Study on the influences of interaction behaviors between multiple combustion-gas jets on expansion characteristics of Taylor cavities

The purpose of this study is to investigate means of controlling the interior ballistic stability of a bulk-loaded propellant gun（BLPG）.Experiments on the interaction of twin combustion gas jets and liquid medium in a cylindrical stepped-wall combustion chamber are conducted in detail to obtain time series processes of jet expansion,and a numerical simulation under the same working conditions is also conducted to verify the reliability of the numerical method by comparing numerical results and experimental results.From this,numerical simulations on mutual interference and expansion characteristics of multiple combustion gas jets（four,six,and eight jets） in liquid medium are carried out,and the distribution characteristic of pressure,velocity,temperature,and evolutionary processes of Taylor cavities and streamlines of jet flow Held are obtained in detail.The results of numerical simulations show that when different numbers of combustion gas jets expand in liquid medium,there are two different types of vortices in the jet flow field,including corner vortices of liquid phase near the step and backflow vortices of gas phase within Taylor cavities.Because of these two types of vortices,the radial expansion characteristic of the jets is increased,while changing numbers of combustion gas jets can restrain Kelvin-Helmholtz instability to a certain degree in jet expansion processes,which can at last realize the goal of controlling the interior ballistic stability of a BLPG.The optimum method for both suppressing Kelvin-Helmholtz instability and promoting radial expansion of Taylor cavities can be determined by analyzing the change of characteristic parameters in a jet flow field.

Method of Testing of Dynamic Forces on Digital Jet Elements

Method of testing for dynamic output forces from jet elements is studied, the handwidth is large in testing with this method. By establishing a model of the test system and simulating it, principles of how inherent features of the test system affect the dynamic force test are found out. Thus a theoretical foundation is given for the design and error modification to the actual test system.

Design of the Testing System for Jet Elements

To analyze the errors of processing data, the testing principle for jet elements is introduced and the property of testing system is theoretically and experimentally studied. On the basis of the above, the method of processing data is presented and the error formulae, which are the functions of the testing system property, are derived. Finally, the methods of reducing the errors are provided. The measured results are in correspondence with the theoretical conclusion.

Mathematical model for abrasive suspension jet cutting based on orthogonal test design

This paper describes the application of orthogonal test design coupled with non-linear regression analysis to optimize abrasive suspension jet （AS J） cutting process and construct its cutting model. Orthogonal test design is applied to cutting stainless steel. Through range analysis on experiment results, the optimal process conditions for the cutting depth and the kerr ratio of the bottom width to the top width can be determined. In addition, the analysis of ranges and variances are all employed to identify various factors： traverse rate, working pressure, nozzle diameter, standoff distance which denote the importance order of the cutting parameters affecting cutting depth and the kerf ratio of the bottom width to the top width. ~rthermore, non-linear regression analysis is used to establish the mathematical models of the cutting parameters based on the cutting depth and the kerr ratio. Finally, the verification experiments of cutting parameters＇ effect on cutting performance, which show that optimized cutting parameters and cutting model can significantly improve the prediction of the cutting ability and quality of ASJ.

Properties and testing of a hydraulic pulse jet and its application in offshore drilling

Offshore drilling has attracted more attention than ever before due to the increasing worldwide energy demand especially in China. High cost, long drilling cycles, and low rate of penetration （ROP） represent critical challenges for offshore drilling operations. The hydraulic pulse generator was specifically designed, based on China offshore drilling technologies and parameters, to overcome problems encountered during offshore drilling. Both laboratory and field tests were conducted to collect the characteristics of the hydraulic pulse generator. The relationships between flow rate and pressure amplitude, pressure loss and pulse frequency were obtained, which can be used to optimize operation parameters for hydraulic pulse jet drilling. Meanwhile a bottom hole assembly （BHA） for pulse jet drilling has been designed, combining the hydraulic pulse generator with the conventional BHA, positive displacement motor, and rotary steerable system （RSS） etc. Furthermore, the hydraulic pulse jet technique has been successfully applied in more than 10 offshore wells in China. The depth of the applied wells ranged from 2,000 m to 4,100 m with drilling bit diameters of 311 mm and 216 mm. The field application results showed that hydraulic pulse jet technique was feasible for various bit types and formations, and that ROP could be significantly increased, by more than 25%.

Continuous Process Optimization and Computational Fluid Dynamics Simulation of a Methyl Anthranilate Jet Reactor

Methyl anthranilate(MA)is an important material for the synthesis of sodium saccharin,but the yield and quality of MA are not stable due to the batch operation conditions.In this study,the optimum conditions obtained by an orthogonal test in a batch reactor were a volume ratio of methanol to amide solution of 5:4,volume ratio of sodium hypochlorite to amide solution of 7:4,Hoffmann degradation reaction duration of 10 min,Hoffmann degradation reaction temperature of 10℃,esterification reaction duration of 10 min,and esterification reaction temperature of 40℃.The working flow velocity and allowable working viscosity range of a Venturi ejector inlet were both determined by a computational fluid dynamics(CFD)simulation.Based on the above experimental data,the continuous operation of the process was tested in a three-stage continuous reactor,which improved the product yield and quality of the process.

高超声速大动压下整流罩分离测力风洞试验

针对高超声速试验模型整体式整流罩的反推火箭拔罩分离问题,开展了反推火箭喷流模拟方法和风洞测力试验装置设计研究,试验模拟了马赫数5、动压33 kPa时整流罩反推喷流干扰效应和分离距离影响,获得了反推喷流和分离距离影响下的整流罩气动特性。试验研究表明:反推火箭拔罩分离过程中,喷流干扰作用主导了整流罩的气动特性,使得法向力系数、轴向力系数和俯仰力矩系数分别出现了44.5%、32.4%和198.6%的最大变化量;在负迎角下,整流罩压心前移显著,使得静稳定设计的整流罩呈现出静不稳定性,不利于整流罩安全分离;分离距离越大,分离距离变化对整流罩气动特性的影响越弱;将分离初始迎角限定为小的正迎角,整流罩在分离过程中容易保持姿态稳定,有利于整流罩安全分离。

高燃压中型运载火箭发射地面低高度排导技术

综合高燃压中型运载火箭高密度发射燃气流地面排导需求及烧蚀风险分析,提出基于地面双面导流装置与高位挡流墙结合的地面低高度排导技术方案。利用火箭发射燃气动力学研究总结的燃气流膨胀特性以及导流型面设计方法,解决了地面低高度排导技术涉及的地面导流装置导流型面气动设计以及尺度控制两个关键问题。地面低高度排导技术方案设计与燃气流场瞬态仿真多轮叠代,实现了燃气流排导烧蚀范围合理控制,避免了燃气流低高度排导烧蚀反溅影响箭体。地面低高度排导技术采用专利支撑的喷水冷却防护方案实现高燃压中型运载火箭发射燃气流强烧蚀环境发射系统、发射设施综合防护。基于喷流缩比试验相似性控制方法研制了1∶10比例喷流缩比试验系统,通过喷流缩比试验验证确认高燃压中型运载火箭发射燃气流能够实现地面低高度安全、顺畅排导,同时与发射台、导流装置结构融合的阵列喷水方案能够行之有效解决高燃压中型运载火箭地面低高度排导强烧蚀难题。

喷水式超声检测的声−流耦合模型

为研究超声波在射流水柱中的传播特性,提出了喷水式超声检测的声−流耦合建模方法。使用计算流体动力学方法得到喷水探头内部流场的湍动能、速度和压力,并通过弱形式偏微分方程将其映射到声学网格作为声场分析的边界条件,用线性纳维−斯托克斯方程求解湍动能、流速等引起的声学变化,建立了喷水式超声检测的声−流耦合模型。仿真计算了不同流速时工件内部的声压分布,进水口流速的变化不会改变工件中声压的分布规律,但空间声压幅值随着流速的增大而减小。仿真计算了不同流速时的平底孔回波,回波幅值随着流速的增大而减小,通过与实验结果对比,验证了本文方法的准确性。

3/4开口试验段汽车风洞的风阻测量误差分析与修正

汽车风洞用3/4开口试验段模拟真实道路气动环境,有限的试验段尺寸、地面边界层及射流剪切层会干扰流场,从而引起风阻测量误差。根据简化势流模型分析,3/4开口试验段存在模型实体阻塞、喷口阻塞、收集口阻塞以及水平压力梯度4项系统误差源,其中模型实体阻塞让风阻测量值偏低,喷口和收集口阻塞让风阻测量值偏高,彼此平衡抵消机制使3/4开口试验段风洞具有能够适应更大尺寸模型的优势。利用Mercker-Wiedemann修正方法,结合同济大学整车气动声学风洞,计算修正了3辆不同尺寸车型的风阻系数。结果显示:设定风阻系数误差不超过1%为标准,3/4开口试验段汽车风洞最大阻塞比为15%;水平压力梯度对风阻系数误差的影响更大,风洞设计和验收标准应保证dC_(p)(x)/dx≤0.001/m。

基于正交试验法的铝合金车体高压水清洗喷嘴结构优化

抑尘剂等复杂的化合物黏着在铝合金车体上,导致车体污染十分严重,高压水射流清洗方法能够有效去除铝合金车辆车体表面黏着的化合物。通过分析圆柱形、锥形、文丘里形和余弦形喷嘴的射流流场分布、射流出口速度、最大壁面静压、相同清洗宽度下压力值范围,得到余弦形喷嘴的清洗性能最佳,锥形喷嘴次之。基于正交试验法设计五因素、四水平正交试验表,得到常用清洗压力下余弦形喷嘴的最优结构参数:进口直径为40 mm、出口直径为20 mm、过渡段半径为40 mm、出射段长度为25 mm、过渡与余弦部分长度比为4。按照最优喷嘴结构参数进行建模,得到三组压力值下高压水出射速度比未优化前提高了2%,且优化效果随着入口压力值的提高而有所下降。在优化后的喷嘴结构参数下进一步计算得出入口压力为10 MPa时,靶距设置为250 mm能达到较好的清洗效果和节能作用。

导叶叶片数对喷水推进泵瞬态特性的影响

为揭示喷水推进泵不同导叶叶片数时的瞬态特性规律,基于DES混合模拟和FEM声学有限元方法,对喷水推进泵流场和声场进行数值模拟,并进行试验,验证了瞬态特性数值计算方法的准确性,研究了不同导叶叶片数(Z=5,6,7)对喷水推进泵推力、压力脉动、内流诱导噪声等性能的影响规律.结果表明:随着导叶叶片数增大,喷水推进泵推力先减小后增大,流量逐渐减小,转矩逐渐增大;导叶叶片数对叶轮出口压力脉动分布规律影响较小,对压力脉动主频处幅值有较大影响,轮毂处压力脉动幅值受导叶叶片数增大先减小后增大,轮缘和流道中心处幅值随着导叶叶片数增大逐渐减小;导叶叶片数变化会改变内流诱导噪声主频,增大导叶叶片数有利于降低喷水推进泵内流诱导噪声主频处幅值和总声压级.

TCP+MFE+JET三联作测试工艺技术研究与应用

针对低压、低渗非自喷油层求取油层产能、压力、收集有代表性产液样品资料难的问题,研究开发了TCP+MFE+JET三联作测试工艺管柱。经现场应用表明,该工艺不仅解决了上述问题,而且缩短了油气井测试周期,降低了试油成本。

艉板式与浸没式喷水推进器尾迹脉动压力试验研究

喷水推进器的喷射流尾迹对船舶隐身特性造成不利影响,目前缺乏喷水推进船舶喷射流尾迹的测试方法及特性研究。本研究搭建了喷水推进船舶尾迹脉动压力测试试验台,分别对艉板式与浸没式推进器喷射流尾迹开展脉动压力测试,基于不同测点位置、不同航行状态下的尾迹脉动压力频谱结果,对比了艉板式喷水推进器和浸没式喷水推进器的尾迹频率与振幅特性,并基于HHT方法细致分析了航行状态下的喷射流尾迹发展规律。发现在靠近水面的浅水位置,相较浸没式推进器,艉板式推进器的喷射流入水显著增强尾迹强度和影响范围,而在深水位置,喷射流强度整体差异不大。此外,在航行状态下,由艉板式推进器喷射流引起的波浪强度也明显高于浸没式推进器,结论为浸没式喷水推进技术发展与推广应用奠定了基础。

射流撞击式低压喷头设计与水力性能试验

为分散喷头主射流,提高喷头的喷洒均匀度,使喷头适用于农业低压喷灌,该研究结合射流与撞击流提出了一种射流撞击式旋转喷头。首先对比了射流撞击喷头与射流不撞击喷头的水力性能,通过正交试验分析了各结构参数值对射程和组合均匀系数的影响,得到副喷嘴结构优化参数,最后将优化后的射流撞击喷头与改进前的传统15PY2喷头进行水力性能及水滴粒径分布对比。研究结果表明,射流撞击使射程末端水量高点降低,同时射程得到提升,射程平均提升4.39%,在相同压力及组合间距下覆盖范围更大。影响喷头工作性能的结构参数依次为副喷管长度、副喷嘴进口锥角、副喷管内径、副喷嘴仰角,而副喷嘴仰角对射程与组合均匀系数影响最大,15型射流撞击喷头最佳结构参数组合为:副喷管长度20 mm、副喷嘴进口锥角55°、副喷管内径6 mm、副喷嘴仰角33°。射流撞击喷头在压力150~300 kPa下组合均匀系数和综合评分均高过传统15PY2喷头,组合均匀系数平均提升4.84%,综合性能平均提升4%,证明了射流撞击应用于旋转式喷头具有优势。在射程前中段,150和250 kPa下射流撞击喷头水滴直径更大;在射程后段,150 kPa下射流撞击喷头水滴直径更大,但在250 kPa下水滴直径更小。研究所得到的喷头结构及结论可为后续研究射流撞击对水力性能的影响提供参考。

STV-TCP-JET-措施改造四联作测试技术的应用及提高

STV-TCP-JET措施改造四联作工艺技术在不动井口和管柱的情况下,省去了洗压井、起出测试管柱、重新下入措施—排液管柱等工序,缩减试油周期。经过不断的探索和完善,该项工艺已成为南堡油田滩海试油的主导工艺技术。

TCP+MFE+JET三联作试油(测试)工艺技术

TCP+MFE+JET三联作试油(测试)工艺技术集大孔径深穿透负压射孔技术、地层测试技术和水力泵深排强排技术的优点为一体,实现了连续大量排液,减少了洗压井次数和起下作业次数。特别适用于自然产能低的稠油层或低压漏失层等需要连续大量排液的油层。经21井次的现场应用证实,该联作工艺简单、操作方便、施工周期短,是一套完整高效的、有利于保护油气层的试油(测试)新技术,具有良好的经济及社会效益。

燃气舵操纵机构摩擦力矩试验技术研究

针对在试验室条件下高效准确评估燃气舵操纵机构摩擦力矩需求,设计了燃气舵舵轴轴承摩擦力矩试验系统,在此基础上进一步搭建了操纵机构摩擦力矩试验系统,充分模拟燃气舵系统实际安装状态,进而提出了摩擦力矩试验方法,揭示了关键轴承摩擦力矩随加载载荷与过载系数变化规律,探究了操纵机构摩擦力矩关键影响因素。试验结果表明,试验系统为准确获取摩擦力矩提供了合理的测试手段,舵轴关键轴承摩擦力矩随加载载荷和过载系数的升高而增大,增加关键轴承之间的距离可以明显减小摩擦力矩,且轴承摩擦力矩在操纵机构摩擦力矩中起主导作用。

圆周往复水射流式挖藕试验装置设计与试验

为满足莲藕采挖作业多样化的试验要求,提高试验装置的互换性、通用性与测量精度,设计了圆周往复水射流式挖藕试验装置。介绍了试验装置中试验台的结构设计、工作原理和关键部件设计,分析了圆周往复水射流结构在不同条件的挖掘深度及莲藕浮出率等,确定了试验指标,并进行了台架验证试验。结果表明:圆周往复水射流式挖藕试验装置能够有效反映喷头直径、喷射角度和喷头与泥土表面距离对莲藕采挖效果和挖掘深度的影响。当喷头直径不变时,喷射角度越小挖掘深度越深,喷头与泥土表面距离越小挖掘深度越深,喷射角度越大冲刷面积越大,成正比例关系;喷头与泥土表面距离越近、喷射角度越小情况下莲藕的浮出率越高,满足圆周往复水射流式挖藕试验要求。

跨隔+TCP+MFE+JET四联作试油新技术的应用

跨隔 +TCP +MFE +JET四联作试油新技术实现了跨隔、油管输送负压射孔、地层测试、水力喷射泵排液等多项先进技术为一体的研究与现场应用 ,该项技术的优点主要在于使跨隔、射孔、测试、排液等多工序一趟管柱完成 ,减少了注水泥塞封闭原试油层工作 ,避免了压井换管柱污染油层 ,排液及时 ,获取不同制度下的产能、压力资料 ,对于低压、低渗、低产、高凝、高粘油气层特别适用。