模态稳定性的抑制作用,并揭示了周期结构声学带隙对系统模态稳定性的影响规律。结果表明:薄膜结构可实现管腔耦合系统的多模态不稳定性抑制,尤其对声模态特征有显著的干涉作用。此外,可以发现热声耦合系统特征根分布受声学带隙影响较大,部分模态急剧向低频偏移,且所研究频段范围内模态稳定性均得到了改善,充分说明了本文所提出周期性局域共振薄膜在热声耦合不稳定性抑制方面的有效性。 | 刘杨 陈京圳 杜敬涛 | 2022 | 哈尔滨工程大学学报2022，43，9： | 0 |
| 6 | 航空发动机燃烧不稳定性预测及控制研究进展显示文摘燃烧不稳定性问题广泛出现在各类航空发动机燃烧室内,该问题是火焰非定常热释放和声波充分耦合的结果,发生时伴随着大幅度的压力脉动,严重威胁发动机的稳定工作及结构安全。目前,包括中国在内的各航空发动机研制国家在多数发动机型号的研制过程中,均遇到了严重的燃烧不稳定性问题,且发动机越先进,该问题越复杂且难以解决。在深入认识其发生机理的基础上,对其进行准确预测并设计有效的控制手段,对航空发动机的研制具有重要意义。系统阐述了该问题的研究现状,介绍了燃烧不稳定性问题发生关键,即军用的钝体燃烧加力燃烧室和民用的贫油预混环形燃烧室的非定常流动及火焰响应特征。综述了该问题研究常用的燃烧不稳定性声网络预测分析模型,重点报告了为了耦合考虑燃烧室声软壁面被动控制设计,团队所发展的三维燃烧不稳定性预测控制模型。基于该模型,介绍了壁面声衬参数及布局对燃烧不稳定模态控制效果影响的研究进展,为先进发动机燃烧不稳定性的排故提供技术储备。 | 孙晓峰 张光宇 王晓宇 李磊 邓向阳 程荣辉 | 2023 | 航空学报2023，44，14： | 0 |
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