船用分轴燃气轮机主要部件变工况性能的初步研究

建立燃气轮机大负荷范围、准确的变工况模型是燃气轮机热力系统建模研究的一个重要方向。其难点之一在于如何获得准确的部件变工况性能曲线。由于各种原因,一般研究人员只能获得少量的燃气轮机运行数据,因此如何利用这些数据获得准确的部件变工况性能曲线就成为需要解决的问题。在这种情况下,作者以某船用分轴燃气轮机为研究对象,利用少量运行数据对燃气轮机部件变工况通用解析解进行修正,并利用拟合的方法得到了大负荷范围内该燃气轮机主要部件较为准确的变工况性能曲线及其表达式。     

新书《燃气轮机循环与变工况性能》出版

赵士杭教授编著的《燃气轮机循环与变工况性能》一书最近由清华大学出版社出版。 该书介绍了燃气轮机的热力循环及其计算方法;燃气轮机与其他热力循环或生产过程组成的复合循环和系统;不同轴系方案燃气轮机变工况性能及其计算方法;各种因素对燃气轮机的变工况性能的影响;燃气轮机与负载的平衡运行;燃气轮机的不平衡工况等。该书内容翔实,     

PFBC联合循环中燃气轮机的变工况性能

本文以某增压流化床燃烧联合循环为例,建立了增压流化床锅炉及燃气轮机系统变工况性能计算的数学模型,并对ＰＦＢＣ系统中燃气轮机的变工况性能进行了分析。     

小偏差方法在变几何燃气轮机性能研究中的应用

为了分析不同涡轮变几何给燃气轮机性能带来的影响,基于小偏差方程提出了一种研究变几何燃气轮机性能的新方法。该方法的计算结果与特性曲线法的计算结果比较表明,新方法的计算精度在绝大多数工况下都可以保证在4%以内,如表2所示。采用该方法的计算结果表明,不同涡轮变几何可以得到不同的效果:高压涡轮和低压涡轮变几何可以很好地调节压气机的工作点,在燃气轮机改造过程中可以起到很重要的调节作用,动力涡轮变几何则可以更好地改善机组的变工况性能。     

机械传动机车燃气轮机装置变工况的计算和分析

本文对一般的分轴燃气轮机装置变工况特性作了分析,指出牵引(低压)透平阻塞边界,超导边界及空载边界形成的物理概念;指出采用透平可调喷咀和压气机可转导叶的分轴装置可进一步扩大和改善变工况性能。在此基础上,结合“哈尔滨汽轮机厂”7000马力高原机车燃气轮机装置变工况计算的实例,对机械传动的机车燃气轮机装置变工况的特点作了分叶和研究。     

双轴燃气轮机的变工况性能

本文通过变工况计算,得到了2/LL 系列和2/HH 系列双轴燃气轮机的性能曲线,在此基础上对它们的变工况性能进行了分析。最后指出,这些燃气轮机中的几种方案,今后在联合循环电站中将得到一定的应用和发展。     

有限元法计算燃气轮机叶轮温度场的研究

本文讨论了燃气轮机叶轮二维稳定与不稳定温度场的有限元计算方法,采用修正Crank-Nicolson方法离散时间项,考虑变物性的影响,推荐叶轮边界换热的准则关系式。最后,对一台国产单轴燃气轮机启动工况的叶轮温度场作了实例计算,得到了一些有用的数据和结论。     

状态监测与诊断用燃气轮机热力模型的构造方法

提出了以机组实测验收数据为估算依据,在没有详细设计参数的情况下进行机组变工况计算的建模方法,较好地解决型号平均特性与特定机组特性之间的差异问题。采用本方法对某电站单轴燃气轮机变工况性能进行了估算,计算结果与发表数据有较好的吻合,证明了该方法的有效性,可以用于燃气轮机状态监测与诊断。     

简单循环燃气轮机系统建模及其变工况性能分析

以PG6541B燃气轮机为研究对象，充分利用已公开的燃气轮机数据，探讨了简单循环燃气轮机设计工况和变工况下建模的方法。用半经验公式，对冷却空气量的分配进行了计算。利用基元叶栅法，计算得到了压气机的通用特性曲线。分析了燃烧室喷水对燃气轮机性能的影响。图7表2参9     

燃气-串级超临界CO2联合循环变工况策略研究

为优化燃气-串级超临界二氧化碳（GT-CSCO2）联合循环的变工况运行特性,建立以5.67 MW燃气轮机为原动机的GT-CSCO2联合循环模型。分别确定各设备的变工况运行方法,提出联合循环变工况运行策略,进而分析GT-CSCO2联合循环的变工况特性。研究表明：进口导叶达到最小全速角前后燃气轮机排气温度和流量随负荷变化的特性有较大改变,燃气轮机排气温度对底循环的影响大于排气压力;变工况中为维持压缩机入口温度与最终排气温度,底循环流量的减少幅度大于排气流量;负荷在100%~30%之间,GT-CSCO2联合循环热效率由54.80%降低到43.91%,净输出功率与效率约为燃气轮机单机的2倍;与简单回热结构相比,CSCO2循环具有更高的效率,是一种具有良好变工况性能的发电技术。     

轻型燃气轮机长寿命动力涡轮的结构设计

本文介绍一种长寿命动力涡轮结构的设计方法和研制结果。这种结构代替了原设计,生产制造了两台,并进行了１５０小时运行考核。测得的主要部件温度,应力数值与设计计算值基本一致,运行参数和拆检结果都表明产品达到了设计要求。该结构适用于各种固定式和移动式燃气轮机,特别是航空发动机改装的动力涡轮设计。     

ICR进展及关键技术

ＩＣＲ燃气轮机继承了简单循环燃气轮机的一系列优点,且具有优良的变工况性能。ＷＲ－２１代表了ＩＣＲ的最先进水平。本文简述了ＷＲ－２１燃气机的最新进展,对中冷器、回热器、箱装体、数字控制系统等重要部件的关键技术进行了分析。     

Gas turbine turbocharged by a steam turbine: a gas turbine solution increasing combined power plant efficiency and power

A new design of a combined-cycle gas turbine power plant CCGT with sequential combustion that increases efficiency and power output in relation to conventional CCGT plants is studied. The innovative proposal consists fundamentally in using all the power of the steam turbine to turbocharge the gas turbine. A computer program has been developed to carry out calculations and to evaluate performance over a wide range of operating conditions. The obtained results are compared with those of combined cycles where the gas turbines are not turbocharged and the gas and the steam turbines have independent power exits; the advantages of the new design are stated.     

Development of a gas turbine performance analysis program and its application

A general-purpose performance prediction program, which can simulate various types of gas turbine such as simple, recuperative, and reheat cycle engines, has been developed. A stage-stacking method has been adopted for the compressor, and a stage-by-stage model including blade cooling has been used for the turbine. The combustor model has the capability of dealing with various types of gaseous fuels. The program has been validated through simulation of various commercial gas turbines. The simulated design performance has been in good agreement with reference data for all of the gas turbines. The average deviations of the predicted performance parameters (power output, thermal efficiency, and turbine exhaust temperature) were less than 0.5% in the design simulations. The accuracy of the simulation of off-design operation was also good. The maximum root mean square deviations of the predicted off-design performance parameters from the reference data were 0.22% and 0.44% for the two simple cycle engines, 0.22% for the recuperative cycle engine, and 0.21% for the reheat cycle engine. Both the design and off-design simulations confirmed that the component models and the program structure are quite reliable for the performance prediction of various types of gas turbine cycle over a wide range of operations.     

轴流涡轮变工况性能模拟

给出了计算涡轮平均 S2流场分布和总性能的计算方法 ,并给出了计算叶片排中非设计点的损失和落后角模型 ,计算中考虑了变比热、冷气掺混的影响。针对单级和两级涡轮进行了计算分析 ,结果表明该方法可为预测已有的涡轮性能及其调试、改进提供分析工具。图 3表 1参 6     

Effect of various inlet air cooling methods on gas turbine performance

Turbine air inlet cooling is one of many available commercial methods to improve the efficiency of an existing gas turbine. The method has various configurations which could be utilized for almost all installed gas turbines. This paper presents a comparison between two commons and one novel inlet air cooling method using turbo-expanders to improve performance of a gas turbine located at the Khangiran refinery in Iran. These methods have been applied to one of the refinery gas turbines located at the Khangiran refinery in Iran. Two common air cooling methods use evaporative media or a mechanical chiller. The idea behind the novel method is to utilize the potential cooling and power capacity of the refinery natural gas pressure drop station by replacing throttling valves with a turbo-expander. The study is part of a comprehensive program with the goal of enhancing gas turbine performance at the Khangiran gas refinery. Based on the results, it is found that using turbo-expanders is the most economically feasible option and so is recommended to be utilized for improving gas turbine performance at the Khangiran refinery.     

A new approach for enhancing performance of a gas turbine (case study: Khangiran refinery)

There are various methods which are commercially available for turbine air inlet cooling aiming to improve gas turbine efficiency. In this study a new approach has been proposed to improve performance of a gas turbine. The approach has been applied to one of the Khangiran refinery gas turbines. The idea is to cool inlet air of the gas turbine by potential cooling capacity of the refinery natural-gas pressure drop station. The study is part of a comprehensive program aimed to enhance gas turbines performance of the Khangiran gas refinery. The results show that the gas turbine inlet air temperature could be reduced in range of 4–25 K and the performance could be improved in range of 1.5–5% for almost 10 months.     

SGT5-4000F燃气轮机气缸温度场及位移场分析

使用有限元方法对西门子SGT5-4000F燃气轮机气缸的温度场及位移场进行计算和分析,并把计算结果和排气扩散段金属膨胀节、透平支撑预紧量及放风冷却管路膨胀节的设计参数进行对比分析,表明采用该计算方法得到的结果对燃气轮机结构设计有一定的指导意义。