环形HYLTE喷管叶片的简化设计及加工方法

在不影响喷管性能的前提下,将环形HYLTE喷管叶片分解为4个1/4圆环,经过进一步简化设计后,得到只有3个截面中心共面的内部管道的1/4环形叶片。提出了两种环形HYLTE喷管叶片的加工方法：真空钎焊的方法和嵌铸的方法,并对两种方法进行了比较。对于真空钎焊的方法,进行了验证加工,测试结果表明喷管叶片焊接处气密性良好,力学性能优良,可在较高温度下正常工作。嵌铸的方法在一体化加工方面优势明显,可作为环形喷管加工的备选方法。     

喷管、光腔及压力恢复系统一体化设计

对氧碘化学激光（COIL）系统的喷管和扩压器进行了3维数值模拟,对比分析了几种喷管和扩压器的设计方案,计算了从光腔入口到扩压器出口的气动力学过程。光腔内主副气流借助翼片辅助方法实现充分混合,翼片长0.77 cm,宽0.254 cm,满足气流混合要求。扩压器是1/4结构,即计算区域为入口截面高30 mm、宽60 mm的长方型,之后等截面延续500 mm,然后宽度仍然不变,高度以4°角扩张,延续700 mm,最终的出口截面高度为79 mm。采用空气入射,入口处（光腔出口）马赫数3.2,静压1 232 Pa,温度110 K;计算得到出口处总压13 300 Pa,总温300 K。结果表明：出口静压超出入口静压近10倍,该扩压器很好地起到了压力恢复的作用,而总压下降到1/4.5左右（从60 648 Pa到13 300 Pa）,从而能够减轻后续的引射器的工作压力。利用高光腔压力设计可以减少一级引射器,达到整个系统小型化设计的目的。     

线性喷管构形对激光推力器冲量耦合系数的影响

喷管是激光推力器的重要组成部分。在设计喷管构形时,可以使其与聚光系统一体化设计,也可以把聚光系统和喷管分离设计。针对聚光系统与喷管分离设计的工作模式,建立了一种辅助聚焦系统的点火模型。通过改变喷管的构形,分析了圆锥形、圆台形喷管的冲量耦合系数与喷管顶部直径与出口直径之比以及喷管长度与出口直径之比之间的关系。通过对推力曲线的分析,阐述了喷管结构参数对其性能影响的原因。研究结果显示,圆台形喷管的推进性能优于圆锥形和圆筒形。     

氟化氢泛频化学激光器高超音速低温喷管研究

通过建立一套氟化氢泛频化学激光器实验系统,介绍了一种新型高超音速低温喷管的结构及其实验参数设置方法;对喷管性能进行了测试,并将实验结果同数值模拟结果进行对比,找出了改善喷管性能的方法。由该喷管构成的激光系统已顺利出光。     

副气流中He流量变化对流场混合状态的影响

在保持主气流流量和副气流中I2的流量不变的条件下,改变副气流中He的流量,数值模拟氧碘化学激光器拉伐尔喷管内的流场混合特性。结果表明,随着副气流中He的流量的增加,副气流垂直穿透主气流的深度逐渐变大,主、副气流混合状态也逐渐变好,直至氧碘气流混合均匀。     

Numerical study of hysteresis in annular swirling jets with a stepped‐conical nozzle

This study investigates the experimentally observed hysteresis in the mean flow field of an annular swirling jet with a stepped‐conical nozzle. The flow is simulated using the Reynolds‐averaged Navier–Stokes (RANS) approach for incompressible flow with a k–ε and a Reynolds stress transport (RSTM) turbulence model. Four different flow structures are observed depending on the swirl number: ‘closed jet flow’, ‘open jet flow low swirl’, ‘open jet flow high swirl’ and ‘coanda jet flow’. These flow patterns change with varying swirl number and hysteresis at low and intermediate swirl numbers is revealed when increasing and subsequently decreasing the swirl. The influence of the inlet velocity profile on the transitional swirl numbers is investigated. When comparing computational fluid dynamics with experiments, the results show that both turbulence models predict the four different flow structures and the associated hysteresis and multiple solutions at low and intermediate swirl numbers. Therefore, a good agreement exists between experiments and numerics. Copyright © 2006 John Wiley & Sons, Ltd.     

Simulation of the starting flow in a wedge–like nozzle

The starting process of the flow in a wedge-like expansion nozzle of a shock tunnel is simulated by an unsplit 2-D GRP scheme on an unstructured grid. The scheme is briefly outlined and results are presented and discussed in comparison to the experimental (shadowgraph) findings obtained by Amann. The simulated pattern of reflected and transmitted shock waves in the nozzle inlet region and inside the nozzle is found to agree well with the experimental data. Received 5 April 1996 / Accepted 16 June 1997     

Experimental evaluation of side-loads in LE-7A prototype engine nozzle

During development tests of the LE-7A prototype engine, severe side-loads were observed. The side-load peaks appeared only in certain limited conditions during start-up and shut-down transients. To investigate phenomena causing those severe side-loads observed in the LE-7A prototype engine nozzle, series of cold-flow tests and hot-firing tests as well as CFD analyses were conducted. As a result of the hot-firing tests, two different phenomena were found to cause severe side-loads in the LE-7A prototype engine nozzle. One was a restricted shock separation (RSS) flow structure and the other was a phenomenon termed “separation jump,” the rapid movement of the separation location in the vicinity of the step. A step was installed in the LE-7A prototype to supply film-cooling gas. Hot-firing test results showed that RSS can occur for a limited mixture ratio. Detailed flow structure of RSS on the nozzle surface was revealed by the cold-flow tests. Measured pressures and visualized images of cold-flow tests clarified the mechanism causing the separation jump. The key phenomenon ruling the separation jump was found to be the base flow behind the step. Based on the results of the present study, the latest LE-7A engine nozzle design has been changed to eliminate the severe side-load.

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Synchronization in a fractional-order dynamic network with uncertain parameters using an adaptive control strategy

This paper studies synchronization of all nodes in a fractional-order complex dynamic network. An adaptive control strategy for synchronizing a dynamic network is proposed. Based on the Lyapunov stability theory, this paper shows that tracking errors of all nodes in a fractional-order complex network converge to zero. This simple yet practical scheme can be used in many networks such as small-world networks and scale-free networks. Unlike the existing methods which assume the coupling configuration among the nodes of the network with diffusivity, symmetry, balance, or irreducibility, in this case, these assumptions are unnecessary, and the proposed adaptive strategy is more feasible. Two examples are presented to illustrate effectiveness of the proposed method.     

Large eddy simulation of serration effects on an ultra-high-bypass-ratio engine exhaust jet

Serrated jet nozzles are considered to be an efficient and practical passive control approach for jet noise. However, some fundamental mechanisms of serration effects on jet noise are not fully understood, especially in terms of the sound source. In this paper, a high-fidelity simulation framework using large-eddy simulation (LES) is demonstrated to predict near-field turbulence and far-field acoustics from an ultra-high-bypass-ratio engine with round and serrated nozzles. Far-field sound is predicted using Ffowcs Willams–Hawkings (FWH) integration. The results show that the serrated nozzle increases mixing near the nozzle and hence the turbulence decay rate, reducing the turbulence level downstream. The serrations shift the energy from the low frequencies to the high frequencies and decrease overall sound pressure levels by about 3 dB over the low-frequency range. Sound sources are analysed based on fourth-order space–time correlations. There are six major source components ($R_{1111}$, $R_{2222}$, $R_{3333}$, $R_{1313}$, $R_{1212}$, and $R_{2323}$) inside the jet shear layers. The serrations are able to reduce the amplitude of these source terms, causing them to decay rapidly to a level below the round nozzle jet within 2D downstream of the nozzle.