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基于介质阻挡放电等离子体体积力气动激励机理,数值研究了两种等离子体流动控制方案对螺旋桨桨径根部处于负攻角工况下叶素气动性能的改善效果.结果显示,激励器布置在下翼面时等离子体体积力大于其布置在叶素前后缘时的情况;激励器布置在下翼面时,可抑制流动分离,使得螺旋桨桨根部位叶素产生更大的负拉力,但会减小螺旋桨的扭矩;激励器布置在前后缘时,会使螺旋桨根部叶素拉力增大,提高螺旋桨总拉力,但不能抑制流动分离,所以会增大螺旋桨的扭矩.     

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基于介质阻挡放电等离子体的体积力气动激励机理,仿真研究了等离子体增升减阻技术对沿螺旋桨桨径方向均匀分布的10个叶素气动特性的改善效果.采用叶素理论,对比分析了等离子体对螺旋桨整体气动性能的提高效果.主要结论有:桨尖和桨叶根部的叶素容易发生气动分离现象,其中根部叶素处于负攻角的工况中;采用介质阻挡放电等离子体流动控制技术可以完全抑制流动分离不太严重的桨叶中部区域的叶素气动分离,对桨尖处翼型的严重气动分离不能完全抑制但也有改善作用,但对处于负攻角工况的叶素作用不大;等离子体增升减阻技术确实可以提高螺旋桨的气动性能,对本文所研究的情况,螺旋桨的拉力和效率分别提高了28.27％和 12.3％.     

压气机悬臂静叶流场非定常数值模拟

以现代高压压气机一排悬臂静叶与一排转叶组成的典型级为研究对象,采用非定常数值模拟方法,分析了非定常与定常数值模拟计算得出的级特性线以及峰值效率点气动参数在展向分布的差异,并对悬臂静叶内部流场结构进行了详细分析,结果表明:当悬臂静叶的轮毂设计间隙为2.5%叶高时,非定常计算的综合喘振裕度比定常大5.85%;在峰值效率点工况下,悬臂静叶总压损失和转子效率的非定常影响范围在10%以内,转叶进口相对气流角沿展向分布的影响在0.5°以内。悬臂静叶根部10%叶高以下区域出现了明显的泄漏流动,3.4%叶高压力系数变化最大,轮毂泄漏流起始于20%弦长附近,发展到70%弦长位置时泄漏损失最大,随后逐渐减弱.     

平面扩压叶栅静叶相对位置改变对流动的影响

本文选取某重复级压气机平均半径处的型线,进行平面扩压叶栅非定常数值模拟。对8组不同的静叶相对位置进行了非定常计算,讨论了不同位置时流场的流动特点,优化出第一级、第二级静叶在给定的气动条件下最佳相对位置。     

连续和重复频率激光对旋转壳体加热效率的数值模拟

 基于有效利用激光能量的目的，采用有限元分析方法分析并比较了重复频率和连续激光对旋转壳体的加热效率。数值计算结果表明：重复频率激光要比连续激光的加热效率高，而且加热效率与重复频率、占空比等有关；在平均功率密度相同的前提下，在频率相同条件下，占空比减小，温度上升加快，即加热效率随占空比的减小而增大；在相同占空比条件下，重复频率越小温度周期变化越明显，振荡峰值越大，当占空比较小时随着辐照时间的增加重复频率对加热效率影响减小。     

船舶无空泡螺旋桨非定常推力脉动及其诱导线谱噪声分析

对船舶无空泡螺旋桨非定常推力脉动及其诱导的线谱噪声进行了研究,主要目的在于螺旋桨非定常推力脉动理论预报方法的验证。基于速度势面元法计算得到非均匀流场中无空泡螺旋桨的推力脉动,在大型循环水槽中利用非定常动力仪测试得到全附体船后螺旋桨的脉动推力,以脉动推力作为声源项预报得远场线谱噪声。一阶叶频非定常推力系数理论计算值与试验值最大相差29.3%,由此引起的线谱噪声差别为3.0 dB。上述结果表明,面元法预报船后螺旋桨非定常推力脉动已达到较高精度,为船舶螺旋桨低频线谱噪声的预报提供了物理基础和重要参数。      

多级轴流压气机间隙流动数值模拟

本文对某亚音轴流压气机的中间三排叶片进行定常与非定常数值模拟,分析在不同的动叶叶顶间隙和静叶气封间隙组合下压气机的流动特性。计算结果表明:定常计算条件下,叶顶间隙由0．5％叶高增大到2％叶高时,压气机的效率下降1．028％-1．034％,相同的气封间隙变化使效率下降0．108％-0．114％;非定常计算条件下,效率比定常计算高出 1％左右,并且叶顶间隙与气封间隙同时增大1％叶高时,效率下降约1％,与定常计算的规律相同。     

非定常叶顶间隙泄漏流动和换热的数值研究

通过数值方法研究了带叶顶间隙的某一级半透平中的非定常流动和换热问题.数值模拟采用标准k-ω两方程湍流模型,求解非定常雷诺平均N-S方程.动叶顶部间隙取为0.4 mm.分析了动静干涉对动叶顶部间隙内泄漏流动与换热的影响.结果表明,周期性通过的上游静叶尾迹和通道涡足动叶通道中非定常现象的主要来源.流场的波动主要存在于叶顶吸力面侧中间弦长附近.叶顶换热系数波动主要存在于两个位置,一是叶顶吸力面侧,一是叶顶主泄漏通道.叶顶表面面积平均传热系数非定常计算的时均结果与定常计算获得的结果偏差小于2%.     

离心压缩机级内静叶时序效应的数值研究

本文采用三维粘性非定常数值模拟的方法研究了离心压缩机级内静叶的clocking(时序)效应,研究结果表明,当两级静叶相对周向位置改变时最大效率变化为0.175%.另外,通过对非定常计算叶根,叶中和叶尖处流场图的分析,发现非定常环境下上游周期性尾迹对下游叶片边界层、尾迹以及叶尖泄漏流的相互作用.     

TE01-TE11模式转换器的带宽特性

针对模式转换器设计中在相同的中心频点转换效率下模式转换器越短带宽越宽的传统观点,研究发现了最佳长度的存在,即当结构长度大于最佳长度时,带宽随着结构长度增加而减小,当结构长度小于最佳长度时,带宽随着结构长度增加而增加。通过对中心频率35 GHz、半径13.6 mm的TE01-TE11模式转换器进行的验证发现,最佳长度为550 mm,此时带宽达到最大值6.28%。     

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Based on Reynolds similar principles of plasma-induced jet and propeller blade element theory, experiment of propeller blade element wind tunnel was conducted. The effects of constant and unsteady model were compared, effect of different duty cycle and the frequency in unsteady model were studied. The results showed that: at the same voltage, the enhancement of propeller thrust was 9.8% by steady mode, unsteady mode was greater than the steady mode in enhancement of propeller thrust, the enhancement up to 20.4% in unsteady mode. The thrust enhancement of propeller blade elements by plasma was obvious with relative radius between 0.4 and 0.85, in order to improve energy efficiency, plasma actuator could be arranged between blade relative radius of 0.4 and 0.85. At the same frequency, enhancement of propeller thrust increased with duty cycle decreasing, and in duty cycle of 10%, the enhancement was greatest. At the same duty cycle, there existed an optimal frequency, it was 30Hz in which plasma enhanced propeller thrust the most.     

Prediction and validation of tonal noise from underwater propellers

Prediction and validation of low-frequency line spectrum noise from ship propeller under non-cavitating condition is presented.The flow field is analyzed with potential-based panel method,which requires the hydrodynamic forces to be integrated over the actual blade surface,rather than over the mean-chord surface.Then the pressure data is used as the input for Ffowcs Williams-Hawkings formulation to predict the far field acoustics.At the same time,propeller unsteady force is measured in hull-behind condition in China Large Cavitation Channel(CLCC).Line spectrum noise of the 1st blade passage frequency(BPF) of a five-bladed propeller operating in a non-uniform flow field is got according to the calculated and measured unsteady forces,in which good agreement is obtained,and the 1st BPF noise difference is within 3.0 dB.The investigation reveals that prediction precision of the propeller's 1st BPF unsteady force with panel method have reached engineering practical degree,providing significant parameters for prediction of propeller line spectrum noise.     

Instantaneous orifice discharge coefficient of a physical, driven model of the human larynx

The quasisteady approximation is often made in the study of phonatory aerodynamics to facilitate the modeling of time-varying air flows through the self-oscillating vocal folds. The unsteady, pulsating flow is approximated by a sequence of steady flows through representative configurations of the vocal folds at rest. Previous studies have discussed the accuracy of this approximation for a range of orifice geometries, and flow conditions. The purpose of the present study was to further evaluate the quasisteady approximation experimentally using an improved procedure, from a direct comparison between the discharge coefficients of steady jets through fixed orifices and unsteady jets through modulated orifices of identical shape, area, and transglottal pressures at a given time. Life-scale convergent and divergent glottis-shaped rubber orifices were used in a rigid-walled tube and a low Mach number flow representative of human phonation. It was found that the quasisteady approximation is valid during 70% of the duty cycle, when the Reynolds number was above 3000, for a frequency of oscillations of 100 Hz. The steady form of Bernoulli's equation along a streamline, and Bernoulli's flow obstruction theory were found to be reasonably accurate for the unsteady flows. These models break down at low Reynolds numbers, near the beginning and the end of the duty cycle, due to viscous effects and to the influence of flow displaced by the motion of the walls.     

不均匀伴流场中螺旋桨空化的黏性流数值模拟和低频噪声预报

阐述了采用空化黏流CFD瞬态模拟和脉冲球形气泡辐射噪声理论相结合的思路在螺旋桨空化低频噪声谱预报上的应用方法。预报了全附体SUBOFF潜艇标称伴流条件下的NSRDC4383五叶大侧斜桨和某七叶大侧斜桨的片空化低频噪声谱,分析了桨叶负载和空化程度对线谱成分及其谱源级的影响。空化模拟时采用作者提出的且可信性经过验证的改进Sauer空化模型和修正SST湍流模型。噪声谱预报时空化体积由空化特征长度求取,较空泡表面球形等价假设更加合理。计算表明,七叶桨较五叶桨的确具有负载小、空化初生延迟、空化低频线谱噪声低的特征。在相同的基于航速的空化数下,非均匀进流与桨叶相互作用会明显增加线谱成分及其谱源级。在伴流、空化数和转速一定时,随着负载减小,推力、力矩和桨叶空化面积均会减小,但空化体积加速度幅度却变大,离散线谱噪声级增加且由奇次谐频为主转变为以偶次谐频为主;当仅减小空化程度时,谐频线谱成分明显被抑制,且1 kHz频率处谱源级减小2.54 dB。较完整地构建了螺旋桨空化水动力和噪声性能评估的数值平台,可用于指导艇尾低噪声桨的数值设计。      

叶型优化在非定常流动条件下效果的数值分析

本文对叶型优化在非定常流动条件下的效果进行数值研究。叶型优化基于比较成熟的在定常流动条件下的反问题解法，非定常流动则考虑到动静叶栅之间的相互作用，非定常流动的求解在Ｎ－Ｓ方程的基础上采用分区计算的方法来完成。数值计算的结果表明，定常流动条件下优化得到的叶型在非定常流动条件下同样具有较好的气动性能。     

Low temperature ITO thin film deposition on PES substrate using pulse magnetron sputtering

Experiments were conducted using pulse magnetron sputtering (PMS) to deposit transparent conducting indium tin oxide (ITO) thin film onto flexible polyethersulfone (PES) plastic substrates. The thin film microstructure, optoelectronic and residual stress were analyzed using the modulating PMS power, work pressure, pulse frequency, duty cycle and cycle time process parameters. The residual stress of the thin film was determined by scanning electron microscopy (SEM) combined with the Sony equation. The experimental results show that PMS has a lower process temperature, higher deposition rate and lower resistivity compared with the radio frequency process at the same output power. The duty cycle increase produces the optimum optoelectronic characteristics. When the pressure, power, duty cycle and sputter time are increased, the thin film stress will also increase, causing flexural distortion in the PES plastic substrate. When the deposition thickness reaches 1.5 μm, ITO thin film will appear with a distinct split. Under 5 mtorr work pressure, 60 W power, 33 μs duty time and 2 μs pulse reverse time at duty cycle 95%, thin film with an optimized electrical 3.0 × 10⁻⁴ Ω-cm, RMS surface roughness of 0.85 nm and visible region optical transmittance will be achieved with acquisition of over 85%.     

On vortex–airfoil interaction noise including span-end effects,with application to open-rotor aeroacoustics

A linear analytical model is developed for the chopping of a cylindrical vortex by a flat-plate airfoil, with or without a span-end effect. The major interest is the contribution of the tip–vortex produced by an upstream rotating blade in the rotor–rotor interaction noise mechanism of counter-rotating open rotors. Therefore the interaction is primarily addressed in an annular strip of limited spanwise extent bounding the impinged blade segment, and the unwrapped strip is described in Cartesian coordinates. The study also addresses the interaction of a propeller wake with a downstream wing or empennage. Cylindrical vortices are considered, for which the velocity field is expanded in two-dimensional gusts in the reference frame of the airfoil. For each gust the response of the airfoil is derived, first ignoring the effect of the span end, assimilating the airfoil to a rigid flat plate, with or without sweep. The corresponding unsteady lift acts as a distribution of acoustic dipoles, and the radiated sound is obtained from a radiation integral over the actual extent of the airfoil. In the case of tip–vortex interaction noise in CRORs the acoustic signature is determined for vortex trajectories passing beyond, exactly at and below the tip radius of the impinged blade segment, in a reference frame attached to the segment. In a second step the same problem is readdressed accounting for the effect of span end on the aerodynamic response of a blade tip. This is achieved through a composite two-directional Schwarzschild's technique. The modifications of the distributed unsteady lift and of the radiated sound are discussed. The chained source and radiation models provide physical insight into the mechanism of vortex chopping by a blade tip in free field. They allow assessing the acoustic benefit of clipping the rear rotor in a counter-rotating open-rotor architecture.