Evaluation of component characteristics of a reheat cycle gas turbine using measured performance data

In this work, component characteristics of a reheat cycle gas turbine in a commercial combined cycle power plant were evaluated. An inverse performance analysis, in which component characteristic parameters were estimated based on measured performance data, was carried out. The measured parameters were the power, the fuel flow rates of two combustors, and the temperatures and pressures at various locations such as the compressor discharge, exits of both the high-and low-pressure turbines. The estimated parameters from the analysis include the compressor and turbine efficiencies and the inlet air flow rate. The analysis was performed for a wide operation range in terms of the ambient temperature and load, providing a database for the variations of the characteristic parameters with changes in the operating condition. In addition, a sensitivity analysis was performed to examine the influence of the uncertainties of the measured parameters on the estimated parameters. The analysis program can be further developed into a performance diagnosis tool and the obtained component characteristic data can be used as reference database.     

Analysis of performance deterioration of a micro gas turbine and the use of neural network for predicting deteriorated component characteristics

Deteriorated performance data of a micro gas turbine were generated and the artificial neural network was applied to predict the deteriorated component characteristics. A program to simulate operation of a micro gas turbine was set up and deterioration of each component (compressor, turbine and recuperator) was modeled by changes in the component characteristic parameters such as compressor and turbine efficiency, their flow capacities and recuperator effectiveness and pressure drop. Single and double faults (degradation of single and two parameters) were simulated. The neural network was trained with a majority of the generated deterioration data. Then, the remaining data were used to check the predictability of the neural network. Given measurable performance parameters as inputs to the neural network, characteristic parameters of each component were predicted and compared with original data. The neural network produced sufficiently accurate prediction. Using a smaller number of input parameters decreased prediction accuracy. However, an acceptable accuracy was observed even without information on several input parameters. This paper was recommended for publication in revised form by Associate Editor Ohchae Kwon Mr. J. E. Yoon received his MS degree from Dept. of Mechanical Engineering, Inha University in 2008. His thesis topic was test and simulation of micro gas turbines. He has been working at LG Digital Appliance Company. Mr. J.J. Lee received his MS degree from Dept. of Mechanical Engineering, Inha University in 2006, and is now Doctoral student at the same department. His research topics include simulation and diagnosis of gas turbines. Prof. T.S. Kim received his PhD degree from Dept. of Mechanical Engineering, Seoul Na-tional University in 1995. He has been with Dept of Mechanical Engineering, Inha Univeristy since 2000, and is Associate Professor as of Oct. 2008. His research area is aero-thermodynamc simulation and test of gas turbine systems including microturbine and their components. His recent research concern also includes analysis on fuel cells and fuel cell/gas turbine hybrid systems. Prof. J.L. Shon 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 Professor as of Oct. 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.     

针对脉冲发电机突变负载的微型燃气轮机工作性能研究

为分析有动力涡轮的微型燃气轮机在带动脉冲发电机中的性能,建立带动力涡轮的微型燃气轮机数学模型.因有动力涡轮的微型燃机是由动力涡轮驱动负载,其负载变化对燃机核心机影响不大,但为了使动力段转速恢复稳定而采用的改变供油量方法会对核心机产生很大影响.基于所建立的微型燃气轮机数学模型对其进行仿真计算,研究了该燃机设计点性能参数、...     

Research on soft sensing modeling method of gas turbine’s difficult-to-measure parameters

During the operation of a gas turbine, there are many key parameters that are difficult to directly measure or to ensure measurement accuracy, which can only be measured by offline analysis methods. However, the data obtained by offline analysis has a large time lag, and it is difficult to realize real-time monitoring, control and optimization of gas turbines. In recent years, with the widespread application of data-driven methods, data-driven soft sensing technology has become a breakthrough method for online prediction of difficult-to-measure variables. Due to the time-varying nature of the gas turbine operation process, the predictive performance of the offline modeling method will inevitably degrade over time. Therefore, an adaptive soft-sensing multi-level modeling method based on the combination of the just in time learning and the ensemble learning is proposed in this paper. Taking compressor inlet air flow and turbine inlet temperature as examples, the research is carried out and verified by actual operating data. The results verify the effectiveness of the method.

     

Performance simulation of a turboprop engine for basic trainer

A performance simulation program for the turboprop engine (PT6A-62), which is the power plant of the first Korean indigenous basic trainer KT-1, was developed for performance prediction, development of an EHMS (Engine Health Monitoring System) and the flight simulator. Characteristics of components including compressors, turbines, power turbines and the constant speed propeller were required for the steady state and transient performance analysis with on and off design point analysis. In most cases, these were substituted for what scaled from similar engine components’ characteristics with the scaling law. The developed program was evaluated with the performance data provided by the engine manufacturer and with analysis results of GASTURB program, which is well known for the performance simulation of gas turbines. Performance parameters such as mass flow rate, compressor pressure ratio, fuel flow rate, specific fuel consumption and turbine inlet temperature were discussed to evaluate validity of the developed program at various cases. The first case was the sea level static standard condition and other cases were considered with various altitudes, flight velocities and part loads with the range between idle and 105% rotational speed of the gas generator. In the transient analysis, the Continuity of Mass Flow Method was utilized under the condition that mass stored between components is ignored and the flow compatibility is satisfied, and the Modified Euler Method was used for integration of the surplus torque. The transient performance analysis for various fuel schedules was performed. When the fuel step increase was considered, the overshoot of the turbine inlet temperature occurred. However, in case of ramp increase of the fuel longer than step increase of the fuel, the overshoot of the turbine inlet temperature was effectively reduced.     

Enhancement of combined cycle performance using transpiration cooling of gas turbine blades with steam

Gas/steam combined cycle is synergetic combination of Brayton cycle based topping cycle and Rankine cycle based bottoming cycle, which have capability of operating independently too. Combined cycle performance depends on the constituent cycles and it can be reasonably improved by enhancing gas cycle performance using gas turbine blade cooling. Amongst different cooling techniques the transpiration cooling offers effective utilization of coolant as compared to film cooling because of better shrouding of blade surface as the coolant is discharged from entire blade surface. The present work deals with evaluation of performance enhancement of combined cycle by using steam transpiration cooling of gas turbine blades. The combined cycle performance parameters e.g. overall efficiency and specific power output etc. have been compared for air transpiration cooling and steam transpiration cooling. The results revealed that for the specified conditions the steam is superior coolant in comparison to air and the combined cycle performance can be enhanced by applying transpiration cooling in gas turbine blades with steam as coolant. With a turbine inlet temperature of 1800 K and compressor pressure ratio of 23, the combined cycle efficiency with steam transpiration cooling of gas turbine blades is higher by 1.94 percent approximately as compared to the efficiency of combined cycle with air transpiration cooling of gas turbine blades.     

Real time linear simulation and control for small aircraft turbojet engine

The performance of the aircraft gas turbine engine requires optimization because it is directly related to overall aircraft performance. In this study, a modified DYNGEN, a nolinear dynamic simulation program with component maps of the small aircraft turbojet engine, was used to predict the overall engine performance. Response characteristics of various cases, such as 6%, 5% and 3% rpm step models and the real-time linear model of the interpolation scheme within the operating range were compared. Among them, the real time linear model was selected for the turbojet engine with nonlinear characteristics. Finally control schemes such as PI (Proportional-Integral Controller) and LQR (Linear Quadratic Regulator) were applied to optimize the engine performance. The overshoot of the turbine inlet temperature was effectively eliminated by LQR controller with the proper control gain K.     

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.

     

Influence of thermal management and integration with turbomachinery on the performance of polymer electrolyte membrane fuel cell systems

Polymer electrolyte membrane fuel cells (PEMFCs) have many good characteristics for small power sources such as low operating temperature and high power density. In this study, the effects of thermal management on the performance of PEMFC systems using natural gas fuel, and the effects of integrating PEMFC systems with turbomachines, were investigated. Firstly, performance of various system configurations differing in the thermal management of reforming and stack cooling processes was comparatively analyzed. Then, various integrated system combinations with turbomachines (compressors and turbines) were analyzed. We performed a parametric analysis of the influence of turbine inlet temperature and compressor pressure ratio on system performance, and a 10% difference in efficiency among four simple PEMFC systems was predicted. Pressurization of the PEMFC with adequate thermal management may improve system efficiency, while efficiency enhancement from corresponding simple PEMFC systems was hard to achieve in the ambient pressure integrated systems.     

Modal characteristics and fatigue strength of compressor blades

High-cycle fatigue (HCF) has been identified as one of the primary causes of gas turbine engine failure. The modal characteristics and endurance strength of a 5 MW gas turbine engine blade developed by Doosan Heavy Industries & Construction Co., Ltd. in HCF fracture were verified through analysis and tests to determine the reliability of the compressor blade. A compressor blade design procedure that considers HCF life was performed in the following order: airfoil and blade profile design, modal analysis, stress distribution test, stress endurance limit test, and fatigue life verification. This study analyzed the Campbell diagram and estimated resonance risk on the basis of the natural frequency analysis and modal test of the compressor blade to guarantee safe and operational reliability. In addition, the maximum stress point of the compressor blade was determined through stress distribution analysis and test. The bonding point of the strain gage was determined by using fatigue test. Stress endurance limit test was performed based on the results of these tests. This research compared and verified the modal characteristics and endurance strengths of the compressor blades to prevent HCF fracture, which is among the major causes of gas turbine engine damage. A fatigue life design procedure of compressor blades was established. The 5 MW class gas turbine compressor blade is well designed in terms of resonance stability and fatigue endurance limit.     

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.

     

两个高比转速离心压气机模型级的设计分析

介绍了国外两种先进的高比转速单级离心压气机的基本参数及性能参数，分析了比转速的影响，选定了国产100kw燃气轮机拟设计的离心压气机的模化点，并进行了计算与对比，分析了其设计特点，为进一步对100kw燃机压气机的设计提供了初步的数据指导。     

使用条件对民航发动机涡轮叶片蠕变寿命的影响分析

发动机使用条件及自身健康状况对涡轮叶片的实际使用寿命有重要影响。以民航发动机为对象,借助发动机性能仿真模型和拉森-米勒蠕变寿命预测模型,研究了发动机性能退化、大气温度变化以及减推力起飞对涡轮叶片蠕变寿命的影响。通过仿真实验研究发现：发动机性能衰退加速了涡轮叶片的寿命损耗,压气机效率损失3%即可导致涡轮叶片蠕变寿命减少80%;随大气温度的升高,涡轮叶片蠕变寿命呈指数规律递减;减推力起飞对涡轮叶片延寿效果比较明显,但随着推力的进一步减小,对涡轮叶片的延寿效果却不再显著。     

基于内流场分析的液力变矩器改型设计

为了提高液力变矩器的外特性,使其与发动机匹配良好,利用CFD软件对液力变矩器内流场进行三元流场数值计算和分析,在此基础上根据性能要求对原有变矩器作改型设计,改进了叶型进出口角、骨线形状和厚度分布等参数,以期得到分布合理的内流场,从而使改型后的变矩器具有符合要求的更优的外特性。改型后的液力变矩器具有更高的效率和与发动机匹配更优的泵轮容量系数,试验结果与计算结果非常吻合,改型设计效果良好。     

Dynamic test and fatigue life evaluation of compressor blades

High-cycle fatigue (HCF) has been identified as one of the primary causes of gas turbine engine failure. To verify the reliability of the high cycle fatigue fracture of the 5 MW gas turbine engine blade being developed by Doosan Heavy Industries & Construction Co., Ltd., dynamic tests were conducted using real size compressor rigs according to previous studies. The dynamic safety margin of the 5MW gas turbine engine blade was calculated on the basis of the ratio between the dynamic stress and endurance limit stress respectively determined through the compressor rig and fatigue tests. The HCF characteristics and the fatigue life stability of the DGT-5 compressor blades were verified through these processes. A fatigue life design procedure for the gas turbine compressor blade was established on the basis of the design, analysis, and test processes implemented in a previous study. In sum, the 5 MW class gas turbine compressor blades were found to be well designed in terms of resonance stability and fatigue life.     

Investigations on the effect of measurement errors on estimated combustion and performance parameters in HCCI combustion engine

Several parameters derived from heat release analysis are used for combustion diagnostics and control in internal combustion engines. It is important to tune the input parameters used in heat release calculations, in order to get correct estimation of heat release rate. In this study, tuning of input parameters is carried out by using cumulative heat release calculations of cylinder pressure during motoring. This tuning procedure uses offline iterative processing of motoring in-cylinder pressure data. The tuned parameters obtained from this method can also be utilized for online analysis of combustion parameters. Input parameters used in these investigations are intake air temperature, intake air pressure, phasing between the acquired pressure and crank angle position, compression ratio and scaling factor of heat transfer coefficient. Effect of error in these input parameters on estimated combustion and performance parameters like IMEP, combustion phasing, combustion duration, heat release rate, and maximum mean gas temperature are evaluated. The relative importance of measurement error in input parameters and its maximum expected error in the final results is analyzed in a HCCI combustion engine. Results shows that measurement errors in phasing between pressure and crank angle position, compression ratio and inlet air pressure affect estimated combustion and performance parameters significantly.     

进口轮毂比d=0.45的轴流式双级压气机试验研究

为了验证进口轮毂比d=0.45轴流式双级压气机气动性能和掌握压气机性能试验技术,本文进行了上述压气机的性能试验,测得了相对换算转速n(пр)＝0.546、0.766、0.876、1.00下压气机的特性,同时对低转速范围内压气机的喘振现象进行了观察。试验结果表明：试验所得增压比特性与理论计算十分接近,平均半径处速度三角形与设计的基本重合,只是试验的压气机效率,由于温度场的不均及用温升计算,相差较大。     

CO2跨临界制冷循环系统性能评价及Yong分析

通过用Yong分析方法对CO2跨临界制冷循环带节流阀和带膨胀机系统进行分析，发现节流阀的Yong损失较大，用膨胀机代替节流阀后，可使这部分损失降低，提高系统Yong效率。在带膨胀机的系统中，主要Yong损失发生在气体冷却器、压缩机和膨胀机，其中高压侧压力、气体冷却器出口温度以及蒸发温度对各部件的Yong损失和Yong效率都有不同程度的影响，在优化系统设计时应综合考虑这些参数。用Yong分析方法对系统性能进行评价，可为系统的改进提供理论依据。     

Influence of gas turbine specification and integration option on the performance of integrated gasification solid oxide fuel cell/gas turbine systems with CO2 capture

We investigated key design features of the integrated gasification solid oxide fuel cell/gas turbine (IG-SOFC/GT) system including carbon dioxide capture. Two different types of system configurations that depend on the carbon dioxide capture scheme (pre- and oxycombustion captures) were examined. Research focus was given to the effect of the gas turbine specification on the performance of the entire system. IG-SOFC/GT systems using two different gas turbines were analyzed, and their performances were compared. A parametric analysis was carried out to further understand the performance comparison. We found that the net system efficiency was not very sensitive to the turbine inlet temperature and the pressure ratio. As a result, similar net efficiencies were observed between the systems using two gas turbines with quite different specifications. In addition, a revision of the system layout was investigated and it was found that the power capacity of the system could be increased and the system efficiency could also be slightly enhanced by supplying nitrogen separated from the air separation unit to the fuel cell rather than to the gas turbine combustor.     

一类复杂燃气轮机循环的热力学研究

对一类复杂的燃气轮机循环进行了热力学分析和研究,导出了循环输出功、热效率、熵产和火用效率的解析式;通过数值算例,分别讨论了各个性能目标与中冷压比和总压比的关系,并对中冷压比进行了优化;分析了回热度、循环温比、压气机和涡轮机内效率、中间冷却终点温度等循环参数,对性能目标的影响,所得结果对实际燃气轮机装置的参数选择和优化设计具有一定的参考作用。