共查询到19条相似文献,搜索用时 140 毫秒
1.
多级压气机非定常流场数值分析 总被引:3,自引:0,他引:3
通过双时间步求解三维非定常N-S方程,获取多级压气机内部非定常流场细节,为深刻认识多级、逆压环境下叶轮机内部非定常流动特征,进而提高其性能提供有益参考,分析结果表明:动/静叶排相干对下游静子叶片表面压力分布影响随着半径增大而增大;当上游尾迹输运至下游叶片通道时,低能量气流团将会充分与主流掺混,可能导致损失增加,当上游尾迹区域输运至下游静子前缘时,对应的叶栅通道低马赫数区域相对较小;由于下游静子叶片的位势作用,其对上游转子叶片尾缘流动结构产生较大影响,随着流面半径增大,下游叶片对上游流场的位势作用愈明显,非定常分离流动形式差别愈大. 相似文献
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飞机机体表面的开孔设计会形成空腔结构,产生空腔流致噪声。空腔噪声的控制需要彻底认识其流动和噪声机理。以飞机的功能性开孔为例,通过半经验公式分析了其空腔噪声频率随速度的变化规律,预测了出现流声共振的工况。空腔发生流声共振时,特定频率的纯音噪声会被放大。为此,采用脱体涡模拟方法开展了开孔结构流声共振的三维非定常数值计算,分析了其流场和声场特性。其中,数值方法的准确性通过圆形空腔标模计算进行验证。结果表明,在一定速度下剪切层内的扰动将诱发空腔深度方向声模态,出现流声共振现象。此时,剪切层表现为强烈的周期性上下拍动,空腔底部和后缘区域的局部压力脉动幅值较大,声波主要由空腔后缘向上游方向辐射,上游噪声大于下游。 相似文献
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本文研究热激励器对超音速自由射流流动特性的影响,用S-A湍流模型得到马赫数为1.3的自由射流的准稳态流场,然后用LES方法模拟热激励器的热效应对射流流场不同区域的激励作用。文中讨论了持续式加热和脉动式加热对超音速剪切层涡发展的不同影响。前者通过提高局部区域温度,影响自由射流流场结构和超音速剪切层的涡结构;后者则通过凹槽内的脉动式热效应,产生压力扰动作用于主流场来改变涡的发展特性。 相似文献
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本文研究热激励器对超音速自由射流流动特性的影响,用S-A湍流模型得到马赫数为1.3的自由射流的准稳态流场,然后用LES方法模拟热激励器的热效应对射流流场不同区域的激励作用。文中讨论了持续式加热和脉动式加热对超音速剪切层涡发展的不同影响。前者通过提高局部区域温度,影响自由射流流场结构和超音速剪切层的涡结构;后者则通过凹槽内的脉动式热效应,产生压力扰动作用于主流场来改变涡的发展特性。 相似文献
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采用基于纳米示踪的平面激光散射技术(NPLS)对带超声速喷流的后台阶流动精细结构进行了研究. 来流马赫数为3.4, 喷流实测马赫数为2.45, 而名义马赫数为2.5. 结果清晰地揭示了激波、剪切层、混合层、Kelvin-Helmholtz涡、羊角涡及湍流大尺度结构等大量典型流场结构. 基于大量流场精细结构图像, 对典型位置处的结构进行了空间两点相关性分析, 在喷流混合层前端涡结构小于湍流充分发展的尾端, 结构角相对也小. 喷流工作时, 模型台阶下游表面由一薄层气膜覆盖. 获得了模型流向和不同高度展向平面内的流场结构, 对照纹影试验结果, 分析了流动特点及时间演化规律. 采用微型压力扫描系统测试了模型表面的压力系数分布, 靠近喷流下游处压力系数区域0.0146. 针对NPLS图像做了流动的分形维数的分析, 发现在流动初始阶段分形维数接近于1, 越靠下游分形维数越高. 相似文献
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本文主要针对低速开式空腔流动自激振荡产生噪声问题,在0.55 m×0.4 m航空声学风洞开展了不同低马赫数(0.1/0.15/0.2/0.25)条件下长深比为2的空腔腔内流场结构和噪声特性风洞试验研究。通过利用高频粒子图像测速技术捕捉腔内流场结构,分析了腔内声波传递路径;完成空腔远场噪声和壁面压力测试,分析了噪声自激振荡模态和简正波模态,并对空腔壁面脉动压力和远场噪声进行压/声相关性研究。结果表明:空腔内部除主涡外,在腔口前缘处剪切涡与腔口后缘处碰撞涡明显存在;在875 Hz,1288 Hz,1875 Hz,2050 Hz四个频率附近出现了由声腔共振所致的单频噪声;壁面压力与远场噪声密切相关,在壁面压力主频位置有明显单频噪声出现。 相似文献
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为了探究熵层对扫掠激波/湍流边界层干扰特性的影响规律,采用仿真方法对尖鳍/钝板物理模型进行研究。结果表明:扫掠激波上游的熵层厚度随着平板前缘钝化半径的增大而增加,同时边界层厚度也随着熵层厚度的增加而增加。熵层的引入并不改变扫掠激波/湍流边界层干扰固有的准锥形相似特性,也不会改变拟锥原点(virtual conical origin,VCO)的位置,仅会改变干扰形成的上游影响线和分离线的角度。扫掠激波/湍流边界层干扰形成的锥形主旋涡和角涡的尺度随着熵层厚度的增加而增大。上游熵层的引入增大了下游扫掠激波/湍流边界层干扰区的总压损失,但扫掠激波/湍流边界层干扰自身造成的相对总压损失并不受上游熵层的影响。 相似文献
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在一维平板鞘层中采用流体模型分别研究了不同成分无碰撞等离子体鞘层的玻姆判据.通过拟牛顿法数值模拟了含有电子、离子、负离子以及二次电子的等离子体鞘层玻姆判据.结果表明二次电子发射增加了鞘层离子马赫数的临界值,且器壁发射二次电子温度越高,离子马赫数临界值越小.负离子使离子马赫数临界值减小.而在含有二次电子和负离子的等离子体鞘层中,当负离子较少时,二次电子发射对离子马赫数临界值影响较大;当负离子增加时,离子马赫数的临界值则主要受负离子的影响.
关键词:
鞘层
等离子体
玻姆判据 相似文献
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欠膨胀超音速射流处于螺旋模式下的中度欠膨胀时,其入射剪切层的激波具有很高强度,激波和剪切层发生了强烈的相互作用,远场辐射的拢动波出现了大间隔、交错的上下行类似螺旋锥面波形图像,该扰动波具有很强的向上游传播的指向性,导致上游噪声高于垂直喷嘴方向的声压级.而在相对压比较低的低度欠膨胀情况下,或高压比下的高度欠膨胀的情形,入射剪切层激波强度相对较弱,远场辐射没有大间隔、交错的上下行远场辐射
关键词:
超音速射流
啸叫
扰动波
激波
剪切层 相似文献
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Miguel Fosas de Pando 《Journal of Turbulence》2017,18(4):338-351
Compressible flow over a flat plate with two localised and well-separated roughness elements is analysed by global frequency-response analysis. This analysis reveals a sustained feedback loop consisting of a convectively unstable shear-layer instability, triggered at the upstream roughness, and an upstream-propagating acoustic wave, originating at the downstream roughness and regenerating the shear-layer instability at the upstream protrusion. A typical multi-peaked frequency response is recovered from the numerical simulations. In addition, the optimal forcing and response clearly extract the components of this feedback loop and isolate flow regions of pronounced sensitivity and amplification. An efficient parametric-sensitivity framework is introduced and applied to the reference case which shows that first-order increases in Reynolds number and roughness height act destabilising on the flow, while changes in Mach number or roughness separation cause corresponding shifts in the peak frequencies. This information is gained with negligible effort beyond the reference case and can easily be applied to more complex flows. 相似文献
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Studies on the properties of flow-induced oscillation and sound radiation in streamlined protuberant special cavities 总被引:1,自引:0,他引:1
I.IntroductionAsanuidpassingthroughthecavityatcertainflowrate,themediuminthemouthandthccavityisoscillatingandsoundisradiated.Noton1ystochasticturbu1encenoiscispossi-blyproducedbutsinglefrequencysoundofspecia1lydesignatedpitchisalsoproduced.Andthusthespcctrumofthcradiatedsoundisshownascontinuousspectrumandcharacteristiclinespcctrum.Inthiscascwcmaycallitflow-inducedosci1lation.Flow-inducedoscillationandsoundradiationcanbeproducedasafluid(waterorgas)passingthroughthecavitybysinkingcavityunderint… 相似文献
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This paper describes the control of boundary layer on a flat plate by means of cavity flow. In this study, classifying the shapes of cavities into circular arc, rectangle and triangle makes the discussion, and the depths of the cavities are changed systematically. It is made clear, by numerical calculations and experiments, what states of flow are shown in the internal parts of cavities and what kinds of influence are exerted to the boundary layers in the upstream and downstream flows. As a result, the following facts are made clear. By taking up properly the depth ratios (k/c) of cavities complying with the individual cavity shapes, the boundary layer thickness in the flow upstream and downstream of the cavities can be controlled. Meanwhile with any of the cavities, the existence of the minimum boundary layer thickness (δ/δ m ) min min is seen at a depth ratio. 相似文献
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Shinji Nakaya Hajime Yamana Mitsuhiro Tsue 《Proceedings of the Combustion Institute》2021,38(3):3869-3880
The combustion instabilities of supersonic combustion were investigated experimentally in a laboratory-scale scramjet combustor with a cavity flame holder. Ethylene was injected transversely from an orifice to the supersonic flow of Mach 2 with a stagnation temperature of 1900 K and a total pressure of 0.37 MPa. The dynamic pressure, CH* chemiluminescence and shadowgraph images were measured with a pressure sensor and a high-speed video camera. Dynamic pressure was analyzed by fast Fourier transform, and time-resolved CH* chemiluminescence images were modally decomposed by the sparsity-promoting dynamic mode decomposition (SP-DMD). The results indicated that two combustion instabilities were observed for cavity shear-layer stabilized combustion and the oscillation between jet-wake stabilized and cavity shear-layer ram combustions for the power spectral density (PSD) of pressure. In the case of the combustion instability of cavity shear-layer stabilized combustion, a dominant peak of approximately 128 Hz was observed for the PSD of pressure. This instability corresponded to an entire flame oscillation of the cavity shear-layer stabilized combustion, which was validated by the SP-DMD and a low rank reproduction with 10 modes. This was driven by a fuel injection oscillation in the injection orifice. In the case of oscillation between the jet-wake stabilized and the cavity shear-layer ram combustions, peaks around 1600 Hz were observed for the PSD of pressure. This mechanism was also explained by the SP-DMD modes and a low rank reproduction using within 10 modes. The DMD and shadowgraph images indicated that the vortex formed by a separation of the boundary layer induced a strong jet-wake flame, resulting in the temporal thermal choke followed by cavity shear-layer stabilized ram combustion. The data-driven approach with SP-DMD clarified the combustion instability mechanisms of the supersonic combustion in detail. 相似文献
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In-duct devices are commonly installed in flow ducts for various flow management purposes. The structural construction of these devices indispensably creates disruption to smooth flow through duct passages so they exist as structural discontinuities in duct flow. The presence of these discontinuities provides additional possibility of noise generation. In real practice, in-duct devices do not exist alone in any duct system. Even though each in-duct device would generate its own noise, it might be possible that these devices could be properly arranged so as to strengthen the interference between individual noise; thus giving rise to an overall reduction of noise radiation in the in-duct far field. This concept of passive noise control is investigated by considering different configurations of two structural discontinuities of simple form (i.e., a cavity) in tandem in an unconfined flow and in opposing setting within a flow duct. It is known that noise generated by a cavity in unconfined domain (unconfined cavity) is strongly dependent on flow-resonant behavior within the cavity so the interference it produces is merely aeroacoustic. The objective of the present study is to verify the concept of passive noise reduction through enhancement of aeroacoustic interference due to two cavities by considering laminar flow only. A two-dimensional approach is adopted for the direct aeroacoustic calculations using a direct numerical simulation (DNS) technique. The position and geometries of the cavities and the Mach number are varied; the resultant aeroacoustic behavior and acoustic power are calculated. The numerical results are compared with a single cavity case to highlight the effect of introducing additional cavities to the aeroacoustic problem. Resonant flow oscillations occur when two unconfined cavities are very close and the associated acoustic field is very intense with no noise reduction possible. However, for duct aeroacoustics, it is found that a 7.9 db reduction of acoustic power in the downstream side of the duct or a total reduction of ∼6 db is possible with opposing cavities having an offset of half a cavity length. In addition, the reduction is shown to be free from lock-on with trapped modes of the ducts with cavities. 相似文献
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C.K.W. Tam 《Journal of sound and vibration》1976,49(3):353-364
A theoretical study of the acoustic modes of a two-dimensional rectangular cavity is presented in this paper. It is found that for cavities with length to depth ratio of unity or larger the natural modes are heavily damped due to acoustic radiation. Numerical results for lower order modes are given. The physical significance of strong radiation damping on the onset of cavity tones induced by outside flow at low Mach number is discussed. 相似文献