一种新型激光法测量仪器在喷嘴雾化特性测量中的应用

本文介绍了一种新型在激光测量仪器及其测量原理和数据处理方法。在数据处理中引入分布函数，大大提高了计算速度。最后给出实验实测测量超声波喷嘴燃油雾化粒子尺寸分布的数据，并根据结果分析了所测的超声波雾化特性。     

超声波喷嘴雾化性能影响因素的研究

为研究新的雾化方式并将其应用于实际的油雾润滑系统中,针对流体动力式超声波喷嘴,设计其雾化性能测试系统。通过测量喷嘴产生的油雾浓度和喷嘴的流量,研究喷嘴在不同进气压力、进出口压差时的雾化性能。研究结果表明:随着喷嘴进气压力的增大,油雾浓度先增大后减小,喷嘴流量先增大后趋于恒定,喷嘴的进口压力最佳值为0.5 MPa;增大喷嘴进出口压差可以明显地提高油雾浓度和喷嘴的流量,喷嘴的雾化性能得到显著提升。     

具有旋芯的高效雾化喷嘴仿真和实验研究

雾化喷嘴广泛应用于动力机械工程领域。在煤矿湿式除尘系统中,喷嘴的雾化性能决定了除尘效果,开展雾化喷嘴结构参数研究,对提高除尘效率具有重要意义。基于喷嘴气穴等因素,首先阐述了雾化机理;随后设计了一种旋流雾化喷嘴,并利用Fluent对雾化过程进行数值模拟,得出了两相流的运动规律;最后实验测量了不同入口压力下的粒径分布情况,验证了仿真结果的正确性。研究表明:旋流雾化喷嘴可以有效阻止气穴现象的产生,可提高喷嘴的喷雾效率。     

新型细水雾灭火喷嘴的仿真及试验

为了解决细水雾喷头喷雾保护半径小的问题,研制了一种新颖的两级雾化高压细水雾灭火喷嘴。计算了索太尔雾滴直径DSM、喷嘴流速、流量和充分雾化距离。在CFD仿真中,将两级雾化喷嘴的速度场和水体积分数分布与单级雾化喷嘴的对应仿真结果分别进行对比,并优化了两级雾化喷嘴的结构参数。试验测量了DSM、喷雾速度、喷雾密度分布并和仿真结果进行对比验证。研究表明,优化设计后两级雾化喷嘴的喷雾保护半径为0.34 m,喷雾密度分布均匀;具有多喷嘴的两级雾化细水雾喷头的喷雾保护半径可以超过2 m,在消防领域具有实用价值。     

4种脱硫喷嘴雾化特性对比试验

对目前湿法烟气脱硫系统中常用的4种机械式雾化喷嘴进行了雾化试验,采用高速数码摄影法对4种喷嘴在不同压力下的喷雾状况进行测试,并用ImageJ软件处理,得到各喷嘴在不同工况下的粒径、粒径分布和雾化角等特性。研究结果表明:4种喷嘴雾化粒径随液压的增大呈减小趋势,其中螺旋喷嘴雾化粒径最小,扇形喷嘴雾化粒径最大;螺旋喷嘴、空心锥喷嘴和扇形喷嘴的雾化角随液压增大变化不大,较为稳定,实心锥喷嘴雾化角随液压增大而增大,螺旋喷嘴与扇形喷嘴的雾化角较大,空心锥喷嘴的雾化角最小;各喷嘴在小于0.2MPa的液压下粒径分布不均匀,当达到0.2MPa后粒径分布较为均匀。综合结构特点和雾化特性,螺旋喷嘴较适用于火电厂湿法烟气脱硫系统。     

喷嘴雾化性能检测控制系统设计

设计了一种用于喷嘴喷雾角度自动检测装置,当喷雾场接近压力传感器时.对喷嘴喷雾的打击力进行数据处理,测量了雾滴群流量的分布,由VB编程计算出喷嘴喷雾的角度.     

喷孔结构对双旋流气泡雾化喷嘴喷雾特性的影响

研究了喷孔形状对双旋流气泡雾化喷嘴雾化特性的影响规律,分析了圆形孔、椭圆形孔和正方形孔喷嘴对流量特性、索特尔平均直径、粒径分布和粒子速度的影响。结果表明,不同喷孔结构的喷嘴流量特性曲线呈现相同的趋势,随着气液质量流量比的增大,喷嘴出口单位面积下的喷雾流量逐渐减小;相同气液质量流量比下,正方形孔喷嘴流量最大。相同工况条件下,椭圆形孔和正方形孔对比圆形孔的喷嘴具有更加优良的雾化效果,其D32降幅分别为28.2%,35.8%,而正方形孔喷嘴的雾化粒径最小。正方形孔喷嘴的微分分布曲线向左移动,累积分布曲线变陡,说明大颗粒液滴减少,小颗粒液滴所占比例增大,液滴的雾化质量得到改善,正方形孔喷嘴小尺度粒径更多,粒径分布更集中。异形喷嘴的速度大于圆形孔喷嘴的速度;椭圆形孔喷嘴和正方形孔喷嘴的粒子速度分别增加了14.8%和24.4%。     

单相高压细水雾喷嘴雾化特性的试验研究

雾化喷嘴的雾化特性对单相高压细水雾灭火系统的灭火效果有直接影响。通过试验研究了供水压力、喷嘴关键结构参数对喷嘴流量、流量特性系数、粒径分布规律的影响规律。发现喷嘴的结构参数变化对喷嘴雾化特性有显著影响。     

新型细水雾灭火喷头的研制

为了解决细水雾喷头喷雾保护半径小的问题，研制了一种新型细水雾灭火喷头。该喷头由一个喷头壳体、连接体以及多个喷嘴组成。在CFD仿真中，将两级雾化喷嘴的速度场和水体积分数分布与单级雾化喷嘴的对应仿真结果分别进行对比，并优化了两级雾化喷嘴的结构参数。试验测量了雾滴直径、喷雾密度分布并和仿真结果进行对比验证。介绍了细水雾灭火试验的装置和测温方法并采用研制的喷头进行了细水雾灭火试验。研究表明，该喷头具有2m的喷雾保护半径，采用该喷头产生的细水雾具有高效的灭火能力,在消防领域具有实用价值。     

气—液两相流旋流喷嘴雾化特性研究

液体的有效雾化是当前气液两相流研究中的重要课题,这其中雾化喷嘴的选择能很大程度影响雾化效果。通过查阅大量文献,对不同类型的气液两相流旋流喷嘴的结构、工作原理以及影响雾化效果的各个因素(包括:喷嘴结构、压缩空气压力以及气液比)做出了论述。在实验中采用压缩空气作为雾化介质,利用lyc2000激光粒度仪测量了不同情况下的喷雾特性参数如油雾粒径、油雾浓度等。同时对气液两相流旋流喷嘴雾化特性进行分析,并做了图表分析和曲线拟合。     

An experimental study on the effect of square grooves on decay characteristics of a supersonic jet from a circular nozzle

In this experimental work, the effect of square grooves on the structure of a supersonic jet emanating from a circular nozzle has been investigated at three different nozzle inlet total pressures i.e 360 kPa, 550 kPa and 720 kPa. The nominal exit Mach number is 1.8. A new empirical relation for predicting the supersonic core length for grooved nozzle has been suggested. Further, a new parameter “groove effectiveness” has also been suggested to quantify the effect of the groove by using the total pressure data in the supersonic core length. Experimental results suggest that at higher nozzle inlet total pressure, the groove effectiveness plays a minor role. From the jet centreline total pressure data, supersonic core length, the locations at which 50 % and 90 % decay occurs have been obtained. It has been observed that higher groove effectiveness is associated with smaller values of supersonic core length, L_50% and L_90%. Schlieren images of the jet structure shows unsymmetrical shock pattern of jets emanating from a single grooved nozzle.     

An experimental study of supersonic dual coaxial free jet

A supersonic dual coaxial jet has been employed popularly for various industrial purposes, such as gasdynamic laser, supersonic ejector, noise control and enhancement of mixing. Detailed characteristics of supersonic dual coaxial jets issuing from an inner supersonic nozzle and outer sonic nozzles with various ejection angles are experimentally investigated. Three important parameters, such as pressure ratios of the inner and outer nozzles, and outer nozzle ejection angle, are chosen for a better understanding of jet structures in the present study. The results obtained from the present experimental study show that the Mach disk diameter becomes smaller, and the Mach disk moves toward the nozzle exit, and the length of the first shock cell decreases with the pressure ratio of the outer nozzle. It was also found that the highly underexpanded outer jet produces a new oblique shock wave, which makes jet structure much more complicated. On the other hand the outer jet ejection angle affects the structure of the inner jet structure less than the pressure ratio of the outer nozzle, relatively.     

An experimental study of the nozzle lip thickness effect on supersonic jet screech tones

It is well known that screech tones of supersonic jet are generated by a feedback loop driven by the instability waves. Near the nozzle lip where the supersonic jet mixing layer is receptive to external excitation, acoustic disturbances impinging on this area excite the instability waves. This fact implies that the nozzle lip thickness can influence the screech tones of supersonic jet. The objective of the present study is to experimentally investigate the effect of nozzle-lip thickness on screech tones of supersonic jets issuing from a convergent-divergent nozzle. A baffle plate was installed at the nozzle exit to change the nozzle-lip thickness. Detailed acoustic measurement and flow visualization were made to specify the screech tones. The results obtained obviously show that nozzle-lip thickness significantly affects the screech tones of supersonic jet, strongly depending on whether the jet at the nozzle exit is over-expanded or under-expanded.     

Experimental study on hysteresis phenomena of shock wave structure in an over-expanded axisymmetric jet

In recent studies on two-dimensional supersonic jets, it is reported that the hysteresis phenomenon for the reflection type of shock waves in the jet flow field is occurred under the quasi-steady flow condition and this phenomenon is affected by the transitional pressure ratio between the regular reflection and Mach reflection. However, so far, there are few researches on the hysteresis phenomenon for the transition of shock waves between regular and Mach reflection in over-expanded supersonic jets and the phenomenon has not been investigated satisfactorily. Therefore, the purpose of this study is to clarify the hysteresis phenomena for the reflection type of shock wave in the over-expanded axi-symmetric supersonic jet experimentally, and to discuss the relationship between hysteresis phenomenon and rate of the change of pressure ratio with time. Furthermore, the effect of Mach number at the nozzle exit on hysteresis loop was investigated for two kinds of nozzle.     

A computational analysis of unsteady transonic/supersonic flows over backward facing step in air jet nozzle

A transonic/supersonic axisymmetric backward facing step nozzle flow in an air-jet loom has been analyzed numerically by using a time accurate characteristic based upwind flux difference splitting compressible Navier-Stokes method. The unsteady pressure and Mach number behavior along the center line of the main nozzle were analyzed by periodic inlet condition changes to simulate the intermittent flow inside main nozzle of an air-jet loom.     

Study on drug powder acceleration in a micro shock tube

Recently, micro shock tubes have been widely used in the medical engineering. The needle-free drug delivery device which mainly consists of a micro shock tube and an expanded nozzle has been produced to inject drug powders into human and animal bodies without any sharp metal needles. The drug powders were delivered by obtaining high momentum, which can be done by accelerating drug powders in the micro shock tube and supersonic nozzle. The particle-gas flows are induced by the incident shock wave developing by rupturing the diaphragm in the micro shock tube and again accelerated in the supersonic nozzle. The momentum of injected drug particles should be strictly controlled otherwise patients will suffer from skin injury or hurt. Even though micro shock tubes have been investigated in the past several decades, the detailed studies on particle-gas flows in the micro shock tube were rare to date due to the micro size and difficult experimental operation on micro shock tubes. In this paper, the experimental and numerical studies were carried out on investigating particle-gas flows in a designed micro shock tube. Particle tracking velocimetry (PTV) was performed to calculated particle average velocity at the exit of the supersonic nozzle. The nozzle flows were analyzed by obtaining instantaneous particle fields. The particle number density ratio was also investigated in the test section. The numerical simulations were performed by calculating unsteady Naver-Stokes equations on compressible flows and using fully implicit finite volume schemes. Discrete phase model (DPM) was used for simulating particle-gas flows in the micro shock tube. Particle diameter and density were varied to investigate their effects on the particle-gas flows. Unsteady particle-gas flows and shock wave propagation were obtained in details in the micro shock tube for present experimental and numerical studies.     

Li/Li2 supersonic nozzle beam

The characterization of a lithium supersonic nozzle beam has been made using spectroscopic techniques. It is found that at a stagnation pressure of 5.3 kPa (40 Torr) and a nozzle throat diameter of 0.4 mm the ground state vibrational population of Li(2) can be described by a Boltzmann distribution with T(v)= (195+/-30) K. The rotational temperature is found to be T(r)= (70+/-20) K by band shape analysis. Measurements by quadrupole mass spectrometer indicate that approximately 10-mol. % Li(2) dimers are present far downstream for an oven body temperature of 1370 K in the supersonic nozzle expansion. This measured mole fraction is in agreement with the existing dimerization theory.     

二维超音速喷管型线设计仿真研究

采用计算软件FLUENT,对四种经典收缩段型线下的流场特性进行数值模拟,为选择超声速风洞收缩段的型线提供依据。基于特征线理论,利用解析法完成超音速喷管膨胀段型线设计,通过分析总压恢复系数及均匀度等流场参数,确定型线膨胀角角度及喷管长度。结果表明,收缩段型线选用双三次曲线,膨胀角度3.5°的情况下,超音速喷管出口达到了设计要求马赫数,并获得了较好的气流品质。     

Supersonic turbine stator design using dense gas with numerical method

In recent years, interest in renewable energy as a substitute for power generation using coal has increased. As a next-generation power system, the Organic Rankine cycle (ORC) system, which requires a multi-stage turbine or a supersonic turbine to generate a high power, has been shown to have high potential for such uses. In this paper, a dense gas is chosen as a working fluid and a supersonic nozzle is designed for a supersonic turbine with advantages in terms of cost, power density and layout. Two stators are designed using the Method of characteristics (MOC) for air and dense gas. To validate the numerical model, the nozzle designed for the air is compared to that of a PIV experiment from the open literature, and the results indicate a reasonable agreement. The nozzle for the dense gas is different as that needed for air. Therefore, the modified MOC is applied based on a polytropic assumption. In conclusion, an estimation of the performance is implemented with loss coefficients for a different number of blades. The number of blades is shown to be proportional to the loss coefficient. For example, the case with the biggest numbers of blades is affected the most by the shock effect that occurs at the trailing edge.