基妻相似理论估算PFBC—CC燃气轮机变工况性能

文章基于相似理论方法分析燃气轮机变工况性能,提出采用一流量修正系数修正参考工况点的无因次准则数,用来模拟燃气轮机共同工作线,并对一增压流化床联合循环电站的燃气轮机机组由于环境状况和负荷要求变化引起的变工况分别作了示例计算,结果表明本方法可以用作缺乏设备详细性能特性时,燃气轮机变工况性能的近似估算。     

PG9171E型燃气轮机变工况计算模型的建立

为了建立PG9171E型燃气轮机变工况计算模型,必须根据电厂提供的原始数据建立该机型的压气机特性.由于现有基线估算方法的建立未包含高压比压气机实验数据.故一般只被应用于压比小于11的压气机特性估算,而PG9171E型燃气轮机的压气机压比已接近12.为了解决这个问题,在压气机特性计算过程中首次提出分段计算法,计算结果表明:该方法的精度能够满足实际应用要求.在变工况计算模型的燃气热力性质计算方面,根据热力性质表[2].归纳出空气、CH2燃气、C燃气和水蒸气的热力性质通用关系式,简化了燃烧室燃用重油时的湿燃气焓值和对数压比值的计算过程,变工况计算模型的计算结果与燃气轮机实测参数进行比较,表明上述改进方法在实际应用中能够满足建模精度的要求.     

MS6001燃气轮机特性计算及安全监测评估系统软件实现

以从法国引进的MS6001燃气轮机发电机组为研究对象,开发了1套以燃气轮机循环计算、压气机和涡轮特性计算及燃气轮机变工况计算为基础的工况监控显示系统软件。该软件的开发有利于提高燃气轮机系统运行的管理水平,为全面实施燃气轮机机组的智能监控和诊断打下坚实的基础。图4表1参5     

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。     

不同运行工况下给水加热器端差特性的计算分析

给水加热器端差性能,随机组运行工况的变化而变化。对ASME加热器性能试验标准中采用的加热器性能计算方法进行了介绍,并对利用这种方法进行加热器端差性能的变工况计算进行了说明。针对某一国外机组提供的加热器变工况特性进行了核算,计算结果表明,采用ASME标准中提供的方法进行加热器性能变工况计算后得到的结果,与厂家提供的性能特性能较好的吻合。采用的方法在计算加热器特性时有明显的优势。     

跨音速透平特性计算

在分析及计算燃气轮机装置变工况性能时,需要知道透平特性。利用综合的试验数据定性地估算多级跨音速透平特性是一种最简便的方法。本文主要介绍多级跨音速透平特性计算的程序设计,对计算方法和损失模型只作一般讨论。文末,结合实例,对JB公司PG5331燃气透平及斯贝发动机高压透平进行了计算。本程序在DIS—21型电子计算机上计算一个二级跨音速透平特性约一小时。     

某F级重型燃气轮机启动过程仿真研究

基于MATLAB/SIMULINK仿真平台,采用模块化建模方法建立了重型燃气轮机非线性仿真模型以及启动过程中启动升速、转速/功率与压气机进口可转导叶开度(IGV)温度控制等关键控制器仿真模型。以某F级重型燃气轮机机组为研究对象,对设计工况与启动加载过程进行了仿真计算与分析,结果表明,所搭建的燃气轮机瞬态仿真模型不仅在设计工况下具有较好的仿真精度,还可以对燃气轮机启动过程进行较好的仿真模拟,在机组瞬态过程运行特性分析与预测,控制系统的调试与优化以及系统与设备的故障诊断等方面均具有实际的工程意义。     

考虑冷气掺混的重型燃气轮机变工况运行的精细建模及特性分析

为了研究全工况下燃气轮机内部运行参数及其所具有的特性规律,以PG9351FA燃机为分析对象,建立具有冷气掺混的重型燃气轮机变工况运行精细模型。该模型采用半经验公式对燃机冷却空气掺混量进行估算,充分考虑了冷气掺混对透平性能的影响,以及马赫数、攻角对透平变工况运行时造成的气流参数变化及速度损失的修正。结果显示:所建模型的精度有所提高,利用其计算所得结果与厂家提供数据相比,数据误差可控制在±0.4%以内,可用于预估燃机在部分负荷工况下的运行特性。应用模型分析了透平背压变动对透平膨胀比分配、排气温度及输出功率(出功)的影响,得到了透平内部气体流动参数和性能参数以及分级特性规律,其结果更真实地反映了机组在特定运行策略是的全工况特性规律。     

燃气轮机涡轮特性计算方法

介绍一种计算燃气轮机涡轮变工况特性的方法，给出了主要公式、主要公式的推导、计算表格和气体动力函数的主要公式。采用气体动力函数为工具便于实现计算机编程。特性用折合参数形式表达，可通用于涡轮各种工况。与压气机特性一起可完成燃气轮机联合工作线计算，确定启动过程和变负荷特性，对于设计新的燃气轮机和研究在运的燃气轮机是必不可少的。本方法曾用于工厂燃气轮机设计计算。     

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     

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.     

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.     

Extensible object model for gas turbine engine simulation

This paper presents an extensible object model for gas turbine engine performance simulation. The extension method for gas path balancing is analyzed and a new design rationale is developed to overcome deficiencies of the traditional component-based object modeling method. A class framework implementing this rationale is described and the dynamic performance of a three-shaft gas turbine engine is simulated to evaluate the model’s effectiveness.     

Thermal performance analysis of gas turbine engines based on different compressor configurations

In this study, the performance of several gas turbine engines has been investigated using computational modelling based on the actual manufacturer's data. Further, the study focuses on evaluating the impact of varying the configuration of the compressor on overall engine performance based on the first and second laws of thermodynamics. The results confirm that the main source of irreversibilities occurs in the combustion chamber in all cases. The exergetic efficiency of the gas turbine engine significantly varies with compressor configurations, type of compressors, load variation, climatic condition, and isentropic efficiency. The engine capacity and high‐pressure turbine inlet temperature govern the gas turbine performance, and higher values are more favourable. The gas turbine exergetic efficiency drops off when the power setting adjusted at part‐load and at high ambient temperature. The most optimal gas turbine performance is located at the single axial compressor case, followed by the axial‐centrifugal compressor and then the centrifugal–centrifugal compressor.     

三压再热汽水系统IGCC的设计工况和变工况性能

以三压再热式汽水系统ＩＧＣＣ（整体煤气化燃气－蒸汽联合循环）为研究对象组成了整体空分ＩＧＣＣ系统方案,建立了气化炉,净化系统,燃气轮机,空分装置,余热锅炉,汽轮机各组成部件的数学模型,对ＩＧＣＣ系统的设计工况和变工况特性进行计算,分析了煤气轮机采用不同调节规律和汽轮机采用不同运行方式时对系统变工况性能的影响并提出了合理的运行方式。     

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.     

燃气轮机排气管的流场研究及改进

结合某型机组船用化改装任务,分别对A型及B型机组排气管进行多种方案的模型试验,分析了排气管出口及气流转弯导流片对其性能的影响。证明了在其结构尺寸配合恰当的情况下,采用导流片乃为进一步改进其性能的一种行之有效的方法。本文还对排气管运行时其结构可靠性进行了探讨与分析。     

Gas turbine performance prognostic for condition-based maintenance

Gas turbine engines experience degradations over time that cause great concern to gas turbine users on engine reliability, availability and operating costs. Gas turbine diagnostics and prognostics is one of the key technologies to enable the move from time-scheduled maintenance to condition-based maintenance in order to improve engine reliability and availability and reduce life cycle costs. This paper describes a prognostic approach to estimate the remaining useful life of gas turbine engines before their next major overhaul based on historical health information. A combined regression techniques, including both linear and quadratic models, is proposed to predict the remaining useful life of gas turbine engines. A statistic “compatibility check” is used to determine the transition point from a linear regression to a quadratic regression. The developed prognostic approach has been applied to a model gas turbine engine similar to Rolls-Royce industrial gas turbine AVON 1535 implemented with compressor degradation over time. The analysis shows that the developed prognostic approach has a great potential to provide an estimation of engine remaining useful life before next major overhaul for gas turbine engines experiencing a typical soft degradation.