Numerical investigation on properties of attack angle for an opposing jet thermal protection system

The three-dimensional Navier Stokes equation and the k-ε viscous model are used to simulate the attack angle characteristics of a hemisphere nose-tip with an opposing jet thermal protection system in supersonic flow conditions. The numerical method is validated by the relevant experiment. The flow field parameters, aerodynamic forces, and surface heat flux distributions for attack angles of 0°, 2°, 5°, 7°, and 10° are obtained. The detailed numerical results show that the cruise attack angle has a great influence on the flow field parameters, aerodynamic force, and surface heat flux distribution of the supersonic vehicle nose-tip with an opposing jet thermal protection system. When the attack angle reaches 10°, the heat flux on the windward generatrix is close to the maximal heat flux on the wall surface of the nose-tip without thermal protection system, thus the thermal protection has failed.

逆向射流对高超声速升力体构型的减阻特性研究

在高超声速飞行过程中,飞行器往往会面临巨大的阻力,严重限制了其飞行性能,并增加了飞行器表面的热负荷和材料应力。针对这一问题,通过数值模拟系统地分析了射流孔数量、位置和攻角对升力体减阻性能的影响。研究结果表明,随着射流孔数量的增加,整体减阻率显著提高,有效降低了升力体头部的高压区域,但也导致四周流场的不稳定性增强。射流孔位置对激波脱体距离和“气膜”厚度具有重要影响。此外,增大攻角会导致整体减阻率下降,但对局部减阻率影响较小,同时会增加上下壁面之间的压差。进一步比较研究发现,在20 km和55 km高空条件下,这3种因素对减阻性能的影响规律保持一致。研究结果为设计高效减阻方案提供了重要参考。

反向射流作用下可回收火箭升阻特性

可回收火箭动力减速过程中反向射流将大幅改变箭体气动特性,为获得反向射流对箭体气动特性的影响,利用数值模拟方法获得箭体升阻力系数,分析升阻特性变化规律并提出升阻特性表征参数。首先,对反向射流钝体构型进行数值模拟,将得到的结果与已公开的实验数据进行对比,验证了数值模拟方法的有效性。其次,采用RANS方法模拟了单喷管构型火箭多种典型飞行状态,得到箭体升阻力系数随迎角变化曲线以及升阻特性变化规律,通过对回流区内流动状态进行分析得到升阻特性改变的机理。最后,由反向射流对箭体气动特性影响程度提出表征参数。结果表明:反向射流会对箭体形成遮挡作用并影响箭体升阻力特性。有射流时升阻力特性受飞行高度影响较大,受飞行马赫数影响较小,与无射流时的规律恰好相反。大部分飞行工况下阻力系数小于0.1,部分高空飞行工况将出现负阻力。本研究提出以反向射流与箭体宽度比作为气动特性表征参数,可以较好地反映反向射流对箭体的遮挡作用并表征箭体在反向射流作用下的气动特性变化规律。

不同迎角下逆向喷流减阻降热特性研究

文章采用基于SST k-ω湍流模型的N-S(Navier-Stokes)方程数值模拟方法,探究不同来流迎角下,逆向喷流与钝头体同轴及不同轴时,同自由来流相互作用产生的干扰流场对减阻降热效果的影响。结果表明:与无喷流情况相比,同轴逆向喷流能有效减小钝头体的阻力系数,迎角为2°时阻力系数可减小32.53%;迎角较小时,同轴逆向喷流可有效减小壁面斯坦顿数,迎角较大时,迎风面壁面斯坦顿数较大,背风面壁面斯坦顿数大幅减小;逆向喷流与钝头体轴向夹角的变化对流场及减阻降热效果产生影响,喷流与轴线夹角增大,迎风面壁面压强逐渐减小,存在使壁面斯坦顿数峰值取得最优解的喷流角度;较同轴逆向喷流,来流迎角为5°时,壁面斯坦顿数峰值可减小9.02%,来流迎角为8°时,减阻效果最高可提升1.92%。

逆向喷流对可回收火箭气动特性的影响研究

可回收火箭返回时,需要依靠发动机进行点火减速制动,为得到逆向喷流条件下箭体气动性能的变化规律,通过对低空和高空两次点火过程进行数值仿真,分析来流马赫数和攻角对箭体气动性能的影响,同时开展单喷管、多喷管喷流条件下的仿真研究。结果表明,低空状态,逆向喷流会导致全箭轴向力系数绝对值减小,且喷流数目越多,轴向力系数绝对值越小。小攻角条件下,逆向喷流会引起全箭压心大幅前移,随着开机台数增加,压心前移越多。高空条件下,喷流膨胀区和来流存在强烈的相互干扰,导致轴向力系数减小明显,其绝对值在0.04以内,0°~10°攻角内箭体法向力系数绝对值小于0.1,随着来流静压增加,法向力系数绝对值小于0.1的攻角区间减小。

稀薄流高超声速钝化前缘逆向射流流场特征研究

为准确预测稀薄过渡区逆向射流对稀薄大气的干扰流动特征,本文采用直接蒙特卡洛算法(DSMC),在自由流马赫数为7的情况下,对稀薄流中逆向射流干扰下的高超声速流动进行了数值模拟。计算中考虑了60~90 km高度的典型大气环境,研究了压比和自由流克努森数对压力、剪切力和热流密度的影响规律。结果表明,逆向射流改变了流场结构,且具有明显的热防护性能,但减阻效果不明显。逆向射流对高超声速稀薄来流的影响随压比的增加明显增强,形成的马赫盘大小也随之增加。高度的增加伴随稀薄效应不断增强,自由流克努森数增大,导致弓形激波厚度随高度增加而增加,壁面处的回流区范围不断减小至消失。这项研究初步揭示了稀薄流中逆向射流/高超声速流动相互作用的机制。

Effect of CO_(2) Opposing Multiple Jets on Thermoacoustic Instability and NO_(x) Emissions in a Lean-Premixed Model Combustor

This paper experimentally studied the effect of CO_(2) opposing multiple jets on the thermoacoustic instability and NO_(x) emissions in a lean-premixed model combustor.The feasibility was verified from three variables:the CO_(2) jet flow rate,hole numbers,and hole diameters of the nozzles.Results indicate that the control effect of thermoacoustic instability and NO_x emissions show a reverse trend with the increase of open area ratio on the whole,and the optimal jet flow rate range is 1-4 L/min with CO_(2) opposing multiple jets.In this flow rate range,the amplitude and frequency of the dynamic pressure and heat release signals CH~* basically decrease as the CO_(2) flow rate increases,which avoids high-frequency and high-amplitude thermoacoustic instability.The amplitude-damped ratio of dynamic pressure and CH*can reach as high as 98.75% and 93.64% with an optimal open area ratio of 3.72%.NO_(x) emissions also decrease as the jet flow rate increases,and the maximum suppression ratio can reach 68.14%.Besides,the flame shape changes from a steep inverted "V" to a more flat "M",and the flame length will become shorter with CO_(2) opposing multiple jets.This research achieved the synchronous control of thermoacoustic instability and NO_(x) emissions,which could be a design reference for constructing a safer and cleaner combustor.

Study of premixed flame stabilization by using opposed jet

A preliminary study on the criterion for opposed jet flame stabilization is reported. The experimental investigation consists of the measurement of flame blowoff by means of premixed lean liquefied petroleum gas and the temperature distribution. The criterion for flame stabilization has been obtained. It is correlated with main stream velocity VPm, mass flux ratio of jet to main streamF, internal diameter of jet nozzled; and equivalent ratio of fuel-air ?. The stabilization character of opposed jet flame is described as a well-stirred reactor, and the critical zone acts as a strong ignition source to maintain flame stabilization. A criterion for flame stabilization by theoretical analyses is in good accordance with experimental results.

逆向射流流场建立瞬态过程

为研究高超声速来流下逆向射流流场建立过程及其瞬态特性,基于非定常Reynolds平均Navier-Stokes(unsteady Reynolds-averaged Navier-Stokes,URANS)方程,采用高精度数值格式编制了一套适用于高超声速复杂流动的计算程序。首先,利用经典实验验证了计算程序对包含激波干扰非定常流场模拟的可靠性。随后,深入研究了逆向射流开启后射流流场的建立过程。计算结果表明:仿真结果清晰再现了逆向射流流场建立过程及流场波系演化特征,整个流场波系结构变化非常剧烈,钝体壁面压力和热流急剧变化,气动阻力先是迅速降低至最小值,随后小幅上升至稳定值。此外,逆向射流总压比升高,气动阻力下降后将经历更为剧烈的波动才趋于稳定。

Analysis of Cold Flowfield of Multi-Annular Opposed Jets

The technique of the use of multi-annular opposed jets as different from using swirl and bluff body creates an excellent recirculation zone with desired size in a large space.The size of recirculation,the magnitude of reverse velocity and turbulence intensity are much greater than those formed by bluff body.Factors affecting the flowfield include the velocity ratio of the opposed jets to the primary air J,the diameter and construction of the opposed jet ring,secondary air velocity and configuration,and confined or unconfined flow condition and so on.This method is a promising way for flame stabilization in combustion technology.

Assessing stress conditions and impact velocities in fluidized bed opposed jet mills

Fluidized bed opposed jet mills are capable of meeting the continuously growing dema nd for contamination-free fine particles.In this type of jet mill,the solid material is entrained and accelerated by expanding gas jets that are focused onto a focal point in side a fluidized bed.The resulting particle collisions induce breakage.The process is affected by the relative particle velocities and the number of particle-particle collisions.Clearly,both quantities are distributed.However,to date,neither relative particle velocities nor collision frequencies in such units have been determined.The present work introduces an innovative method to assess the stressing conditions in jet mills experimentally.To this end,mixtures of glass and ductile metal microspheres were used,with the latter employed in small amounts.Inter-particle collisions between the aluminum and glass spheres lead to the formation of dents on the microparticles.The size and number of these dents are associated with the individual collision velocities and overall collision frequencies.The correlation between dent size and collision velocity was obtained from finite element calculations based on empirical data.The proposed approach was validated using particle image velocimetry during secondary gas injection into a fluidized bed reactor.In this case the effect of the distance between two opposed nozzles was examined.For a lab-scaled fluidized bed opposed jet mill the effects of gas pressure and hold-up were investigated.Relative particle velocities were found to be sign ificantly lower tha n the gas velocities,while the nu mber of contacts per particle was determined to be extremely high.

四喷嘴对置式撞击流的数值模拟

通过实验测量和数值模拟(Realizableκ-ε湍流模型)相结合的方法研究了四喷嘴对置式撞击流的流场,得到了两者相吻合的结果。模拟结果再现了装置内的分区流动情况;通过对模拟数据分析,计算出了回流比沿装置轴向的分布,发现喷嘴顶部高度和喷口速度的大小对顶部空间的回流比分布影响明显;而喷嘴顶部高度和喷口速度对喷嘴以下空间的回流比分布影响甚小,大约距喷嘴2倍装置直径距离后喷嘴以下空间回流消失。

应用蒸汽相变脱除燃煤湿法脱硫净烟气中细颗粒物

以经石灰石/石膏法脱硫后的高湿烟气为对象,采用撞击流结构蒸汽相变室,试验研究了烟气相对湿度、蒸汽添加位置及添加量、烟气对喷水平间距、喷雾聚并等对细颗粒脱除效率的影响规律,并与普通蒸汽相变室进行了比较。结果表明:采用撞击流结构相变室,细颗粒脱除效果明显优于普通蒸汽相变室,在蒸汽添加量为0.04 kg.m-3时,数浓度脱除率可由普通相变室的35%增至65%左右;细颗粒脱除效率随烟气对喷水平间距增大先提高后降低,随烟气相对湿度增大而提高,随蒸汽添加量增加先增大后趋于稳定;最佳蒸汽添加位置是在烟气撞击区上游;相变室中喷入雾化水对细颗粒物脱除效果影响不明显。

超细高长径比硅灰石制备技术研究

对制备超细高长径比硅灰石的研究从破碎阶段开始就注重对其针状晶体的保护 ,采用长腔颚式破碎 ,使破碎作用于硅灰石矿物上的力分别以挤压力和摩擦力为主 ,避免过粉碎 ,可有效地保护粗颗粒硅灰石的针状晶体结构。采用多种超细粉碎设备对硅灰石进行超细粉碎 ,结果表明 ,QLM Ⅳ型流化床式气流粉碎系统在磨腔工质压力为 0 . 7～ 0 . 8MPa,轴承防护气体压力为 0 . 2 0MPa、清洗气体工作压力为0 .15MPa、分级轮转速 2 0 0 0r/min的工艺条件下 ,粉碎产品平均粒度为 5 . 60 μm ,长径 /短径高达 16 .17。

两喷嘴对置撞击流径向射流流动特征

对喷嘴间距与喷嘴直径比为0.5～100范围内两喷嘴对置撞击流径向射流的湍流脉动特征、速度分布和扩展率等进行了实验研究和数值模拟。研究结果表明,撞击流径向射流明显较自由射流湍动强烈;从驻点开始径向射流速度逐渐增大到最大值后开始衰减,射流呈现自相似性;随着喷嘴间距增大,撞击流径向射流的扩展率呈现增大的趋势,大约为自由圆射流的1.5～3倍。采用CFD软件对撞击流径向射流的速度分布特征进行了数值模拟,与实验结果相比,两方程湍流模型预报的撞击流径向射流的扩展率明显偏小,雷诺应力模型的预报精度有较大改进。

流化床对撞式气流粉碎制备SiC超微粉

采用流化床对撞式气流粉碎 (QLM 80K)对工业用SiC粉体进行超微化处理 ,考察了工作压力对超微化的影响 ;并采用激光粒度分布仪、扫描电镜、XRD对超微化前后的SiC粉体进行粒度、形貌及结构的研究。研究结果表明 :工作压力愈高 ,SiC粉体的超微化效果愈明显。工作压力为 0 6MPa时 ,超微化前后SiC粉体的平均粒径由 3 0 1μm降至 0 75 μm ,粒径小于 2 5 μm的比例由 82 86 %升至 99 85 % ,粒径主要分布由 0 4～ 1 5 μm和 8～2 3μm的双峰分布变为 0 4～ 1 2 μm的单峰分布 ,分布宽度从 2 5 12 5降到 0 833;颗粒主要以片状、小块状存在 ,分布均匀 ,超微化前存在的大块状颗粒基本消失 ,团聚现象明显减少 ;超微化前后SiC粉体的晶型都属于α SiC(6H) ,超微化后各主要衍射峰的强度减弱。

小间距两喷嘴对置撞击流流场的数值模拟与实验研究

Experimental study and numerical simulation were performed for the averaged flow field of two closely spaced opposed jets with hot wire anemometer(HWA)and CFD software and the simulation was compared with the measurement and approximate analytic solution in the literature.The results showed that the exit velocity profile of the single jet was top-hat distribution due to the presence of boundary layers.At L<2D(where L is nozzle separation and D is nozzle diameter),bimodal distribution of exit velocity profile,low in the middle and high on both sides,was present,while such bimodal distribution of exit velocity profile was absent at L=2D.With increasing nozzle separation,the stagnation point offset of the impinging plane increased.With the same velocity ratio,stagnation point offset of the nozzles with uniform profiles was larger than that with top-hat profiles.The approximate analytic solution of the flow field of two opposed jets in the literature was only valid for the nozzles with uniform exit velocity profiles and the prediction accuracy became worse for the nozzles with top-hat exit velocity profiles.

同轴对称撞击流中的颗粒运动行为

采用高速相机对同轴对称撞击流中颗粒运动行为进行了实验研究,采用图像处理软件对获得的图片进行分析处理,得到了颗粒在同轴对称撞击流中的运动轨迹、运动速度、最大渗入距离和旋转速度等参数。考察了喷嘴出口气速、颗粒大小、颗粒出口速度以及喷嘴间距对颗粒运动行为的影响。结果表明:颗粒在同轴对称撞击流中的运动有直接射出模式和振荡模式,其中振荡模式占70%;出口气速的增加使颗粒轴线速度和旋转速度变大;随着颗粒相对出口速度、颗粒Stokes数和喷嘴间距的增加,颗粒的最大渗入距离变大。

平面撞击流振荡特性

The oscillation characteristics of two planar opposed jets were studied by using high-speed camera,smoke wire visualization and hot-wire anemometry(HWA).The oscillation periods of two planar opposed jets at different nozzle separations and exit nozzle velocities were studied.The results showed two models of instabilities:streamwise quasi-periodic oscillation model and deflection oscillation model.The oscillation model was mainly streamwise quasi-periodic oscillation model at L<5H(where L was the nozzle separation and H was the nozzle slot height),and it was mainly deflection oscillation model at L>5H.The deflection oscillation model had a stable period which decreased with increasing normalized nozzle separation.

高超声速逆向喷流数值模拟和风洞试验

作为一种主动流动控制技术,逆向喷流因其在降低气动热方面的广阔前景而成为研究热点。为探索逆向喷流流动控制技术对高超声速飞行器降热的影响规律及相关机理,对半球体钝体模型进行了不同来流和喷流条件下的数值模拟和风洞试验研究,得到了模型表面的流场和斯坦顿数分布,并对数值模拟和风洞试验结果进行了相互校验。结果表明:逆向喷流产生的降热效果是喷流气体回流和喷流推离头部脱体激波共同作用的结果;在相同来流马赫数下,逆向喷流降热效果随喷流压比的增大而更加显著;在相近喷流压比条件下,来流马赫数越大,逆向喷流降热效果越好。