3D打印燃气轮机天然气喷嘴的流场仿真分析

开展3D打印天然气喷嘴流场仿真研究,为小型化燃气轮机控制技术的提升奠定基础.利用Solidworks、ANSYS ICEM CFD软件进行3D打印天然气喷嘴模型建模和网格划分,基于FLUENT仿真完成不同压力工况下稳态天然气喷射流场的数值模拟计算.在天然气喷嘴外流场中形成的几何回流区会随着供气压强的增大而消失,中心回流...     

某型燃气轮机寿命分析

对燃气轮机的主要转子结构件进行强度计算,选取安全系数较小的低压涡轮盘和高压涡轮盘作为低循环疲劳的基本分析对象,进行低循环疲劳试验,得出低疲劳循环值,再通过不同次循环损伤比计算以及选取寿命分散系数,得出转子件的实际循环值,最后通过工作换算计算出燃气轮机的寿命。     

Performance evaluation of a twin-shaft gas turbine engine in mechanical drive service

This study aimed at quantifying the effect of mechanical load on the performance of an 18.7 MW offshore gas turbine engine. The targeted engine is of two-shaft free power turbine configuration that operates as a mechanical driver for a process compressor in the gas compression service. The study is a part of a comprehensive performance health monitoring program to address the diagnostic and prognostic requirements in oil and gas offshore platforms and is motivated by the need to provide in-depth knowledge of the gas turbine engine performance. In this work, only the context of some design point key performance parameters and a limited set of collected operational data from the gas turbine in the real plant are available. Therefore, three major tasks, namely design point calculation, characteristic map tuning and off-design performance adaption, were needed to be performed. In order to check the validity of the proposed model, the obtained simulation results were compared with the operational data. The results indicate the maximum inaccuracy of the proposed model is 3.04 %. Finally, by employing the developed model, the engine capability for power generation when exposed to various load speeds is investigated. The obtained result demonstrates at the maximum gas generator speed, every 3 % decrease in mechanical speed leads to 1 % decline in the gas turbine power output. Moreover, when the gas turbine operates under design power load and mechanical speed is lower than 80 % of design speed, every 1 % decrease in load speed results in 0.2 % loss in thermal efficiency. The established relationship will assist proper assessment of mechanical drive gas turbines for performance health monitoring.

     

进排气压力损失耦合作用下的船用燃气轮机性能研究

基于不同的燃气轮机运行工况,获得进排气系统的压力损失变化规律。运用容积惯性法建立了三轴燃气轮机动态仿真模型,考虑船用燃气轮机进排气压力损失作用,对燃气轮机的性能进行仿真研究。数值实验结果表明:随着燃气轮机工况(其值为运行工况功率与额定工况功率之比)的增加,进排气系统的压力损失按近二次方规律增加;燃气轮机的输出功率损失也随工况增加而增大,并呈现非线性特性;热效率同样因进排气压力损失的影响而下降,但在0.8工况左右损失最大,总体也呈现非线性特性。所得结果可为燃气轮机的性能修正、运行管理和优化设计提供参考。     

涡轮流量计前导流器的结构与性能

对DN100气体涡轮流量计的关键部件之一前导流器引起的流量计压力损失进行试验测量和数值计算.对比分析两种不同结构前导流器对压力损失的影响,发现前导流器的结构变化不仅影响该部位的气流速度分布,使当地压力损失发生变化,更重要的是对后面各部件内的气体流动速度梯度和压力恢复也有明显影响,使总压损失进一步放大或减小.数值计算通过分析流动参数的变化从流动机理上解释了结构与压损间的关系.     

高压燃气涡轮叶栅热辐射特性研究

采用商用软件CFX11.0的不同湍流模型对NASA-Markll高压燃气气冷涡轮叶栅进行气热耦合换热计算,得出最佳湍流模型。针对不同涡轮叶栅前进口总温进行考虑和不考虑热辐射的数值计算,着重分析叶栅流道内热辐射效应随涡轮前入口温度的变化情况,得出在实际的高温高压气冷涡轮叶栅耦合换热计算时,辐射热流应当作为源项加入到方程中。这样能够更准确地得出叶片内部温度分布,为热应力计算以及寿命预估提供准确的边界条件。     

The effect of major parameters on simulation results of gas pipelines

Predictions of the gas temperature and pressure profiles are vital to the design and operation of gas transmission lines. Available analytical methods for the calculation of these profiles are evaluated and a numerical framework for the rigorous calculation has been developed. The predictions from both the analytical and numerical procedure have been compared to field data from the Iranian Gas Trunk-lines (IGAT). These comparisons showed that all the available methods were tuned using data obtained from small to medium diameter pipes extrapolated poorly to large diameter pipelines. In order to improve the predictions for large diameter pipelines, the effect of model parameters such as soil thermal conductivity, pipe relative roughness and velocity profile correction factor has been evaluated. The results show that temperature and pressure profiles at high Reynolds number are sensitive to the Fanning friction factor; however, thermal conductivity and velocity distribution correction factor have almost no effect on the temperature and pressure profiles provided these parameters were set at an average acceptable industry value. Since the pressure profile for large diameter pipes was most sensitive to the Fanning friction factor a parameter optimization method was used to fine-tune the Fanning friction factor as a function of Reynolds number at an average accepted industry relative pipe roughness.     

Development of a test rig for investigating the flow field around guide vanes of Francis turbines

This paper summarizes the development of a test rig containing three guide vanes of a Francis turbine, whose flow field is set up to match with that of the actual turbine. The rig is made suitable for Particle Image Velocimetry (PIV), such that the flow field around guide vanes can be measured. It has been studied that using three consecutive guide vanes in the rig give optimum results in terms of the lab capacity and having minimum influence of the wall surrounding the guide vanes. This rig also facilitates the measurements at off-designed conditions by changing the guide vane's opening angles. The flow conduits at inlet and outlet of the vanes have been optimized using CFD, to match the velocities corresponding to the turbine's design. The rig is also made suitable for testing the guide vanes with different clearance gaps. On comparing the results obtained from the experiment with CFD on the basis of velocity and pressure measurements, it is seen that the two results are comparable.     

基于整机瞬态热应力场重型燃气轮机转子的寿命评估

针对某F级重型燃气轮机,根据机组的实际运行监测数据,提取得到该机组在冷态启动、热态启动两种工况下各测点温度随时间的变化曲线,分析得到转子各处的换热边界条件,采用有限元方法计算该燃气轮机转子在不同启动工况下的整机瞬态温度场及应力场,并基于该瞬态热应力分析结果对转子的低周疲劳寿命损耗进行评估。计算结果表明：最大热弹性应力值一般都出现在透平第一级轮盘的出气侧底部圆角处及压气机后三级轮盘的中间部位的圆角区域;气流参数变化的快慢对转子应力分布影响极大;冷态启动一次的寿命损耗最高达0.02%,大于热态启动的对应值。研究结果为轮盘结构设计与机组运行规程的优化提供了重要参考。     

Influence of steam injection through exhaust heat recovery on the design performance of solid oxide fuel cell — gas turbine hybrid systems

This study analyzed the influence of steam injection on the performance of hybrid systems combining a solid oxide fuel cell and a gas turbine. Two different configurations (pressurized system and ambient pressure system) were examined and the effects of injecting steam, generated by recovering heat from the exhaust gas, on system performances were compared. Performance variations according to the design of different turbine inlet temperatures were examined. Two representative gas turbine pressure ratios were used. Without steam injection, the pressurized system generally exhibits higher system efficiency than the ambient pressure system. The steam injection augments gas turbine power, thus increasing the power capacity of the hybrid system. The power boost effect due to the steam injection is generally greater in the relatively higher pressure ratio design in both the pressurized and ambient pressure systems. The effect of the steam injection on system efficiency varies depending on system configurations and design conditions. The pressurized system hardly takes advantage of the steam injection in terms of system efficiency. On the other hand, the steam injection contributes to the efficiency improvement of the ambient pressure system in some design conditions. In particular, a higher pressure ratio provides a better chance of efficiency increase due to the steam injection. This paper was recommended for publication in revised form by Associate Editor Kyoung Doug Min Mr. S. K. Park received his MS degree from Dept of Mechanical Engineering, Inha University in 2007, and is now Doctoral student at the same department. His research topics include performance analysis of fuel cell and fuel cell/gas turbine hybrid sys-tem and advanced energy systems. Prof. T. S. Kim received his PhD degree from Dept of Mechanical Engineering, Seoul National University in 1995. He has been with Dept of Mehanical Engineering, Inha University since 2000, and is Associate Professor as of Nov. 2008. His research area includes simulation and test of gas turbines and aerodynamic performance of their components. He is also interested in researches on fuel cells and fuel cell/gas turbine hybrid systems. Prof. J. L. Sohn received his PhD degree from Dept of Mechanical Engineering, The University of Alabama in Huntsville in 1986. He has been with School of Mechanical & Aerospace Engineering, Seoul National University since 2000, and is BK Associate Proessor as of Nov. 2008. His research area is design, simulation and test of gas turbine system and components. He is also interested in researches on fuel cells and fuel cell/gas turbine hybrid systems.     

某燃气轮机高压转子—涡轮抗冲击性能研究

燃气轮机高压转子—涡轮受到冲击载荷作用时,可能会导致燃气轮机的破坏。采用Hy-perMesh对某燃气轮机高压转子—涡轮进行有限元建模,并设置了边界条件,利用三角形变化历程分别从垂向和水平方向作为冲击载荷输入,对高压转子—涡轮进行冲击动响应计算和分析,结果表明高压转子—涡轮对加速度冲击载荷的动态响应特性与冲击载荷的峰值、加载方向有关,动叶片部位是高压转子—涡轮结构抗冲击的危险区域。所得结论对燃气轮机抗冲击方面的研究具有一定的参考价值。     

Parametric simulation and performance analysis of a solar gas turbine power plant from thermodynamic and exergy perspectives

Using solar energy in gas turbine cycles is a new method that can improves the efficiency of gas turbines. Placing a solar receiver before a combustion chamber can raise the temperature of the air coming into the chamber and reduce the consumption of fuel in the chamber. The system that combines a solar energy receiver with a gas turbine cycle is technically called a “solar gas turbine”. The goal of this paper is the parametric simulation and performance analysis of a gas turbine cycle equipped with a solar receiver from thermodynamic and exergy aspects of view. The selected parameters in this study, include the pressure ratio of compressor, the temperature of gases at the turbine inlet and the direct normal irradiance. The obtained results indicate that the fuel consumption of this combined system is reduced by using a solar receiver and the temperature of gases entering the combustion chamber increased. The reduction of consumed fuel, in turn, reduces the rate of exergy destruction in the combustion chamber. Another important point is that the solar receiver itself has the least amount of exergy destruction. The net power generated by a solar gas turbine cycle is 10 % higher than that produced by a simple gas turbine cycle. Also, the studies show that the electrical efficiency of a solar gas turbine cycle is about 41 % higher than the simple gas turbine cycle.

     

Robust model of a transient wind tunnel for off-design aerothermal testing of turbomachinery

Short duration wind tunnels offer an economical approach to study the aero-thermal operation of propulsion components, while reproducing temperature ratios, Reynolds and Mach numbers of the actual engine conditions. The present paper aims at modeling with high fidelity the von Karman Institute compression tube facility. This wind tunnel was simulated using the EcosimPro suite to characterize the behavior of each subcomponent during the whole test envelope, including the turbine map at off-design. The numerical predictions were then assessed through the comparison with experimental data. The model was proven to be an effective tool to accurately evaluate all the operating regimes that a research turbine experienced during the experimental sequence. Consequently, the present model allows exploiting the complete test run duration to obtain unique experimental data from the turbomachinery operating at far off-design conditions. The capability to experimentally test components at off-design is fundamental to understand the flow physics of any gas turbine engine operating at extreme conditions and to characterize the transient performances of fluid-machinery in high-speed propulsion concepts. However, technical dissemination on these aspects is scarce.     

重型燃气轮机支承座热态自适应对中机理

透平端支承是重型燃气轮机轴系设计中的重要组成部分。基于流固耦合的有限元法研究切向支承座的热态自适应对中机理。运用Pro/Engineer软件分别建立切向支承、扩压器、高温燃气和冷却气体的3维模型。然后结合支承座的结构特点和流体的物性参数,通过定义流固耦合接触界面,进行计算流体动力学(Computational fluid dynamics, CFD)计算,最后将得到的固体温度场作为热载荷传递到ANSYS软件中进行结构分析,得到切向支承的热变形和热应力场,并选取支承座8个检测点的变形量进行对比。结果表明,机座在热载荷下产生的变形通过切向支承板使轴承座发生强制性旋转,从而减小了中心标高的偏离,实现了热态下的自适应对中,为今后支承座的优化设计和试验研究提供了重要参考依据。     

CAN总线型智能涡轮流量计

针对涡轮流量计的工作要求和CAN现场总线的应用状况,介绍了以STC89C52RD单片机为核心,采用涡轮流量计、压力和温度传感器及CAN总线控制器等构成的CAN总线型智能涡轮流量计的软硬件设计。这种CAN总线型智能涡轮流量计能通过温压补偿实现对气体流量的准确测量与现场显示,可方便地与CAN总线网络进行挂接,实现基于CAN总线的远程监测。     

某型伺服引气阀蝶阀压力损失分析

蝶阀作为伺服引气阀的主阀,其压力损失特性对于伺服引气阀的工作效率、流量控制精度以及下游涡轮起动机性能至关重要。建立了蝶阀压力损失计算的数学模型;通过计算流体力学数值计算方法获取了蝶阀流场总压分布情况,得到了不同工作环境和开启角度时的蝶板压力损失情况。结果表明,供气压力的升高增大了蝶阀压力损失,但不改变蝶阀和涡轮起动机上的压降分配比例;而蝶阀压力损失不受供气温度的影响。对海平面下不同开启角度的蝶阀压力损失进行了试验测试,验证了数学模型及数值计算结果的正确性。     

Uncertainty estimation in calibration of instruments of model turbine test facility

The experimental testing of the reduced scale model turbine is an important phase to obtain the performance characteristics of the prototype because the characteristics are difficult to obtain from theoretical calculations. A specially designed hydraulic test facility following the guidelines of international standards is generally used to obtain the performance characteristics of model turbine. These characteristics are transposable to the prototype turbines. The model turbine test facility is also used for the research and development work by the designers and scientists. The accuracy of the results obtained is entirely dependent on the instrumentation, calibration and uncertainty estimation. In the present study, the instrumentation and calibration procedure of a model Francis turbine test facility is presented by following the guidelines of international electrotechnical commission. The instruments such as flow meter, inlet and differential pressure transducers, torque sensors, angular position sensors and temperature sensors are calibrated using primary and secondary methods. The calibration curves and uncertainties involved in different instruments are obtained and presented. Both systematic and random uncertainties involved in hydraulic efficiency measurements are also presented. The maximum total uncertainty is ±0.15% in the hydraulic efficiency of model Francis turbine at best efficiency point.     

CFD在涡轮钻具机械性能预测分析中的应用

文中采用实体建模、CFD前置处理器等工具真实、准确地建立涡轮定、转子单周期跨叶片流道计算模型,应用CFD(计算流体动力学)技术研究分析了其在不同转速下的内流场。对模拟出的涡轮叶栅内流场,重点分析了转子叶片表面压力场的分布情况,并将模拟结果与十级涡轮台架的实验数据进行了对比,证明了应用CFD技术对涡轮钻具叶栅内流场模拟分析的有效性,为涡轮钻具机械性能预测分析提供了一种有力的技术手段。     

A study on an axial-type 2-D turbine blade shape for reducing the blade profile loss

Losses on the turbine consist of the mechanical loss, tip clearance loss, secondary flow loss and blade profile loss etc.,. More than 60 % of total losses on the turbine is generated by the two latter loss mechanisms. These losses are directly related with the reduction of turbine efficiency. In order to provide a new design methodology for reducing losses and increasing turbine efficiency, a two-dimensional axial-type turbine blade shape is modified by the optimization process with two-dimensional compressible flow analysis codes, which are validated by the experimental results on the VKI turbine blade. A turbine blade profile is selected at the mean radius of turbine rotor using on a heavy duty gas turbine, and optimized at the operating condition. Shape parameters, which are employed to change the blade shape, are applied as design variables in the optimization process. Aerodynamic, mechanical and geometric constraints are imposed to ensure that the optimized profile meets all engineering restrict conditions. The objective function is the pitchwise area averaged total pressure at the 30 % axial chord downstream from the trailing edge. 13 design variables are chosen for blade shape modification. A 10.8 % reduction of total pressure loss on the turbine rotor is achieved by this process, which is same as a more than 1 % total-to-total efficiency increase. The computed results are compared with those using 11 design variables, and show that optimized results depend heavily on the accuracy of blade design.     

气体涡轮流量计性能优化的模拟与实验研究

以TRZ80气体涡轮流量计为研究对象,采用数值模拟与实验测试相结合的方法,提出了前整流器和后导流体的结构优化方案。通过对结构优化前后流量内部流场特征的分析,揭示了流量计结构与性能优化背后确切的流体力学机制。研究结果表明：前整流器和后导流体区域的压降突变与后导流体尾部的涡旋结构和回流现象是影响流量计计量性能的主要机制。优化的流量计结构可以明显减弱压降突变、涡旋结构与回流现象。优化的流量计结构既可以显著降低流量计的压力损失,又可以明显提高流量计的测量精度与稳定性,其压力损失和线性度误差分别降低了约48.58%和32.43%。研究结果有助于为今后开发与量产计量性能更好的气体涡轮流量计提供理论指导和技术支持。