某航改型燃气轮机发电机组应用于 通信电源系统可行性浅析

本文通过简要介绍某航改型燃气轮机发电机组的结构组成、主要性能指标及技术水平等现状,反映出该燃气轮机发电机组能够满足通信行业标准性能参数要求及通信设备应急供电需求。对比柴油机发电机组,分析了该燃气轮机发电机组在结构性能、经济性及应用前景等方面的优势,表明了某航改型燃气轮机发电机组应用于通信电源系统更加胜任,更加符合未来发展趋势。     

联合循环FT4000的额定性能

正据《Gas Turbine World》2014~2015年年度手册报道,美国PW Power Systems于2014年推出基于FT4000航改型工业用燃气轮机组成的FT400 Swift Pac 60联合循环装置。这是该公司于1990年推出基于FT8航改型工业用燃气轮机组成的FT8 Swift Pac 30联合循环装置后,时隔24年推出的又一型基于航改型燃气轮机组成的高性能的联合循环装置。     

分布式能源用SGT-700工业型燃气轮机与 LM2500 +G4航改型燃气轮机对比分析

为推进分布式能源项目用30 MW等级燃气轮机选型工作,以Siemens公司典型工业型燃气轮机SGT-700和GE公司典型航改型燃气轮机LM2500+G4为研究对象,从结构特点、热力性能、污染物排放特性、燃料适应性、启动及运行特性、供热(冷)能力、检修维护等方面综合对比分析分布式能源用SGT-700工业型燃气轮机与LM2500+G4航改型燃气轮机的优缺点,为30 MW等级分布式能源用燃气轮机主机选型提供参考依据。LM2500+G4燃气轮机对于分布式供能方面具有一定的优势,SGT-700燃气轮机在检修维护上具有一定的优势。     

分布式能源与燃气轮机选型

针对适用的5家燃气轮机厂的主要燃机型号进行了分析比较,汇总了航改型燃机和工业重型燃机的差异,并通过工程实例的分析,给出了燃气轮机选型建议:对于分布式能源项目,采用工业重型燃机比较合适;对于调峰电厂,采用航改型燃机比较合适。     

GE公司升级改进的LM2500＋型机组

2005年10月号报道，GE公司能源航改型发动机分部宣布了第四次增加其LM2500航改型燃气轮机额定性能的技术，其机型为LM2500＋G4，它是具有更大输出功率的LM2500＋的升级改进方案。改进采用GE的航空发动机和LM6000燃气轮机的技术。     

航改和重型燃气轮机组成最佳不对称联合循环

正据《Gas Turbine World》2013年5-6月刊报道,正在提出一种独特的联合循环设计理念,使航改型燃气轮机和重型燃气轮机组合成不对称装置,可以改变加载,以便达到极好的低负荷运行特性和效率。与相当额定参数的1×1F级设计比较,使用1台100 MW的LMS100航改型燃气轮机和1台210 MW Fr7FA.05重型燃气轮机,基于2×1配置设计的422 MW联合循环装置突出的优点是:—调节     

航改型舰用燃气轮机的火用分析

利用火用分析方法对航改型舰用燃气轮机动力涡轮进行了分析和讨论,并就改型中所涉及到的对压气机、发动机的外函道的修改对整个装置的火用损失率的影响进行了分析.     

航改型舰用燃气轮机的Yong分析

利用Yong分析方法对航改型舰用燃气轮机动力涡轮进行了分析和讨论，并就改型中涉及到的对压气机，发动机的外函道的修改对整个装置的Yong损失率的影响进行了分析。     

航改燃气轮机的湿空气透平循环改型方案研究

航改燃气轮机具有压比高、效率高、可靠性高和结构紧凑等特点,它将航空发动机先进技术有效地应用于工业领域。以某型三轴航改燃气轮机为研究对象,对其不同的HAT循环改型方案进行了研究。建立了一种基于饱和曲线和工作线的饱和器模型,该模型避免使用难以准确获得的传热传质系数,利用饱和器实验数据对该模型进行了验证,结果表明:建立的饱和器模型具有较高的准确性,其中出口空气温度最大误差小于0.8%,出口湿度最大误差小于1.9%。此外,设计并仿真了3种不同结构形式的HAT循环方案,仿真结果表明:原始的压气机和透平特性不适合于改型后的HAT循环,它限制了HAT循环的效率和燃气轮机的输出功率(简称出功)。针对这一问题,提出了改进透平特性方案,该方案有效地解决了水蒸气的加入带来部件不匹配问题。在此基础上分析了3个HAT方案设计点的性能,结果表明方案2即在简单循环基础上加入了饱和器、经济器、回热器和中冷器是最佳的改型方案。     

简单循环FT4000的额定性能

正据《Gas Turbine World》2014~2015年年度手册报道,美国PW Power Systems于2012年推出由PrattWhitney的PW4000航空涡轮风扇发动机改型得到的工业用FT400燃气轮机。这是该公司于1990年推出由JT8D航空涡轮风扇发动机改型得到的工业用FT8SP30后,时隔22年推出的又一型高性能的航改型工业用燃气轮机。     

燃机选型分析

燃机发电作为占世界发电量1／5的发电方式,在世界工业发展中占据不可替代的地位,E级、F级燃机为中国燃机的主力机级,现对两种机级的性能、经济性以及电厂选级进行对比,指出无论从燃机本身的性能,还是燃气一蒸汽联合循环的性能,F级燃机均优于E级燃机,并介绍现今世界前沿的G级燃机一些睛况。     

冷却空气量对涡轮冷却性能影响综述

涡轮冷却技术被广泛应用于航空发动机及燃气轮机涡轮研发中,冷却空气的引气量成为影响整机效率的重要因素之一。本文基于现代燃气轮机及航空发动机涡轮叶片采用外部冷却与内部冷却结合的复合冷却的技术发展背景,综述了国内外在冷却空气量对涡轮叶片冷却性能影响方面的研究进展,分析并总结了冷却空气量对气膜冷却、交错肋冷却以及对综合冷却效率的影响规律,并对未来的研究方向给出了一定的建议。分析表明：对气膜孔形状的探索是未来气膜冷却技术研究的重点;交错肋研究主要处于定性研究阶段,对定量研究方法的探索是目前的发展趋势;对综合冷却效率的研究还处于起步阶段,未来可以从外部冷却和内部冷却之间的相互作用关系方面对综合冷却效率开展进一步的研究。     

燃气轮机发电机组投资成本模型

本文首先通过大量的文献调研,对现有的燃气轮机整机投资成本模型进行了分析和比较,运用最新工业数据对现有模型进行了更新。进而,总结和验证了燃气轮机成本数据随功率呈幂函数关系变化的规律,并提出了新的燃气轮机投资成本模型。在此基础之上,结合国内工程的报价和实际造价,给出了符合我国实际情况的燃用天然气的燃气轮机成本模型。最后,分析了合成气燃气轮机的改造工作和改造费用组成,并对合成气燃气轮机投资成本的发展做出预测。     

Nonlinear design-point performance adaptation approaches and their comparisons for gas turbine applications

Accurate performance simulation and understanding of gas turbine engines is very useful for gas turbine manufacturers and users alike and such a simulation normally starts from its design point. When some of the engine component parameters for an existing engine are not available, they must be estimated in order that the performance analysis can be started. Therefore, the simulated design point performance of an engine may be slightly different from its actual performance. In this paper, two nonlinear gas turbine design-point performance adaptation approaches have been presented to best estimate the unknown component parameters and match available design point engine performance, one using a nonlinear matrix inverse adaptation method and the other using a Genetic Algorithm-based adaptation approach. The advantages and disadvantages of the two adaptation methods have been compared with each other. In the approaches, the component parameters may be compressor pressure ratios and efficiencies, turbine entry temperature, turbine efficiencies, engine mass flow rate, cooling flows, and bypass ratio, etc. The engine performance parameters may be thrust and SFC for aero engines, shaft power, and thermal efficiency for industrial engines, gas path pressures, temperatures, etc. To select the most appropriate to-be-adapted component parameters, a sensitivity bar chart is used to analyze the sensitivity of all potential component parameters against the engine performance parameters. The two adaptation approaches have been applied to a model gas turbine engine. The application shows that the sensitivity bar chart is very useful in the selection of the to-be-adapted component parameters, and both adaptation approaches are able to produce good quality engine models at design point. The comparison of the two adaptation methods shows that the nonlinear matrix inverse method is faster and more accurate, while the genetic algorithm-based adaptation method is more robust but slower. Theoretically, both adaptation methods can be extended to other gas turbine engine performance modelling applications.     

Nonlinear design-point performance adaptation approaches and their comparisons for gas turbine applications

Accurate performance simulation and understanding of gas turbine engines is very useful for gas turbine manufacturers and users alike and such a simulation normally starts from its design point. When some of the engine component parameters for an existing engine are not available, they must be estimated in order that the performance analysis can be started. Therefore, the simulated design point performance of an engine may be slightly different from its actual performance. In this paper, two nonlinear gas turbine design-point performance adaptation approaches have been presented to best estimate the unknown component parameters and match available design point engine performance, one using a nonlinear matrix inverse adaptation method and the other using a Genetic Algorithm-based adaptation approach. The advantages and disadvantages of the two adaptation methods have been compared with each other. In the approaches, the component parameters may be compressor pressure ratios and efficiencies, turbine entry temperature, turbine efficiencies, engine mass flow rate, cooling flows, and by-pass ratio, etc. The engine performance parameters may be thrust and SFC for aero engines, shaft power, and thermal efficiency for industrial engines, gas path pressures, temperatures, etc. To select the most appropriate to-be-adapted component parameters, a sensitivity bar chart is used to analyze the sensitivity of all potential component parameters against the engine performance parameters. The two adaptation approaches have been applied to a model gas turbine engine. The application shows that the sensitivity bar chart is very useful in the selection of the to-be-adapted component parameters, and both adaptation approaches are able to produce good quality engine models at design point. The comparison of the two adaptation methods shows that the nonlinear matrix inverse method is faster and more accurate, while the genetic algorithm-based adaptation method is more robust but slower. Theoretically, both adaptation methods can be extended to other gas turbine engine performance modelling applications.     

GA-based design-point performance adaptation and its comparison with ICM-based approach

Accurate performance simulation and estimation of gas turbine engines is very useful for gas turbine manufacturers and users alike and such a simulation normally starts from its design-point. When some of the engine component parameters for an existing engine are not available, they must be estimated in order that the performance analysis can be started. Therefore, the simulated design-point performance of an engine may be slightly different from its actual performance. In this paper, a Genetic Algorithm (GA) based non-linear gas turbine design-point performance adaptation approach has been presented to best estimate the unknown component parameters and match available design-point engine performance. In the approach, the component parameters may be compressor pressure ratios and efficiencies, turbine entry temperature, turbine efficiencies, engine mass flow rate, cooling flows, by-pass ratio, etc. The engine performance parameters may be thrust and SFC for aero engines, shaft power and thermal efficiency for industrial engines, gas path pressures and temperatures, etc. To select the most appropriate to-be-adapted component parameters, a sensitivity analysis is used to analyze the sensitivity of all potential component parameters against the engine performance parameters. The adaptation approach has been applied to an industrial gas turbine engine to test the effectiveness of the approach. The approach has also been compared with a non-linear Influence Coefficient Matrix (ICM) based adaptation method and the advantages and disadvantages of the two adaptation methods have been compared with each other. The application shows that the sensitivity analysis is very useful in the selection of the to-be-adapted component parameters and the GA-based adaptation approach is able to produce good quality engine models at design-point. Compared with the non-linear ICM-based method, the GA-based performance adaptation method is more robust but slower in computation and relatively less accurate.     

Review of recent offshore wind power developments in china

Rapid wind power development in China has attracted worldwide attention. The huge market potential and fast development of wind turbine manufacturing capacity are making China a world leader in wind power development. In 2010, with the newly installed wind power capacity and the cumulative installed capacity, China was ranked first in the world. In 2009, China also constructed and commissioned its first large offshore wind farm near Shanghai. Following earlier papers reviewing the state of China's onshore wind industry, this paper presents a broader perspective and up‐to‐date survey of China's offshore wind power development, making comparisons between the developments in the rest of the world and China, to draw out similarities and differences and lessons for the China offshore wind industry. The paper highlights six important aspects for China's offshore wind development: economics, location, Grid connection, technological development, environmental adaptation and national policies. The authors make recommendations for mitigating some outstanding issues in these six aspects for the future development of China's offshore wind resource. Copyright © 2012 John Wiley & Sons, Ltd.     

基于SMIV-1DCNN的燃气轮机剩余使用寿命预测方法研究

为了实现船用燃气轮机剩余使用寿命的预测,对燃气轮机健康监测参数进行斯皮尔曼(Spearman)相关关系分析,采用平均影响值(Mean Impact Value, MIV)进一步分析监测参数对性能退化的敏感性,筛选出敏感特征;对得到的燃气轮机特征参数进行预处理,以消除外界环境的影响;研究了一维卷积神经网络(One Dimension Convolutional Neural Networks, 1DCNN),挖掘滑窗特征参数与运行时间的映射关系,实现燃气轮机剩余使用寿命预测。基于美国国家航天局发布的航空发动机退化数据集,验证了SMIV-1DCNN剩余使用寿命预测方法的有效性;开展了船用燃气轮机性能退化剩余使用寿命预测仿真试验。仿真试验结果表明,该方法不受燃气轮机初始状态影响,剩余使用寿命预测绝对误差56.10、平均绝对百分误差107.87、均方误差70.95,预测性能优于BP神经网络、LSTM神经网络与GRU神经网络。     

风力发电机叶片设计与气动性能仿真研究

运用叶素理论和气动理论,基于设定的风力机性能参数对风轮叶片进行三维设计。利用Gambit建模软件对风力机单叶片进行三维建模,再用Fluent软件进行风力机叶片气动性能的数值模拟,仿真叶片气动流场流态,并计算叶轮的升力、阻力和扭转力矩;验证风力机气动性能数值模拟的可行性和可靠性;计算发电机组功率和风能利用效率等性能参数。对风力发电机叶片的设计和气动数值模拟计算分析的工作可深化对风力发电机组三维叶片的气动性能的了解,仿真风力发电机组气动流场,能为风力机叶片的设计、改型和研发工作提供技术参数和指导意见。     

透平叶片干摩擦阻尼减振研究综述

利用干摩擦阻尼对叶片进行减振是一种简单而又行之有效的方法,广泛应用于航空发动机、电站汽轮机、燃气轮机等涡轮机的叶片上。结合国内外研究成果,本文从阻尼叶片结构分析模型、接触面摩擦模型、接触运动学模型、干摩擦阻尼叶片响应求解方法等几个方面来介绍该领域目前的发展状况,阐述了常见的各种模型及分析求解方法的利弊,最后展望该领域值得更进一步深入研究的几个关键问题。