共查询到17条相似文献,搜索用时 484 毫秒
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为了探寻直排型连续波DF/HF化学激光器的起动特性,建立了一套化学激光器气流通道单喷管小型模型实验装置,通过选用不同的气体(冷气流)作为工作介质和不同的扩压器进行实验,分别研究了工作介质的气动参量对模型起动特性和扩压器喉道最小面积的影响,并与1维定常流理论的计算结果作了比较。最后分析了基区对模型起动特性的影响,比较了两种类型基区的差异。实验结果表明:对于直排型连续波DF/HF化学激光器,采用大比热容比、小相对分子质量的介质作为引射气流,喷管出口和基区之间带有一个向内的圆角,对提高DDCL整体性能是有利的。 相似文献
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直排型DF/HF化学激光器双喷管模型启动特性 总被引:2,自引:1,他引:1
建立了一套直排型DF/HF化学激光器气流通道双喷管小型实验装置,通过选择不同副气流总压(模拟燃烧室气流)进行实验,研究了副气流总压对双喷管实验装置启动特性的影响。实验结果表明:随着副气流总压的增大,装置的启动压力降低,盲腔条件下的启动压力明显高于有副气流时的启动压力。因此,先通入燃烧室气流,再开通引射气流,对直排型连续波DF/HF化学激光器的启动是有利的。采用1维处理方法,建立了从引射气流喷管入口、副气流喷管入口到扩压器出口的理论模型,得到了与实验一致的规律。由于1维理论中采用了一些近似处理,实际启动压力比理论数据高20%~31%。 相似文献
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为了研究直排型连续波DF/HF化学激光器的启动特性,建立了一套化学激光器气流通道双喷管小型实验模型。以氮和氦作为引射介质,采用两种面积比的引射喷管,进行了启动实验。实验表明,当以氮作为引射介质,采用大面积比的引射喷管进行实验时,实验数据与1维理论计算结果相差很大。分析认为,该次实验中,在引射喷管内剧烈地膨胀后,部分N2已经发生相变,理论计算采用的1维定常流处理法已经不再适用。计算表明,连续波DF/HF化学激光器中的光腔燃料和副稀释剂He不会发生相变,但当以N2作副稀释剂时,副稀释剂喷管面积比不能过大。 相似文献
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建立了DF化学激光器压力恢复系统扩压器的流场仿真模型,对扩压器流场结构进行了仿真分析。结果显示,扩压器超扩段长度为1310 mm时,激光器可工作压力为7.18 kPa。增加超扩段长度至1810 mm,激光器的可工作压力上升至8.25 kPa; 插入2片楔形叶片,激光器的可工作压力提升至8.52 kPa。适当增加超扩段长度和插入叶片的方式可在一定范围内提高激光器的工作压力,研究结果对于化学激光器扩压器的设计与优化具有重要的参考价值。 相似文献
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为了研究直排型扩压器的压力恢复能力,设计了一套可模拟不同背压环境的扩压器装置。在扩压器平直段后接入电动闸板阀,通过调节气流的流通面积模拟不同的背压环境。考虑到闸板阀前平直段对扩压器工作性能的影响,建立了扩压器流场的仿真分析模型,得到了加入闸板阀的扩压器装置的流场,进行了扩压器平直段的优化设计,并开展了验证试验。结果表明,仿真分析与实验结果符合得较好,平直段设计合理时,采用闸板阀模拟不同背压环境的方式是可行的,直排型扩压器的恢复压力测试结果稳定可靠。 相似文献
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氧碘化学激光器(COIL)在化学反应条件下,由于光腔及扩压器的气流通道内存在残余化学反应放热,从而导致"热堵"现象发生,影响了扩压器的正常启动及光腔内超声速流场的流动品质。采用数值模拟方法对COIL光腔与超声速扩压器流道内的化学反应流场进行研究,对超声速扩压器插入段的长度、楔形体的数量级扩散段长度对化学反应流场的影响进行研究。数值模拟结果表明:通过优化插入段及楔形体长度、取消扩压器侧壁的半楔形体,改善了因化学反应放热对光腔及扩压器流场造成的不利影响。优化后,光腔内的流动不再受气流分离产生的斜激波的影响,扩压器二喉道内的分离现象消失,扩压器壁面的分离区减小,出口流动更加均匀,"热堵塞"现象消失。化学反应条件下的气流总压损失比冷流时提高约15%,光腔与扩压器的总压恢复系数为0.426,进出口的静压比为3.75,比优化前提高了约25%。 相似文献
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扩压室对喷射器内混合流体的降速增压有着重要影响。本文基于真实流体物性,采用气体动力学方法建立改进的一维混合模型并提出扩压室结构设计优化方法。将模型计算结果与文献实验值对比验证了模型的准确性。分析了扩压室结构参数与喷射器膨胀比、喷嘴喉部直径和混合室直径之间的关系。结果表明,扩压室半锥角α随膨胀比pg/pe、扩压室出口直径与混合室出口直径之比dc/dc3以及喷嘴喉部直径与混合室直径之比dg0/dc3的增大而减小;扩压室长度Ld随膨胀比pg/pe、直径比dc/dc3及喷嘴喉部直径dg0的增大而增大,而随着混合室直径dc3的增大而减小或近似保持不变。 相似文献
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F. Falempin M. A. Goldfeld Yu. V. Semenova A. V. Starov K. Yu. Timofeev 《Thermophysics and Aeromechanics》2008,15(1):1-9
An experimental study of different control methods for hypersonic air inlets aimed at ensuring reliable starting of these
apparatuses and improving their operating characteristics in the range of Mach numbers 2 to 8 is reported. Conditions for
boundary-layer separation and possibilities for preventing this separation by using modified diffuser configurations and/or
perforation bleedage are examined. An air-inlet model was tested for operation in an intermittent wind tunnel and in a blow-down
wind tunnel respectively in the Mach-number ranges 2 to 6 and 5 to 8. Distributions of static and total air pressures on the
walls of the model and in several cross sections were measured, together with air flow coefficients and total-pressure recovery
coefficients. Perforation bleedage is shown to offer an efficient means to facilitate air-inlet starting. Perforation bleed
has enabled a more than two-fold increase in the air flow coefficient on the model with sidewalls. A perforation-bleed panel
installed closer to the air-inlet throat proved to be more efficient. The possibility of sudden starting of the air-inlet
apparatus was checked in the intermittent wind tunnel; it was shown that, here, sudden starting could be realized. The data
obtained in the intermittent wind tunnel proved to be consistent with data obtained in the blow-down wind tunnel with up to
150-ms blowdown time.
This work was supported by the International Scientific and Engineering Center (Contract No. 887) and by MBDA, France. 相似文献
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The results of the numerical modeling of a flow with a pseudo-shock in an axisymmetric duct are presented. The duct included a frontal inlet with the initial funnel-shaped compression part and the cylindrical throat part as well as the subsequent expanding diffuser. To create a flow with a pseudo-shock, the duct was throttled with the use of the outlet converging insert. Numerical computations of the axisymmetric flow have been conducted on the basis of the solution of the Reynolds-averaged Navier?Stokes equations and with the use of the k-ω SST turbulence model. As a result of computations, such parameters of the flow were determined as the location of the beginning of the pseudo-shock, the length of its supersonic part, the velocity profiles in different cross sections of the pseudo-shock, the pressure distribution on the duct wall, the total pressure recovery factor, and others. The behavior of these parameters at the freestream Mach number М = 6 was analyzed versus the diffuser opening angle and different degree of the inlet duct throttling. 相似文献
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In the present paper, we discuss results of an experimental study of performance characteristics of a 3D inlet with a flow-metering device at free-stream Mach numbers M = 1.75 and 2. The inlet was designed using gas-dynamic design methods. The initial external compression in the inlet is achieved using a V-shaped body called a waverider. The inlet is provided with a special device for its starting, also permitting regulation of the internal channel cross-sectional area in the throat region with the help of paired rotary panels, throat doors. The flow-rate and total-pressure loss characteristics in the throat of the model inlet were determined as functions of the degree of opening of the throat doors. 相似文献
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研究了不同几何外形参数对直线分段扩开型氧碘化学激光器(COIL)扩压器性能的影响,实验结果表明:光腔上下壁扩开全角8°时,选取4°超扩段扩散角可获得较好的压力恢复和隔离光腔流场的能力;超扩段增加2 mm竖隔板可降低光腔后部壁面静压,且截止反压提高约12%;在相同腔压下,10°截角唇口的截止反压比直角唇口和1/4圆弧唇口截止反压高出约7.6%;超扩段入口四壁增加人工粗糙带能明显改善光腔壁面静压的分布,并有效提高扩压器效率。 相似文献
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气泡的存在使无阀微泵的工作性能和使用寿命大大降低, 甚至无法正常工作. 为了合理地预测无阀微泵腔内气泡对周期驱动压力的影响, 给出了用来描述收缩管/扩张管型无阀压电微泵的数学模型, 包括泵腔体积变化、连续性方程、流体有效体积弹性模量以及锥管阻力系数的计算. 同时, 分析了腔内不同气泡体积对无阀微泵周期驱动压力的影响, 并对两个气泡进入无阀微泵泵腔时压力脉动过程进行了仿真和试验研究. 通过仿真结果与试验数据的比较表明, 所提出的存在气泡时无阀微泵数学模型及仿真方法是合理的.
关键词:
无阀微泵
气泡
压力脉动 相似文献