RP-3航空煤油五组分模拟替代燃料的层流燃烧特性

为了研究一种RP-3航空煤油的五组分模拟替代燃料（包含摩尔分数为14%正癸烷、10%正十二烷、30%异十六烷、36%甲基环己烷和10%甲苯）的燃烧特性,在定容燃烧装置中对初始温度390K、400K和420K,初始压力0.1MPa和0.3MPa,当量比0.8-1.5的该五组分混合燃料进行了层流燃烧特性的试验。通过对火焰照片进行边界提取和测量,获得了火焰面发展规律、马克斯坦长度和层流燃烧速率,并将试验结果与RP-3航空煤油的层流燃烧速度进行了对比,得出结论：温度升高会促进球形火焰面的传播;压力升高或混合气过浓和过稀都不利于五组分混合燃料的火焰传播。在本文的试验工况下,温度对火焰前锋面不稳定性的影响不明显;随着当量比增加,马克斯坦长度减小,质量扩散的作用逐渐增强而使火焰面变得不稳定;压力升高使火焰前锋面的不稳定程度明显加剧,表现为初始压力较高时火焰面破碎情况严重并出现大量细胞状结构。五组分混合燃料层流燃烧速度的峰值出现在当量比1.2左右,偏离该当量比时,火焰传播速度随着偏离量逐渐减小。通过与RP-3航空煤油的试验数据进行对比,发现在试验工况下,该五组分混合燃料与RP-3航空煤油的层流燃烧速度基本吻合。     

轴向流中圆柱体的非线性动力学分析

通过引入流体摩擦力的二次阻尼项,推导出了轴向流中两端简支圆柱体的新的运动微分方程。对添加二次阻尼项的运动微分方程进行了无量纲化和Ritz-Galerkin离散。通过数值模拟,对两端铰支圆柱体的稳定性进行了系统的分析,并得出颤振发生的临界流速条件。     

基于全局线性稳定性分析的翼尖双涡不稳定特征演化机理

相比于机翼产生的孤立翼尖涡,加装小翼之后的翼尖涡表现出双涡甚至多涡结构,并且呈现出更加复杂的不稳定特征。为揭示翼尖双涡结构不稳定特征及其演化机理,采用体视粒子图像测速（SPIV）技术和全局线性稳定性分析（LAS）方法对不同雷诺数和攻角下带双叉弯刀小翼的M6机翼产生的翼尖涡结构在尾迹区的不稳定特征进行研究。试验结果表明,对称布置的双叉弯刀小翼产生的翼尖涡包含上/下小翼产生的主涡（上/下主涡）结构,两者构成近似等强度的同转涡对,在相互靠近的同时以20 rad/s的角速度相互缠绕。对上/下主涡瞬时涡核位置的统计分析表明,翼尖涡摇摆幅值随流向位置逐渐增大,随雷诺数的增加而增大,随攻角的增加先增大后减小。对16倍弦长的尾迹截面处的翼尖双涡结构进行全局时间稳定性分析,不同工况下,上/下主涡最不稳定模态（模态P/模态S）的稳定性曲线变化规律与摇摆幅值的变化规律相一致,表明翼尖涡的摇摆源自于其内在的不稳定性特征。增加流向扰动波数,发现模态P切向波数逐渐增加;而模态S则是径向波数逐渐增加。不同工况下,模态P的切向波数为5~6,扰动波数分布在[2.75,5]的区间内,所对应的不稳定放大率均大于模态S,而不稳定放大率最大的模态扰动范围作用在上主涡的整个涡核区域,表明这种大切向波数的扰动模态在翼尖涡流控中的潜在价值,也意味着加装小翼会增加涡结构的个数,增强不稳定性的发展,有助于翼尖涡的快速失稳衰减。     

基于纳米多孔薄膜的蒸发特性

实验研究了基于纳米多孔薄膜的蒸发特性,以氟化液FC-72为液态工质,对比分析了开口向上和向下时的相变特性。结果发现：两种工况下,其热流密度-过热度曲线具有相似的变化趋势,且均出现热流密度增加而温度保持不变的“薄液膜蒸发”区间。在低热流密度下,温度均较为稳定,但开口向下时的传热性能始终优于开口向上时,分析原因为重力对供液的影响和液膜厚度对热阻的改变。随着热流密度的增加,表面温度波动也越来越剧烈,甚至出现了温度的峰值,最终开口向下和向上达到的临界热流密度值分别为59 W/cm2和47W/cm2;同时,对蒸发过程进行理论建模,得出其蒸发系数分别为0.043 1和0.021 9。     

航空发动机转子盘腔积油振动故障分析

结合工程中航空发动机转子在试验中遇到的积油振动问题,从积油振动理论、动力学特性和振动信号分析方面展开研究,剖析了转子盘腔积液故障机理,获得了所引起转子失稳振动的特征及规律,建立了盘腔积油故障识别的流程和准则,以及其振动监控指导.研究表明:积油在转子临界转速以上的特定区域才会产生明显的次谐波振动,引起转子自激振动,自激振...     

气流速度振荡场中幂律液膜不稳定性分析

采用线性稳定性分析研究了处于气流速度振荡场中幂律液膜时间模式的不稳定性。振荡的气流速度导致动量方程为含有时间周期系数的希尔方程，采用Floquet理论进行求解。详细研究了不同振荡幅值和振荡频率下表观雷诺数、幂律指数及无量纲速度因子对各不稳定区间的影响。结果表明：振荡幅值的增加或振荡频率的减小会使液膜不稳定区域的个数增加，且Kelvin-Helmholtz（K-H）不稳定区域的最大增长率、主导波数和截止波数随振荡幅值和振荡频率的增加而增加；表观雷诺数、幂律指数和无量纲速度因子的增加增强了K-H不稳定区域内的不稳定性，使参数不稳定区域内的增长率先减小后增加；振荡幅值的变化不改变最大增长率发生转折时对应的流变参数，而当振荡频率较小时，幂律指数和无量纲速度因子的增加却使最大增长率单调增加。     

机翼跨声速抖振数值模拟及模态分析

绕机翼的跨声速抖振流动是典型的复杂不稳定流动，对其非定常特性及失稳机制的研究具有重要的工程和学术价值。通过非定常雷诺平均Navier-Stokes（URANS）仿真方法和动模态分解（DMD）分析手段，研究了CRM（Common Research Model）等典型机翼的跨声速抖振流动特性及其主要失稳模态。数值仿真结果表明机翼的跨声速抖振表现为多失稳模式下的宽频特性。除了激波的弦向失稳，还会伴随发生激波的展向失稳，它们都表现为低频特性。翼梢处的高频响应可能是由激波诱导的低频失稳与翼尖涡相互耦合形成。DMD分析结果显示机翼展长和后掠因素诱导了激波展向失稳模态。本研究对抖振流动的物理建模、控制及理解相关的气动弹性现象具有指导意义。     

Solar activity variations of equatorial spread F occurrence and sustenance during different seasons over Indian longitudes: Empirical model and causative mechanisms

A comprehensive analysis using nearly two decades of ionosonde data is carried out on the seasonal and solar cycle variations of Equatorial Spread F (ESF) irregularities over magnetic equatorial location Trivandrum (8.5°N, 77°E). The corresponding Rayleigh Taylor (RT) instability growth rates (γ) are also estimated. A seasonal pattern of ESF occurrence and the corresponding γ is established for low solar (LSA), medium solar (MSA) and high solar (HSA) activity periods. For LSA, it is seen that the γ maximizes during post sunset time with comparable magnitudes for autumnal equinox (AE), vernal equinox (VE) and winter solstice (WS), while for summer solstice (SS) it maximizes in the post-midnight period. Concurrent responses are seen in the ESF occurrence pattern. For MSA, γ maximizes during post-sunset for VE followed by WS and AE while SS maximises during post-midnight period. The ESF occurrence for MSA is highest for VE (80%), followed by AE (70%), WS (60%) and SS (50%). In case of HSA, maximum γ occurs for VE followed by AE, WS and SS. The concurrent ESF occurrence maximizes for VE and AE (90%), WS and SS at 70%.The solar cycle variation of γ is examined. γ shows a linear variation with F10.7?cm flux. Further, ESF percentage occurrence and duration show an exponential and linear variation respectively with γ. An empirical model on the solar activity dependence of ESF occurrence and sustenance time over Indian longitudes is arrived at using the database spanning two solar cycles for the first time.     

Recent advances in physical understanding and quantitative prediction of impinging-jet dynamics and atomization

Impinging-jet injectors are widely used in liquid propulsion applications, since their simple configuration provides reliable and efficient atomization. The flowfield involves a series of complicated spatio-temporal evolutions. Much effort has been directed toward understanding the underlying physics and developing quantitative predictions of impinging-jet atomization. This paper summarizes the recent advances in this direction, including state-of-the-art theoretical, experimental, and numerical studies, along with representative results. Finally, concluding remarks address remaining challenges and highlight modeling capabilities of high-fidelity simulations.     

Effect of bent inlet pipe on the flow instability behavior of centrifugal compressors

Bent inlet pipes are often used in centrifugal compressors due to limited installation space, and an understanding of the effect on compressor stability is essential for safety and durability. This paper firstly investigates flow instability behaviors in two compressors, one with a straight inlet pipe and the other with an S-shaped bent pipe. In detail, it analyzes the resulting flow fields, instability evolution paths and surge boundaries. The results show that the S-shaped pipe obviously affects the flow field at high mass flow rates, while reverse flow mainly influences the flow field at low mass flow rates. Reverse flow first occurs at certain flow passages with a high pressure difference that is predominantly decided by the volute rather than the S-shaped bent pipe. In addition, centrifugal compressors can tolerate reverse flow to some extent so that surge would not occur immediately if reverse flow occurs unless the reverse flow region extends circumferentially and radially to a sufficiently large size. Since the S-shaped pipe is not dominant in the creation and extension of reverse flow, it does not exacerbate the stability of the central compressor to a great extent. Last but not least, the S-shaped pipe is noted to delay the occurrence of surge at 90% rotating speed, which suggests the possibility of improving compressor stability with bent inlet pipes. This result differs from the conventional understanding that inlet distortion usually deteriorates compressor stability and emphasizes the particularity of centrifugal compressors.