Vortex structures downstream a lobed nozzle/mixer

An experimental study was conducted to investigate the evolutions of unsteady vortex structures downstream a lobed mixer/nozzle.A novel dual-plane stereoscopic PIV system was used to measure all 3-components of vorticity distributions to revealed both the large-scale streamwise vortices produced by the lobed mixer/nozzle and the Kelvin-Helmholtz vortex structures generated due to the Kelvin-Helmholtz instabilities simultaneously and quantitatively for the first time.The instantaneous and the ensemble-averaged vorticity distributions displayed quite different aspects about the evolutions of the unsteady vortex structures.While the ensemble-averaged vorticity distributions indicated the overall effect of the special geometry of the lobed nozzle/mixer on the enhanced mixing process,the instantaneous vorticity distributions elucidated many details about how the enhanced mixing process was conducted.In addition to quantitatively confirming conjectures of previous studies,further insight about the formation,evolution and interaction characteristics of the unsteady vortex structures downstream of the lobed mixer/nozzle were also uncovered quantitatively in the present study.

Study on Combustion Performance of the Radial Staged Combustion Chamber with Lobed Nozzles

In order to investigate the effect of the radial gradation of the lobed nozzles on the flow field organization,a cold water model experimental platform for a combustion chamber with radial⁃staged 13-point lobed nozzles is built.Compared with a series of combustion OH*luminescence experiments tested by the University of Cincinnati,the four corresponding working conditions of no load,partial load,cruise and take off are selected.The vortex structure,vorticity value,multi-combustion materiel field and combustion characteristics of the flow field in the radial staged combustion chamber of the lobed nozzles under the equivalence ratio,the fuel injection method,the fuel injection ratio and other factors are numerically studied.The results show that under different influencing factors,the varation trend of the hydroxyl flame field of the lobe combustion chamber is basically the same as that of the hydroxyl light emission experiment of the swirl combustion chamber,but the flame field shape is quite different.The local equivalent ratio has a greater influence on the relevant combustion performance of the combustion chamber.Under the conditions of lower equivalence ratio,three-stage air and fuel injection mode,and gradually transferring the fuel flow of the pilot circuit to the external circuit,the temperature field and flame field of the combustion chamber are more evenly distributed,the outlet temperature field quality is better,the combustion efficiency is higher,and the NO_(X) emission is relatively low.These are basically consistent with the cold test results.The cold experimental results illustrate the importance of the influence of the flow field organization on the combustion organization and verify the reliability of the calculation results.

NUMERICAL INVESTIGATION OF AERODYNAMIC AND MIXING CHARACTERISTICS OF SCARFED LOBED MIXER FOR TURBOFAN ENGINE EXHAUST SYSTEM

The flow field and aerodynamic performances for the scarfed lobed forced mixer are studied based on a computational fluid dynamics（CFD） technique. A series of computations are conducted to obtain the effects of the bypass ratio and the scarf angle on the mixing performance for the scarfed lobed mixer. Results show that the scarfed lobed mixer is reduced in the system weight. Meanwhile, aerodynamic performances are slightly improved compared with the normal lobed mixer. Two reasons for causing the mixing enhancement between the core and the bypass flow are as follows： （1） The stream-wise vortices shed from the training edge of the half/full scarfed lobed mixer earlier is enhanced by about 25%. （2） The mixing augmentation is also associated with the increase of the interface length caused by scarfing. The thermal mixing efficiency is enhanced with the increase of the bypass ratio and the scarfing angle. The scarfed lobed mixer design has no negative effects on the pressure loss. The total pressure recovery coefficient reaches above 0. 935 in various bypass ratios and scarfed angles. As the bypass ratio increases, the total pressure recovery coefficient also increases for the scarfed lobed mixer.

Computation and Validation of Parameter Effects on Lobed Mixer-Ejector Performances

Three-dimensional numerical computation of the flow fields and pumping performances for the lobed mixer-ejector are conducted using full Navier-Stokes equations. In the computation, the inlet of the primary flow uses the mass flowrate boundary condition. The inlet of the second flow and the outlet of the mixing flow use the pressure boundary condition. Compared with the relative experimental resuits, it is shown that the present calculation is reasonable. And a series of numerical studies is performed to obtain the effects of area ratio and length-to-diameter ratio of mixing duct on pumping coefficient and thermal mixing efficiency of a lobed mixer-ejector.

Effect of Swirl Preset Vorticity on Combustion Performance of Lobe Nozzle Combustor Chamber

To improve the combustor performance of multi-point injection combustion,lobe nozzle design was applied to the aero-engine model combustor,by presetting the swirl through a certain twisted angle of the edge of the lobe outlet.Numerical simulation in combination with modelling test is used in this paper.The effects of swirl vorticity presetting onto the vortex structure,the characteristics of combustion temperature field,the combustor exit temperature field quality,the combustion efficiency,and the NOx emissions of multi-point injection combustion chamber are investigated.Compared with the conventional vortex flow at the lobe outlet edge,the results of numerical simulation and water modelling test of the swirl vorticity presetting show that the swirl presetting can efficiently enhance the range and intensity of the lobe-induced vorticities.Besides,it can improve the uniformity of the combustion temperature in the combustor chamber,together with the reduced emissions of the pollutant NOx.Moreover,compared with the conventional lobe nozzle chamber,the swirl vortex presetting can effectively improve its combustion performance.The flow simulation test results demonstrate the fluid vortex structure in the combustion chamber and validate the simulation results.

一体化红外抑制器排气出流对其气动和红外辐射特性的影响

经地面模型实验验证,数值仿真展示了一体化红外抑制器排气出流、模拟旋翼下洗气流和模拟前飞来流相互作用下的流动和换热特征,通过改变排气出流角度和模拟前飞来流速度,计算分析一体化红外抑制器引射、混合特性以及红外辐射强度空间分布的变化规律。仿真结果表明:模拟的前飞来流与排气出流相互作用后会造成局部排气不畅,前飞来流甚至倒灌入红外抑制器内,从而引起抑制器壁面局部高温,增加了抑制器整体红外辐射强度;改变排气角度可将之改善,且存在气动和红外辐射特性兼顾的最佳角度。前飞来流速度从15 m/s提高到55 m/s,抑制器内部高温壁面温度降低,抑制器红外辐射强度峰值在3~5μm波段降低约50%,在8~14μm波段降低约20%。红外抑制器的下洗气流进口加装弯曲导流片可以对内部混合管高温壁面进行遮挡,有效降低顶部视角的红外辐射强度。最佳排气角度下,利用排气下游隔板的遮挡,正对抑制器排气出口方向(底部视角)上的3~5μm和8~14μm波段红外辐射峰值分别降低约50%和33%。

空气涡轮火箭发动机燃烧室异形尾缘波瓣混合器掺混、燃烧特性研究

为了促进空气涡轮火箭发动机(ATR)燃烧室内涵富燃燃气与外涵空气之间的掺混,提高燃烧室燃烧效率,本文通过对波瓣进行尾缘修形设计,探究C形尾缘结构对波瓣下游流动及燃烧特性的影响规律。研究发现:(1)在波瓣混合器尾缘增加C形结构,会诱导产生多源副涡结构;(2)径向高度越高,径向速度梯度越大,造成副流向涡和副展向涡的强度和尺度越大;(3)由于受到C形尾缘结构诱导的副流向涡和副展向涡的影响,燃烧室展向截面温度分布出现“串状”局部高温区,燃烧得到强化;(4)当燃烧室距离与波瓣直径<1时,内、外涵气流掺混强烈,热混合效率、燃烧效率以及总压损失迅速增大;(5) C形尾缘结构数量与燃烧效率不成单调递增关系,当C形结构数量≤2时,副涡强化掺混起主导作用,燃烧效率随着副涡量的增大而增大;当C形结构数量≥3时,出口面积增大导致的涡量衰减起主导作用,燃烧效率随着副涡量的增大而减小。

Optimization of a Lobed Mixer with BP Neural Network and Genetic Algorithm

A Sequential Approximate Optimization framework(SAO)for the multi-objective optimization of lobed mixer is established by using the BP neural network and Genetic Algorithm:the ratio of lobe wavelength to height(η)and the rise angle(α)are selected as the design parameters,and the mixing efficiency,thrust and total pressure loss are the optimization objectives.The CFX commercial solver coupled with the SST turbulence model is employed to simulate the flow field of lobed mixer.A tetrahedral unstructured grid with 5.6 million cells can achieve the similar global results.Based on the response surface approximation model of the lobed mixer,it is necessary to avoid increasing or decreasingαandηat the same time.Instead,theαshould be reduced while theηis appropriately increased,which is conducive to achieving the goal of increasing thrust and reducing losses at the expense of a small decrease in the mixing efficiency.Compared with the normalized method,the non-normalized method with better global optimization accuracy is more suitable for solving the multi-objective optimization problem of the lobed mixer,and its optimal solution(α=8.54°,η=1.165)is the optimal solution of the lobed mixer optimization problem studied in this paper.Compared with the reference lobed mixer,theα,β(the fall angle)and H(lobe height)of the optimal solution are reduced by 0.14°,1.34°and 3.97 mm,respectively,and theηis increased by 0.074;its mixing efficiency is decreased by 4.46%,but the thrust is increased by 2.29%and the total pressure loss is decreased by 0.64%.Downstream of the optimized lobed mixer,the radial scale and peak vorticity of the streamwise voritices decrease with the decreasing lobe height,thereby reducing the mixing efficiency.For the optimized lobed mixer,its low mixing efficiency is the main factor for the decrease of the total pressure loss,but the improvement of the geometric curvature is also conducive to reducing its profile loss.Within the scope of this study,the lobed mixer has an optimal mixing efficiency(ε=74.14%)that maximizes its thrust without excessively increasing the mixing loss.

基于PAM-STAMP仿真的波瓣混合器整体成形技术研究

对混合器波瓣的整体成形工艺进行了分析,利用PAM-STAMP软件对成形过程进行模拟仿真,对仿真结果显示可能造成零件减薄和开裂的部位采取措施,最后提出合理的成形工艺方案,解决了零件整体成形时产生裂纹、减薄、起皱等难题。

High mixing effectiveness lobed nozzles and mixing mechanisms

For a circular lobed nozzle with the exit plane displaced from the center body,adding a central plug at exit or replacing the nozzle with an alternating-lobe nozzle can improve the mixing effectiveness.In this study,numerical investigations of jet mixing in the lobed nozzles with a central plug and alternating-lobe nozzles in pumping operation were conducted.The effects of the central plugs with the wake ranging from attached to separated flow on the mixing were analyzed,along with the mechanism of improving the mixing performance in a"sword"alternating-lobe nozzle.The simulation results reveal that the large-scale mixing rate,which is dominated by streamwise vortices,is related to the intensity of the attainable heat and mass transfer in the streamwise vortices.The effects of the streamwise vortices on the normal vortex ring are virtually a manifestation of the heat and mass transfer/mixing process of the streamwise vortices.The simulation results also show that the central plug with the attached rear-flow performs better in improving the mixing effectiveness and pumping performance;on the contrary,if the rear-flow is separated,more pressure loss will be induced.In particular,a completely separated flow over the rear of the central plug will severely degrade the attainable heat and mass transfer in the streamwise vortices.For the sword alternating-lobe nozzle,wider sword deep troughs help to increase the flux of the secondary stream around the core region and delay the confluence of the primary stream in the region between the deep and shallow troughs.Thus,the mixing is improved in the middle and posterior segments.Compared to the lobed nozzle with a central plug,the improved sword alternating-lobe nozzle can achieve a higher mixing effectiveness with much less pressure loss,which is preferred in situations when the power loss of the engine is restricted.

Convective heat transfer on flat and concave surfaces subjected to an impinging jet form lobed nozzle

A tri-dimensional lobed nozzle is concerned in the jet impingement on a flat target and a concave target in the current study. The jet impingement heat transfer experiments are conducted under two jet Reynolds numbers(Re=10000 and 20000) and four nozzle-to-surface distances(H/d=2, 4, 6 and 8). Simultaneously, to characterize the flow dynamics of lobed jet impingement onto different target surfaces, some computations are conducted under a specific jet Reynolds number. The results show that the lobed jet is capable of achieving an increase of stagnation Nusselt number about 25% in relative to the round jet at small nozzle-tosurface distances. However, at large nozzle-to-surface distances, the lobed jet otherwise weakens the convective heat transfer in the vicinity of jet stagnation, especially under high jet Reynolds number. When compared to the flat target, approximately a20%–30% reduction of stagnation Nusselt number is produced on a concave target, which is attributed to the combined effect of destabilization and confinement due to the concave curvature.

Effects of Lobe Peak-to-Trough Width Ratio on Mixing and Combustion Performance in ATR Combustors

The air-turbo-rocket(ATR)engine is a promising propulsion plant for achieving numerous surface and air launched missile missions.The application of lobed mixer in the ATR combustor can promote the mixing of the fuelrich gas and the air,thus improving the engine performance significantly.The numerical simulation method was conducted to explore the effects of lobe peak-to-trough width ratio on mixing and combustion performance in ATR combustors.Results show that:For a given peak lobe width b1,the combustion efficiency and total pressure loss decrease with the increase of trough lobe width b2;For a given b2,the combustion efficiency and total pressure loss decrease with the increase of b1;The fan-type lobed mixer with smaller b2has a better effect on promoting the combustion efficiency in the region near the ATR combustor center line than that with a pair of parallel side walls.The total pressure recovery coefficient reaches more than 0.99 at the exit of combustor in nonreactive combustion while the total pressure loss reaches more than 4%in the reacting combustion.Compared with the mixing process,more than80%of the total pressure loss is caused during combustion.

Performance analysis of lobed nozzle ejectors for high altitude simulation of rocket engines

Ejectors are used in high altitude testing of rocket engines to create vacuum for simulat-ing the engine test in vacuum conditions.The performance of an ejector plays a vital role in creating vacuum at the exit of the engine nozzle and the nozzle design exit pressure at the time of ignition.Consequently,the performance of ejectors has to be improved to reduce the consumption of active fluid.In this investigation,the performance of an ejector has been improved by changing the exit shear plane of the nozzle.Conventionally,conical nozzles are used for creating the required momentum.Lobes of 4 no’s,6 no’s and 8 numbers for an equivalent area ratio=5.88 are used to increase the shear area.The influence of shear plane variation in the suction pressure is studied by a detailed CFD analysis.

异形喷嘴撞击流混合器涡特性及混合性能数值模拟

为了研究撞击流混合器不同形状喷嘴的流场涡特性及混合效果,利用数值模拟方法对不同工况下的流场进行分析,得到不同喷嘴撞击流混合器的速度场、涡量场、涡结构以及浓度变异系数的变化规律,揭示不同形状喷嘴对撞击流混合器混合效果的影响。结果表明:喷嘴出口截面为圆形、等边三角形和正方形的撞击流混合器轴向速度为“V”形分布;喷嘴截面为圆形和正方形的撞击流混合器径向速度为“M”形分布。等边三角形截面喷嘴的撞击流混合器产生的流向涡数量多、强度大并且产生的涡旋结构的连续性更高,分布范围更广。相同工况下等边三角形截面喷嘴的撞击流混合器混合效果明显优于圆形喷嘴和正方形喷嘴混合器,最快达到混合均匀。

冶炼烟气制酸装置设备优化改进

针对铜冶炼烟气制酸装置在运行过程中易出现的动力波洗涤器的逆喷管高温损坏,压滤机房弥漫SO2气体,余热锅炉带压给水管道高温水泄漏,混酸器、干燥塔塔底过滤器及脱吸塔酸管等设备、管道腐蚀泄漏等问题,从设备管理方式、设备的结构和材质等方面进行了优化改进。优化改造后,制酸装置的设备运行稳定可靠,制酸系统作业率得到提升,确保了制酸系统长周期生产稳定。

Flow-Field of an Axisymmetric Lobed Mixer

The flow-field of a fuel/air mixing system with an axisymmetric lobed mixer was numerically investigated. Large-scale streamwise vortices are formed immediately downstream of the mixer trailing edge, stretched further downstream, and finally broken into fragments where more intense mixing occurs. Both numerical and experimental results indicate that the length required for streamwise vortices breakdown in the confined flow-field of an axisymmetric lobed mixer is much shorter than that in the case of planar lobed mixers subject to parallel freestreams. For the conditions studied, the streamwise vortices start to breakdown at three wavelengths downstream of the mixer trailing edge.

波瓣混合器内、外张角对燃烧室燃烧影响研究

采用数值模拟的方法,对ATR发动机燃烧室波瓣混合器不同内外张角结构的燃烧流场及性能进行研究,得到外张角增大5°和内张角减小5°会增加流向涡的尺度和涡量的大小的结论。增加波瓣混合器外张角会增强内、外涵气流掺混,提高波瓣混合器的热混合效率;减小波瓣混合器外张角可以有效降低外机匣的热负荷,同时减小波瓣混合器内张角可以降低中心锥热负荷;增加波瓣混合器内外张角可以提高空气涡轮火箭发动机的燃烧效率。

Computational Studies of Lobed Forced Mixer Flows

Full Navier-Stokes Analyses have been conducted for the flows behind the trailing edge of a lobed forced mixer. The governing equations are derived from the timedependent compressible Navier-Stokes equa tions and discretized in the finite-difference form. A simple two-layer eddy viscosity model has also been used to account for the turbulence. Computed results are compared with some of the velocity measurements using a laserDoppler anemometer (Yu and Yip (1997)). In general, good agreement can be obtained in the streamwise mean velocity distribution but the decay of the streamwise circulation is underpredicted. Some suggestions to the discrepancy are proposed.

直升机排气系统用波瓣喷管引射-混合式红外抑制器研究

在针对直升机排气系统用波瓣喷管引射-混合式红外抑制器开展的一系列数值计算和模型实验研究基础上,对其内流气动特性和红外辐射特性进行较为系统的综合总结。揭示并分析了这种形式的红外抑制器内部混合流动特征,引射混合和隔热遮挡的红外抑制作用效果,以及红外抑制器缩比模型红外辐射模化关系;同时也指出了需进一步研究的一些问题。

圆排波瓣圆柱混合管的气动特性实验研究

建立了实验装置 ,对圆排波瓣喷管与 8只圆柱混合管相配合 ,进行了冷热态实验。得出了它们引射混合的引射流量比随主次流温度比、混合管截面比、次流进口截面比的变化关系曲线。另外 ,还对不同温度下修正流量比的温度指数进行了研究 ,得出圆排波瓣圆柱混合管引射混合器的修正流量比温度指数 n=0 .4。