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燃气涡轮试验与研究

燃气涡轮试验与研究

北大核心

Gas Turbine Experiment and Research
本刊（季刊）是经国家科委批准向国内外公开发行的正式期刊，系综合性技术刊物，由中国航空工业第一集团公司主管，中国燃气涡轮研究院主办。本刊以燃气涡轮技术为基础，重点报道航空动力装置试验研究，设计和制造行业中具有学术价值，工程应用价值和创造性的科技成果及其在国民经济领域的应用。
  • 发文量：1387
  • 被引量：398
  • H指数：1
  • 开始收录时间：1989,2(1)
  • CNKI综合因子：0.213
  • 维普期刊影响因子： 0.55
  • 万方期刊影响因子：0.18
  • 创刊时间：1988
  • 国内刊号/CN：51-1453/V
    国际刊号/ISSN：1672-2620
  • 发行周期：双月刊
    邮发代号：-
  • 主管单位：中国航空工业第一集团公司
    主办单位：中国燃气涡轮研究院
燃气涡轮试验与研究-联系信息
  • 主编：刘志友
  • 电话：028-83017527
  • 邮箱：rqwlsy@163.com
  • 地址：四川省成都市新都区新军路6号
  • 邮编：610500
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  • • 荣获《中文核心期刊要目总览》2011年版(即第六版)之航空,航天类核心期刊殊荣.
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燃气涡轮试验与研究 >2023年第1期

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  • 摘要：An inverse method of airfoil design adapted for engineering application has been employed to im- prove the performance of high loading fan rotor. The basic ideas of combination of viscous CFD and numeri- cal optimization can meet airfoil design requirements with the element profile flow characteristics of high in- let Mach number and high adverse pressure gradient, etc. Succeeding to the design criterion of element pro- file stacking, the two-dimensional inverse method and three-dimensional stacking can save the computing time greatly. The airfoil design has been carried out by using the inverse method numerical platform. The re- suits of numerical simulation showed that the rotor airfoil designed with the inverse method can control the shock structure, decrease the shock loss, improve the efficiency and increase the surge margin.%为改进高负荷风扇转子性能，采用了一种工程适用的叶片反问题设计方法。该方法使用粘性CFD与数值优化相结合，适合具有高进口马赫数、高逆压梯度流动特征的高效叶型设计，并应用二维叶型反问题加三维积叠的叶片设计思路，充分继承了已有的基元叶型积叠准则，极大地缩短了计算时间。利用发展的反问题设计平台，完成了叶片的反问题设计。三维数值模拟结果表明：反问题设计的转子叶片能较好地控制转子尖部激波结构，减小激波损失，提高效率，增大稳定裕度。
  • 摘要：北京华清燃气轮机与煤气化联合循环工程技术有限公司（燃气轮机与煤气化联合循环国家工程研究中心，以下简称公司／工程中心）是国家发展和改革委员会审核批准（发改办高技[2008]248号），由清华控股有限公司、东方汽轮机有限公司、哈尔滨汽轮机厂有限公司、南京汽轮动力设备有限公司、上海汽轮机厂有限公司、中国船舶重工集团公司第七。三研究所和中国电力工程顾问集团公司七家单位出资入股，国家重点支持的具有独立法人地位的股份制高科技研发设计企业。
  • 摘要：为了满足发动机宽广飞行参数范围的模拟需要，高空台配置了一套由气源系统、空气处理系统、混合器、进排气调压系统、高空试验舱、排气系统和测试控制系统等构成的庞大试验设备。
  • 摘要：某小型航空发动机在原理样机阶段存在整机振动大的现象，发动机试验时机匣上的最大振动监测值达179mm／s，严重影响发动机试验安全。通过对发动机的转子动力学设计和试验研究，找出转子连接刚性差是造成发动机振动大的关键原因。在验证机阶段设计中，对转子连接刚性进行了针对性改进。改进后的试验表明，发动机振动得到明显改善，最大振动监测值为33mm／s，确保了发动机试验安全。%Violent vibration appeared in the phase of principle prototype of a small aero-engine. During engine tests, the maximum vibration monitoring value of casing was up to 179mm/s, which seriously affected the safety of engine test. Through dynamic design and experimental research on the rotor, it was found that the rotor joint rigidity was the key factor causing engine vio lent vibration. Therefore the improvements on rotor joint rigidity were made during the design of demonstrator. Test results showed that the engine vibra- tion was greatly reduced and the maximum value was only 33 mm/s, which ensured the safety of engine test.
  • 摘要：The engine performance degradation index was established based on geometrical distance of support vector machine （SVM） and predicted by multi-step method based on phase space reconstruction theory. The result of support vector regression （SVR） is superior to neural network. Performance characteristic parameters were simplified by principal component analysis （PCA） and kernel PCA （KPCA）. The principal component was extracted and classification of KPCA was better. Parameters of support vector classification （SVC） and kernel function were optimized by cross validation. Curve of engine performance degradation index was presented. Variation of engine performance was analyzed by establishing statistics to determine the key point of performance variation. The results provide reference for engine maintenance and life extension.%基于支持向量机几何距离建立表征发动机性能衰退程度的指标，并基于相空间重构理论对该指标进行多步预测，表明回归支持向量机结果优于神经网络预测结果。利用主元分析、核主元分析方法对发动机性能特征量约简并提取其主元，得到核主元分析的分类效果更好。利用交叉验证的方法优化分类支持向量机和核函数中相关参数，给出发动机性能衰退指标曲线。通过建立统计量的方法分析发动机性能变化，确定性能变化关键点。所得结论对做好发动机维护保养工作，延长发动机使用寿命具有一定的指导意义。
  • 摘要：通常，风扇／压气机可用稳定裕度明显高于具体使用条件下的最大值，理论上为发动机性能提高提供了可能。基于上述思想，本文开展了主动稳定性控制（ASC）方法研究，在小畸变下，通过降低稳定裕度要求来提高性能；在超出畸变容限时，必须无条件保证发动机的工作稳定性。建立了进气畸变气动稳定性模型，并嵌入常规控制规律，推导出主动稳定性控制规律，给出相应控制策略。以某涡扇发动机为对象，开展了主动稳定性控制仿真研究。结果表明，在中等畸变强度以下，主动稳定性控制能有效满足降低稳定裕度的要求。%Generally the available stability margin of fan/compressor is larger than the maximum stability margin employed in practical operation, which provides a chance to enhance the aero-engine performance in theory. Based on this idea, investigation on the active stability control （ASC） of aero-engine. At the small inlet distortion, the aero-engine performance can be improved by relaxing stability margin （SM） demands. If inlet distortion exceeds the tolerance of aero-engine, stable operation of aero-engine is most important. Ac- cording to this principle, an aerodynamic stability model is constructed for inlet distortion and embedded with conventional control law. By this model, an ASC law is derived, and the corresponding control strategy is proposed too. Taking a turbofan as an example, the simulation study for ASC has been carried out, and the results demonstrate that the ASC with decreasing the SM requirement is most effective at the moderate inlet distortion.
  • 摘要：在地面试车台上，利用叶片式旋流发生器和五孔探针，对进气道旋流模拟和测量进行了试验研究。试验验证了旋流模拟方法、测量方法的有效性及旋流评定指标的可行性，结果表明：叶片式旋流发生器能有效地模拟出典型的整体涡、局部涡及对涡结构，其中整体涡强度可达15°；旋流测量方法行之有效且精度较高；旋流评定指标合理可行，能较为直观地反映旋流流场的强弱和结构。%The simulation and measurement of inlet swirl were carried out in ground test bed by using blade type swirl generator and five-hole probes. The validation of swirl simulating and measuring methods and the feasibility of evaluation criterion were testified. Test results show that designed blade type swirl generator can efficiently simulate typical bulk swirl, local swirl and twin swirl; the intensity of generated bulk swirl can reach to 15°. Swirl measuring method is feasible and with high resolution; swirl evaluation criterion is reasonable and can directly reflect intensity and structure of swirl.
  • 摘要：以某型涡扇发动机科研试飞为平台，设计搭建发动机附面层测量试验系统，进行了多种飞行工况及涡扇发动机工作状态下的附面层测量试验。通过试验数据分析和研究，评估了各计算参数对涡扇发动机进口附面层厚度的影响。建立三维数值模型，计算了相应工况下的附面层特性，计算数据与试验数据吻合良好。研究结果表明：随着发动机状态的增大，进气道出口的附面层物理厚度增大、附面层位移厚度减小，附面层对空气流通能力的影响降低。%Based on the flight test of a turbofan engine, the measure system of boundary layer were designed and built. Boundary layer of inlet was measured under different flight conditions and the engine conditions. By analyzing the test data, the effect of each calculating parameter on boundary layer thickness was evaluated. The model of numerical simulation for the boundary layer was established and modified using flight test data. By comparing the results of numerical simulation and flight test data, it was found the numer- ical results are in agreement with flight test data and the error can be acceptable. The results show that the thickness of boundary layer increases, displacement thickness of boundary layer and effect of boundary layer for mass flow reduces with the increasing of turbofan engine N1hs.
  • 摘要：利用FLUENT软件对S弯进气道旋流畸变进行数值模拟，通过分别对不同攻角、侧滑角飞行状态下的进气道沿程及出口流场进行分析，展现了旋流畸变的产生机理和发展过程。引入旋流评价指标，对旋流畸变进行评定，并与总压畸变评价体系进行对比和分析。研究表明：该S弯进气道出口固有的对涡旋流结构不随攻角变化，但旋流强度随攻角的增大略有减弱；在侧滑状态下，该S弯进气道出口对涡旋流消失，旋流以整体涡出现且强度较大；传统的总压畸变指数无法描述旋流，引入的旋流评价指标能较为准确、直观地评定旋流畸变强度和流场结构。%Numerical simulation was carried out to a S-duct inlet by applying FLUENT software. The characteristic and evolutive processes of swirl distortion were revealed by analyzing flow-field in different work conditions. An evaluation criterion for inlet swirl distortion was introduced and applied to analyze results, and compared to total pressure distortion evaluation criterion. Numerical simulation results and analysis show that the connatural twin swirl of S-duct inlet does not change with angle of attack, but the intensity of swirl reduces with angle of attack increasing; in the yawing flight conditions, the bulk swirl comes instead of twin swirl and the intensity is biggish; traditional total pressure evaluation criterion cannot be used to evaluate swirl distortion, by contraries the presented evaluation criterion for swirl distortion is feasible and can be used to evaluate both intensity and structure of inlet swirl distortion.
  • 摘要：介绍了自主研制的国内首台可变环境条件（压力、温度、流速）旋转碰摩式钛火试验器及相关试验研究，建立了旋转碰摩着火试验流程。通过设定旋转碰摩的工作环境及进给力大小，成功再现了钛合金试样（TC17/TC4）着火、稳定燃烧、燃烧扩展等复杂燃烧过程。该试验器的成功研制，为钛合金构件着火性能及其防护研究提供了试验手段，在航空发动机钛合金燃烧特性评估和防钛火试验研究领域，具有良好的应用前景。%The first self-developed rotating friction test facility for titanium fire is presented in different environmental conditions （including total pressure, total temperature and flow rate）. The relevant experimental study and rotating friction on-fire test procedures are introduced. The test procedures successfully reproduced the course of complex combustion （ignition, stable combustion, extension） of the titanium sample （TC 17/TC4） by setting rotation friction work conditions and entering force. The facility development was successful and provided experimental means to study the fire performance and fire proof coat of titanium alloy components. It will be widely used in the evaluation of aero-engine titanium alloy combustion characteristics and anti-titanium fire experimental research area.
  • 摘要：As one of the most suitable engines for high speed vehicle in future, TBCC （turbine-based combined cycle） engine enable aircraft with functions of horizontal take-off, flight maneuver and repeated use. This paper illuminates the various TBCC projects, such as RTA, FACET and Trijet in U.S, HYPR and ATREX in Japan and LAPCAT in Europe. Through the detailed analysis on the characteristics of various TBCC schemes, it is concluded that with turbine engine trchnology evolution, as well as the application of rocket ram injection and precooling technologies, the working Mach number could be expanded to 4.0, TBCC is feasible in engineering and it is the most promising aerospace propulsion in future.%涡轮基组合循环（TBCC）发动机是未来高超声速飞行器最适合的动力系统之一，配备该类发动机的高超声速飞行器具备水平起降、机动飞行和重复使用能力。本文对国外开展的TBCC研究项目（如美国的RTA、FACET和Trijet，日本的HYPR和ATREX，以及欧洲的LAPCAT）进行了系统阐述，较为详细地分析了各研究项目中TBCC方案特点，表明随着涡轮发动机技术的全面发展，及采用火箭引射冲压和预冷等技术，涡轮发动机的工作马赫数可扩大到4．0，且TBCC发动机具有工程可实现性，是未来最具发展潜力的空天动力。
  • 摘要：涡轮叶片外换热计算程序STAN5，采用Patankar—Spalding方法求解可压缩边界层微分方程，获得流动及温度边界层内的参数分布，进而得到叶片表面的外换热系数分布。本文分析了STAN5程序的求解方法，研究了程序在外流场存在较强逆压梯度时出现计算不收敛及错误收敛等现象的机理，并对程序进行了两点改进：修正了逆压梯度下边界层内部速度分布，建立了边界层内部沿流向的网格分布与主流压力梯度问的联系。改进后的程序有效地避免了计算发散等问题。%The STAN5 has been widely used for turbine blade external heat transfer calculation. Through solving the compressible boundary layer differential equations with Patankar-Spalding, the distribution of parameters, like velocity and temperature, inside the boundary layer can be gained. And then the distribution of external heat transfer coefficient of turbine blade can be gotten. The numerical methods of STAN5 are discussed. Two improvements have been made according to the non-convergence and the non-reason- able convergence problems of the program operating under reverse pressure gradient conditions. One was the modification of the boundary layer velocity distribution. Another was connecting the grid density along the stream line with the main stream pressure gradient. The problem of non-convergence is effectively avoided with these improvements.
  • 摘要：The finite element model of compressor rotor of marine gas turbine was buih. Mode analysis of the rotor was done and critical speed and unbalance response of rotor were calculated. Influence on dynamic characteristics of rotor by increase in stiffness was analyzed. The results show the rotor is a rigid rotor. Vibration behavior of rotor is affected mainly by first mode. Critical speed of rotor is 12825drain. Unbalance response of rotor is most sensitive to unbalance at 4th disc. Results also show that critical speed of rotor is not sensitive to stiffness change, which yet has an effect on unbalance response of rotor. The conclusion provides references for optimization design of the rotor.%建立某型舰用燃气轮机压气机转子的有限元模型，对转子的动力学特性进行研究。计算了转子的固有频率和振型，求解了转子的临界转速和不平衡响应，并就转子前支承刚度变化对转子临界转速和不平衡响应的影响进行了分析。结果表明：转子为一刚性转子，其振动行为主要受转子一阶模态影响；转子的一阶临界转速为12825r／min；转子不平衡响应对第4级附近存在的不平衡量最敏感；转子前支承刚度增大对转子临界转速影响不大，但对转子不平衡响应有一定影响。本文结果可为燃气轮机的可靠运行及转子的进一步优化设计提供依据。
  • 摘要：Titanium combustion in aero-engine is a serious hidden trouble for the application of titanium. The research on combustion characteristics of titanium could be in favor of rightly selecting titanium alloy for engine parts and suppression techniques of titanium fire. The combustion characteristics of titanium alloy TC1 1 were studied. In the test, the TC11 was ignited by TA1 droplet. The process of combustion, the influ- ence of temperature and content of oxygen on the ignition and the microstructure of burned alloy were ana- lyzed. On the effect of compressed air and oxygen, the combustion reaction of TA1 droplet and TC11 flake was very exquisite and many sparks ejected from the surface. With the increase of TC11 flake temperature, the critical oxygen partial pressure decreased. There was an oxide film form on the burned alloy surface. Under this oxide film, the microstructure was different from the original TC 11 alloy, three typical regions of loose region, compact region and infected region were formed due to the high temperature of titanium combustion.%钛火严重威胁航空发动机用钛安全，开展钛合金燃烧特性研究是发动机合理用钛及采取有效防范措施的基础。通过液滴引燃试验法初步研究了TCll合金的燃烧特性，分析了燃烧的过程特征、试片温度与氧气含量f分压）对启燃的影响及燃烧表面的微观组织。结果表明：在压缩空气／氧气作用下，TAl液滴发生燃烧并将TCll合金试片引燃，燃烧过程中反应剧烈，喷射出大量火花；随着TCll合金试片温度的提高，引燃所需的临界氧气分压逐渐降低；TCll合金试片的烧损表面形成了氧化层，从表面到内部呈现出疏松区、致密区和燃烧影响区三种典型的组织区。
  • 摘要：在对国内外各类叶片三维反问题深入分析的基础上，针对高效、高负荷风扇的设计需求，提出了级环境下风扇叶片三维反问题设计的技术思路。以高压比单级风扇为例，利用数值模拟、流动分析等技术手段，采用从基元截面、单排到单级环境逐步深入的方式，对级环境下三维反问题设计方法的可行性进行了验证，初步探索了级环境下叶片载荷分布规律，进一步发展并完善了高效、高负荷风扇叶片的三维反问题设计技术。%The detailed analysis on all kinds of national and international technical data of three-dimensional inverse method was carried out. According to the design requirements of high efficiency and high loading fan, the idea of fan airfoil design in stage environments by using three-dimensional inverse method was proposed. Numerical simulation and flow field analysis were performed in high pressure ratio single-stage fan. The feasibility of the inverse method in stage environments was validated from basic elements, single row to single stage. The blade loading distribution law was preliminarily studied. The airfoil in- verse design technique of high efficiency and high loading fan was improved and developed further through above methods.
  • 摘要：叶尖间隙是燃气轮机中的一个重要性能参数和安全监测参数。现代燃气轮机中采用H形凹腔冷却涡轮叶片，该叶片具有单叶片双间隙的特点。利用电容式叶尖间隙测量系统，通过改进算法，实现了H形叶片的叶尖间隙测量，并成功应用于H形叶片涡轮级性能试验。试验录取了三种不同设计间隙下的实际叶尖间隙变化数据，分析了叶尖间隙与涡轮性能之间的关系，并对试验中的转子异常运动进行了成功监测。%Tip clearance is an important parameter of performance and safety monitor in gas turbine. The H-form blade which is characterized with two tips has been used in modern gas turbines. Software that can calculate tip clearance of H-form blade was developed based on hardware of the capacitance tip clearance measure system, and had a good impression in a turbine experiment. Tip clearance data of three different designs were collected in experiments. The relationship between turbine performance and tip clearance was analyzed, and an abnormal state of turbine was monitored successfully in the experiment.
  • 摘要：针对某型航空发动机闭环转速控制器引起的转速摆动问题进行研究，分析得出转速控制器是一个典型的比例积分控制器，并建立了转速控制器的AMESim模型。通过模型得到转速控制器的频率特性，发现其截止频率与转速摆动频率重合。分析指出转速摆动量与比例控制器精度的关系，找到了转速摆动的根本原因，并通过设计稳态试验台实现了验证，指出了解决转速摆动和提高控制精度的方法。%　　This work is dedicated to the research of speed oscillation problem of an aero-engine, which is caused by its closed-loop hydro-mechanical speed controller. Analysis showed that the speed controller was a typical PI controller. The AMESim model of speed controller was established,and frequency response of speed controller was examined based on the model. It was found that the cut-off frequency of controller was identical with that of speed oscillation. Analysis revealed relationship between amplitude of oscillation and accuracy of proportional controller. The origin of speed oscillation was found out;verification for analy⁃sis was carried out by designing a steady-state test facility. Methods for resolving speed oscillation and im⁃proving control accuracy were given.
  • 摘要：采用NUMECA商用软件，模拟了叶片附面层吸气技术对高负荷风扇叶片三维流场的影响.重点研究了抽气模型的建立方法，深入分析了不同开孔位置、尺寸及不同抽吸量对风扇气动性能的影响.结果表明，在来流条件相同的情况下，转、静子选取适当的开孔位置，抽吸流量为总流量的1.5%时，压比、效率最大可分别提高6.5%和1.6%.%　　The numerical simulation of a high-loading aspirated fan was introduced. NUMECA software was adopted to simulate the influence of high-loading fan with boundary layer suction on the three-dimensional flowfield. The method of building the suction model and the influence of suction location and suction flow rate on the performance of fan were investigated in details. The results showed that with the same flow and appropriate suction locations for stator and rotor, the pressure ratio and adiabatic efficiency could be improved to 6.5%and 1.6%respectively with 1.5%suction ratio.
  • 摘要：确定部件修正参数和目标性能参数作为模型修正基础，结合稳态模型的平衡方程，构造修正发动机非线性模型的代价函数，修正发动机稳态模型。计算了在不同工况修正后的特性参数，并与用影响系数矩阵方法所得结果进行对比，经遗传算法修正后参数精度有了较大提高。利用部件修正参数组合对发动机稳态模型进行修正，其结果表明敏感性参数在模型修正中起关键作用。所用修正方法对发动机性能模型修正、提高模型精度有一定指导意义。%　　Making component modified parameter and objective performance parameter as basis of model modification, stable engine model was modified by establishing cost function of engine nonlinear model modification with balance equation of stable model. Comparison of modified characteristic parameter at dif⁃ferent work conditions with modified results by influence coefficient matrix method showed that accuracy of parameters modified by genetic algorithm was enhanced greatly. Stable engine model was modified by using component modified parameter. The results indicated that sensitive parameter played key role in model modification. The method is referential to engine performance model modification and model accuracy en⁃hancement.
  • 摘要：The precision of single-inclined hot-wire measuring three-dimensional velocity depends on the algorithm which can reflect the relationship between effective velocity with orientation and flow rate of airflow. Particle swarm optimization algorithm was performed to solve non-linearity least square problem based on analyzing the defects of least square method and L-M algorithm, through adjusting inertia and mutation factor to overcome the defects of traditional particle swarm optimization algorithm. The method of measuring three-dimensional velocity by using single-inclined hot-wire was developed and the compressor rotor outlet flowfield test has proved its relatively high accuracy.%　　单斜热丝技术测量三维速度场的精度，取决于能否在较大速度和角度范围内，准确有效地反映有效速度与气流大小和方向的关系。在分析最小二乘、L-M算法拟合测量数据不足的基础上，采用粒子群优化算法求解测量数据，有效解决了热线旋转角度不确定性问题，避免了实际测量计算时重新引入热线方向性误差。同时，通过动态调整惯性权重因子及引入变异因子，克服了传统粒子群算法易陷入局部极值的缺点。本文发展的单斜热丝测量三维速度场的试验数据确定方法，经压气机转子出口流场测试试验表明，该算法精度较高。
  • 摘要：Experimental research on the inter-stage performance of a multistage axial flow compressor was made. Its performance characteristics, such as the working ability at different conditions, stage pressure ra⁃tio, unsteady boundary variation law and the matching between stages with design angle and optimized an⁃gle were analyzed. The test results showed that the matching between stages can be further optimized under off-design conditions. Meanwhile, the variation of the vane angle at inlet would change the load distribution and the location of the unsteady boundary, which would cause the moving of the unsteady boundary of the compressor. It is suggested that the first and second vane angle could be enlarged appropriately to improve the flowfield of the second and third rotor to enhance the performance;at the same time, vane angle should be optimized without affecting unsteady boundary of whole compressor.%　　对某多级轴流压气机级间性能进行试验研究，详细分析了该压气机在设计角度与优化角度下，不同工况时的性能特性(包括各级做功能力、级压比和不稳定边界变化规律等)和级间匹配情况。研究结果表明，在非设计状态下各级匹配可以进一步优化、改进设计；进口静叶角度变化会改变压气机的级负荷分配和级不稳定边界位置，影响压气机不稳定边界移动。建议适当开大一、二级静叶角度，以改善二、三级转子流场，提高其性能；同时，应在不影响整台压气机不稳定边界的情况下进行静叶角度优化。
  • 摘要：某型高压压气机整体叶盘在使用过程中出现叶片裂纹故障。运用ANSYS软件对该转子叶片振动特性进行详细计算分析，并结合裂纹叶片断口宏观、微观及金相组织检查结果，找出了转子叶片裂纹产生的原因；针对故障原因，采取相应改进措施，对转子叶型及结构进行优化设计，并完成试验验证考核。结果表明，针对该叶片裂纹故障的原因分析准确，改进措施有效。%　　Blade crack occurred on a high pressure compressor blisk when it was in service. Based on nu⁃merical simulation and analysis of blade vibration characteristics using ANSYS software, and according to the inspecting results of metallurgical structure at crack cross section, the cause of the crack was found out. Accordingly, some improvement measures were taken to optimize the blade profile and structure, and test re⁃sults indicated that the employed improvement measures were effective.
  • 摘要：采用试验与数值模拟相结合的方法，研究了某超声速涡轮导向叶栅尾缘冷气喷射对叶栅流场结构的影响。数值模拟时，使用环形叶栅模型近似模拟平面叶栅内的流动。研究结果表明：数值模拟结果与试验结果吻合较好；尾缘冷气喷射可减少主气流在尾缘停滞区的能量耗损，削弱叶栅尾缘处的内边缘激波，叶栅气动效率随冷气量的增加先增大后减小；尾缘冷气喷射对叶栅出口附近气流角的周向分布有影响，但对质量平均的叶栅出口气流角基本无影响。%　　The influence of cooling jet from a supersonic turbine guide vane cascade trailing-edge on the cascade flow-field was investigated by using simulation results and test results. An annular cascade model was used to simulate the flow-field in the plane cascade approximately. The results show that the dissipation of the main stream energy in the trailing edge stagnation region and the strength of the shock wave located at the pressure side of the trailing edge can be reduced by the trailing-edge coolant jet. The aerodynamic efficiency of the cascade will increase firstly and then decrease while the coolant ejection mass ratio increases. The numerical simulation results are good agreement with test results. The circumferential distribution of flow angle located at cascade exit is influenced by trailing edge coolant ejection, while the outlet flow angle at cascade with averaged mass is not.
  • 摘要：用马尔文激光粒度测试仪对自行设计的气动雾化喷嘴的雾化特性进行了实验研究，测量了不同工况下喷雾流场的液滴粒径。根据实验结果，分析了水压、气压、气液比等因素对液滴粒径和均匀性的影响，讨论了液滴粒径随距喷口轴向距离增加的变化规律。最后，利用Fluent软件对喷雾外流场进行了三维数值仿真，其结果与实验结果吻合较好，验证了仿真方法的可行性。%　　Malvern laser particle size analyzer is used to study the spray characteristics experiment of atom⁃izing nozzle. The median volume diameter (MVD) under different conditions was measured. According to the test results, the influences of air pressure, hydraulic pressure and gas-liquid ratio to MVD and uniformi⁃ty were analyzed. Furthermore, the change of the MVD with increasing distance was discussed. The three-dimensional flow field model was built to make numerical simulation by software Fluent. The simula⁃tion results were consistent with experiment results, which indicated the feasibility of simulation.
  • 摘要：At the beginning of the 21st century, a significant change of the American force armament devel⁃opment rudder took place that the Department of Defense (DoD) determined to execute the capabili⁃ties-based planning rather than the former threats-based planning. The objective of the capabilities-based planning is to develop and maintain air, space, and information dominance on battlefields. Americas Air Force Vision 2020 is illustrative of the DoD capabilities-based planning process. It lays out the Air Force concept of operations (CONOPs): global strike, global mobility, global persistent attack, space and com⁃mand, control, communications, computers, intelligence, surveillance, and reconnaissance (space and C4ISR), and agile combat support. The missions require several propulsion capabilities:high speed turbine engine, ram/scramjet/PDE, rocket propulsion, combined cycle, and ultra efficient propulsion. Extensive re⁃search is already done in America. Great technology evolution is obtained.%　　进入21世纪，美军武器装备发展指导思想发生重大转变，放弃始于20世纪80年代基于敌对威胁的防御计划，转而实施基于敌对能力的防御计划，旨在发展和保持美国的航空、航天及信息优势。基于这一指导思想，美国空军2020年远景报告展示了美国空军未来作战概念，包括全球攻击，全球机动，全球持续打击，太空和C4ISR(指挥、控制、通讯、计算机、情报、监视和侦察)，灵活作战支持。美国已针对这些作战任务所需的高速涡轮发动机、冲压发动机、超燃冲压发动机、脉冲爆震发动机、火箭发动机、组合循环发动机和极高效推进技术，开展了大量技术研究工作，并取得重大进展。特别需要关注高速涡轮发动机和超燃冲压发动机技术发展。
  • 摘要：针对高温气冷堆(HTGR)一回路氦气轮机直接发电装置的氦气压气机中，工况最为恶劣的高压级进行性能研究。首先通过实验方法研究了高压级实验叶栅的气动性能，然后采用数值模拟的方法进一步分析其性能，给出了40%~130%设计转速的流量-压比和流量-效率特性曲线，并进行了叶栅内部流动分析。实验研究和数值模拟结果表明，此氦气压气机高压级性能较好，可应用到氦气压气机整机研制中。%　　The high-pressure stage performance of helium compressor is studied, which is used in the di⁃rect power generation device with helium turbine in the primary circuit of high temperature gas reactor (HT⁃GR). The operation conditions of high-pressure compressor are the worst in the whole helium compressor. Firstly, aerodynamic performance of the experimental cascade of high-pressure stage was studied by means of experiment method. Then, the high-pressure stage performance was further analyzed through numerical simulation. The characteristic lines of flow rate versus pressure ratio and flow rate versus efficiency were presented from 40% design rotating speed to 130% design rotating speed and the inner flow of cascade was also analyzed. The results of experiment and computation proved that the high-pressure stage has better per⁃formance and can be used to the development of helium compressor.
  • 摘要：Based on the established turbine blade parametric model, this article chose iSIGHT to optimize the temperature field of turbine blade using inner boundary conditions and to optimize heat transfer coeffi⁃cient of the structure component using geometry parameters. It successfully reduced the maximum tempera⁃ture difference of blade section by this method. This research shows some relationships among different pa⁃rameters, and would be referential for turbine blade cooling design.%　　针对某型发动机高压涡轮工作叶片，采用试验设计方法，通过对内腔边界条件的主效应分析，对涡轮叶片截面温度分布进行优化。同时，对影响叶片内腔不同流动与换热类型的冷却结构元件换热系数的几何参数进行敏度分析。最后通过综合优化，获得在原设计基础上的优化结果。结果表明，该方法可以把原设计的截面最大温差有效降低。另外，通过对涡轮叶片冷却设计优化方法的探索，还获得了影响叶片冷却设计结果的参数关系曲线，该方法及结果可在涡轮叶片冷却设计时参考使用。
  • 摘要：将ADAMS参数化分析方法应用于高压压气机调节机构方案设计中，建立了简易的机构模型，分析了机构几何参数对机构运动/动力学的影响，并对不同优化目标的多个参数进行了优化分析。结果表明，虽然与调节机构虚拟样机的仿真结果有所差异，但在方案设计阶段，参数化分析方法可快速、有效地进行调节机构结构参数优化，所建模型的运动/动力学仿真结果满足设计要求。%　　The parameterized analysis method based on ADAMS was applied to the preliminary design of the variable stator vane mechanism. Using the simple model in ADAMS, the influence of the geometric parameters of the parts was investigated and the optimization analysis was carried out. The results indicate that in spite of the difference with the outcomes of the visual prototype model, the simple model is available and effective in the preliminary design and kinematics/dynamics simulation results are acceptable.
  • 摘要：作为一家新型的为航空发动机试验与测试提供技术服务的企业，德国AneCom航空发动机试验公司集科学试验工作和测试产品开发为一体，并按市场经济运作。简要介绍了该公司的管理方式、主要业务和试验设备，浅析了其运行模式，以期为我国航空发动机试验与测试单位的管理运作提供参考。%　　The new management method, technical specialty, test equipments, and major services of Ane⁃Com AeroTest Company are introduced here. The company is able to provide technical support to test and measurement of aero-engine. Also, it integrates the scientific test and measurement product development, which operates according to the market. The operation mode of company is analyzed for reference.
  • 摘要：给出了扩展多阶多项式拟合公式及等效阶次和评定误差的算法,并利用Matlab编制了相应的拟合函数和计算函数.以此为工具,针对同一典型真实标定曲线,研究了5组28种拟合公式的拟合情况.研究表明,选用合适的正负阶次多项式拟合,可在减少计算复杂度的同时,降低拟合误差,增强拟合效果.在叶尖间隙标定精度小于0.01 mm、电压采集误差小于2.5 mV的情况下,±3阶多项式拟合为该系统标定曲线的最佳拟合方式.

    燃气涡轮试验与研究的期刊信息

    • 创刊时间：1988
    • 地区：CN
    • 语言：中文
    • 热门主题：中国航发四川燃气涡轮研究院
    • 学科分类： 航空、航天;

    燃气涡轮试验与研究的获奖情况

    • • 荣获《中文核心期刊要目总览》2011年版(即第六版)之航空,航天类核心期刊殊荣.

    燃气涡轮试验与研究的收录情况

    • • 北大核心期刊（2011版）
    • • 北大核心期刊（2014版）
    • • 北大核心期刊（2017版）

    燃气涡轮试验与研究的投稿信息

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    • 期刊栏目：模拟高空试验技术；试验与研究；设计与制造；试验设备与测试技术；综述；动态信息等
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