催化燃烧与旋转回热耦合的燃气轮机性能分析

低热值燃气总量巨大,种类繁多,很大一部分由于热值过低无法点火燃烧,常直接排入大气,造成能源浪费,加剧环境污染。为了利用这部分低热值燃气,提出一种催化燃烧与旋转回热耦合的新型燃气轮机系统,把催化燃烧室和高温换热器两个部件融合于一个部件中。相比传统燃气轮机,该燃机具有独特的优势:以低热值燃气为主燃料,采用催化燃烧;旋转回热保证了催化燃烧反应持续发生;结构布局更加紧凑。分析这种新型燃气轮机系统的热力循环特点,计算100 k W级新型燃机的热力性能,研究旋转周期等参数对性能的影响。结果表明:在使用甲烷浓度为2%的低浓度燃气时,透平入口温度保证在1 030~1 200 K,燃机能正常工作,从理论上证明了该新型系统是可行的;不同旋转周期之间系统运行的热力参数变化在3%以内,呈现准周期性;旋转周期之内系统运行的热力参数呈现波动变化;旋转周期减小,燃机输出功率和热效率降低,其波动性也降低。     

Investigation of nonlinear numerical mathematical model of a multiple shaft gas turbine unit

The development of numerical mathematical model to calculate both the static and dynamic characteristics of a multi-shaft gas turbine consisting of a single combustion chamber, including advanced cycle components such as intercooler and regenerator is presented in this paper. The numerical mathematical model is based on the simplified assumptions that quasi-static characteristic of turbo-machine and injector is used, total pressure loss and heat transfer relation for static calculation neglecting fuel transport time delay can be employed. The supercharger power has a cubical relation to its rotating velocity. The accuracy of each calculation is confirmed by monitoring mass and energy balances with comparative calculations for different time steps of integration. The features of the studied gas turbine scheme are the starting device with compressed air volumes and injector’s supercharging the air directly ahead of the combustion chamber.     

Comparative thermodynamic analysis on design performance characteristics of solid oxide fuel cell/gas turbine hybrid power systems

This paper presents analysis results for the hybrid power system combining a solid oxide fuel cell and a gas turbine. Two system layouts, with the major difference being the operating pressure of the fuel cell, were considered and their thermodynamic design performances were compared. Critical temperature parameters affecting the design performances of the hybrid systems were considered as constraints for the system design. In addition to energy analysis, exergy analysis has been adopted to examine the performance differences depending on system layouts and design conditions. Under a relaxed temperature constraint on the cell, the ambient pressure system exhibits relatively larger power capacity but requires both higher cell temperature and temperature rise at the cell for a given gas turbine design condition. The pressurized system utilizes the high temperature gas from the fuel cell more effectively than the ambient pressure system, and thus exhibits better efficiency. Under a restricted temperature constraint on the cell, the efficiency advantage of the pressurized system becomes manifested.     

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。     

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。     

点燃式天然气发动机燃烧室结构优化的仿真与试验研究

利用三维数值仿真的方法,对带有浴盆形燃烧室的天然气发动机缸内流动和燃烧特性进行分析,提出了两种燃烧室结构优化设计方案,试验对比了采用原燃烧室和挤气喷射燃烧室时的发动机性能。结果表明:在不改变压缩比情况下,通过改变活塞头部凸起形状和位置,能够实现浴盆形燃烧室内的挤流与滚流有效耦合;控制点火时刻的火花塞附近气体流速,能提高缸内平均湍动能,加大快速燃烧期内火焰前封面的面积,改善燃烧质量。发动机采用优化的2号挤气喷射燃烧室,能够明显加快发动机燃烧进程,提高发动机的动力性和经济性,发动机功率从75kW提高到78.7kW,最低比气耗降低4.4%,HC和CO排放略有降低。     

考虑压降的开式布雷顿CHP装置性能优化

考虑工质在流动过程中的压降不可逆性,建立开式简单布雷顿热电联产装置的有限时间热力学模型。以可用能率、火用输出率、利润率、第一定律效率和火用效率为目标研究装置的性能。通过Matlab数值计算,在无燃料消耗和装置尺寸约束下,优化了压气机进口相对压降,得到了最优可用能率、火用输出率和利润率,进一步优化压比,得到了最大火用输出率和利润率;在有约束条件下,优化压气机进口相对压降,得到了最优第一定律效率和火用效率,同时得到了各部件最佳的流通面积分配,进一步优化压比,得到了最大第一定律效率和火用效率。研究设计参数对装置最优性能的影响,发现分别存在最佳的供热温度使火用输出率、利润率和火用效率取得双重最大值。通过比较发现按最大火用输出率设计能使装置具有较大的可用能率和较低的压比,按最大利润率设计能使装置具有较大的第一定律效率和火用效率以及较低的燃料和空气消耗。     

Prediction of non-equilibrium kinetics of fuel-rich kerosene/LOX combustion in gas generator

Gas generator is the device to produce high enthalpy gases needed to drive turbo-pump system in liquid rocket engine. And, the combustion temperature in gas generator should be controlled below around 1,000K to avoid any possible thermal damages to turbine blade by using either fuel rich combustion or oxidizer rich combustion. Thus, non-equilibrium chemical reaction dominates in fuel-rich combustion of gas generator. Meanwhile, kerosene is a compounded fuel with various types of hydrocarbon elements and difficult to model the chemical kinetics. This study focuses on the prediction of the non-equilibrium reaction of fuel rich kerosene/LOX combustion with detailed kinetics developed by Dagaut using PSR (Perfectly Stirred Reactor) assumption. In Dagaut’s surrogate model for kerosene, chemical kinetics of kerosene consists of 1,592 reaction steps with 207 chemical species. Also, droplet evaporation time is taken into account in the PSR calculation by changing the residence time of droplet in the gas generator. Frenklach’s soot model was implemented along with detailed kinetics to calculate the gas properties of fuel rich combustion efflux. The results could provide very reliable and accurate numbers in the prediction of combustion gas temperature, species fraction and material properties.     

优能120纳米冷却液对油-电混动车运行热效率的影响

采用台架试验方法评估了在改变发动机进口温度、功率及转速条件下,优能120纳米冷却液对油电混动车运行热效率的影响。结果表明:温度由90℃切换至95℃时,发动机的出口温度为108℃,比参比防冻液要高9.29℃,此时平均油耗下降11.85%,最大油耗下降18.1%,发电效率提高0.52%,并且入口温度提高后其增加的油耗量仅占防冻液的20%。热机效率的提高是纳米冷却液提升了气缸工作温度,高沸点与高换热率降低了流体由于汽化产生气阻与热损失,及"发动机高温燃烧→水箱快速散热→发动机高温燃烧"周期性循环热平衡运行机制三者共同作用的结果。试验出现过热停机现象是由于发动机进口温度被恒定至设定值,故流经水箱的纳米流体的快速降温作用无法体现所致。     

Combustion and emission characteristics of HCNG in a constant volume chamber

Finding an alternative fuel and reducing environmental pollution are the main goals for future internal combustion engines. Hydrogenmethane (HCNG) is now considered an alternative fuel due to its low emission and high burning rate. An experimental study was carried out to obtain fundamental data for the combustion and emission characteristics of pre-mixed hydrogen and methane in a constant volume chamber (CVC) with various fractions of hydrogen-methane blends. A pre-mixed chamber was used to obtain a good mixture of these gases. Exhaust emissions were measured using a Horiba exhaust gas analyzer for various fractions of hydrogen-methane blends. The results showed that the rapid combustion duration was shortened, and the rate of heat release elevated as the hydrogen fraction in the fuel blend was increased. Moreover, the maximum mean gas temperature and the maximum rate of pressure rise also increased. These phenomena were attributed to the burning velocity, which increased exponentially with the increased hydrogen fraction in the fuel blend. Exhaust HC and CO₂ concentrations decreased, while NO_X emission increased with an increase in the hydrogen fraction in the fuel blend. Our results could facilitate the application of hydrogen and methane as a fuel in the current fossil hydrocarbon-based economy and the strict emission regulations in internal combustion engines.     

An experiment analysis of MILD combustion with liquid fuel spray in a combustion vessel

Mild combustion is characterized by its distinguished features, such as suppressed pollutant emission, homogeneous temperature distribution, reduced noise, and thermal stress. Recently, many studies have revealed the potential of MILD combustion in various power systems but most studies have been focused on gas phase fuel MILD combustion. Therefore, further study on MILD combustion using liquid fuel is needed for the application to a liquid-fueled gas turbine especially. In this work, we studied experimentally on the formation of liquid fuel MILD combustion under the condition of high dilution by burnt gas generated from a first premixed flame in two stages combustor which consists of the first premixed burner and secondary combustor. In particular, the effects of burnt gas velocity and oxygen level of burnt gas on the formation of liquid fuel MILD combustion were investigated. The results show that as the burnt gas velocity through the nozzle becomes higher, the color of flames was changed from yellow to pale blue and flames became very short. The OH radical measured by ICCD camera was uniformly distributed on the pale blue flame surface and its intensity was very low compared to conventional liquid diffusion flame. As burnt gas velocity is increased, local high-temperature region appeared to be diminished and the flame temperature became spatially uniform. And CO emission was sampled around 1 ppm and NOx emission was measured around 10 ppm under the overall equivalence ratio of 0.8 to 0.98 for 40 mm or less diameter of velocity control nozzle. This low NOx emission seems to be attributed to maintaining the average temperature in secondary combustor below the threshold temperature of thermal NOx formation. In view of the uniform temperature distribution, low OH radical intensity and low NOx emission data in the secondary combustor, formation of stable MILD combustion using kerosene liquid fuel could be verified at high burnt gas velocity.

     

Feasibility study of ultra-low NOx Gas turbine combustor using the RML combustion concept

A new combustion concept, the so called RML, was investigated to validate its application as a gas turbine combustor for combustor outlet temperatures over 1973 K. The feasibility study of the RML combustor was conducted with zero dimensional combustion calculations. The emission characteristics of RQL, LEAN, EGR and RML combustors were compared. The calculation results showed that the RQL combustor has lower NOx emissions than the LEAN at high outlet temperature. NOx emissions of the RML combustor at equivalence ratio of the rich chamber of 2.0 can be reduced by 30 % compared with the EGR combustor, and lower than the RQL combustor at a combustor outlet temperature over 1973 K. However, the CO emissions of the RML combustor were higher than those of the LEAN and EGR combustors. Also, the possibility of applying the RML combustor to gas turbines was discussed considering residence time, equivalence ratio of the rich chamber and recirculation rate. Although further research to design and realize the proposed RML combustor is needed, this study verified that the RML concept can be successfully used in a gas turbine combustor.

     

Ignition and combustion characteristics of the gas turbine slinger combustor

This paper describes the ignition and combustion characteristics of a gas turbine slinger combustor with rotating fuel injection system. An ignition test was performed under various airflow, temperature and pressure conditions with fuel nozzle rotational speed. From the test, there are two major factors influencing the ignition limits: the rotational speed of the fuel nozzle, and the mass flow parameter. Better ignition capability could be attained through increasing the rotational speed and air mass flow. From the spray visualization and drop size measurement, it was verified that there is a strong correlation between ignition performance and drop size distribution. Also, we performed a combustion test to determine the effects of rotational speed by measuring gas temperature and emission. The combustion efficiency was smoothly enhanced from 99% to 99.6% with increasing rotational speed. The measured pattern factor was 15% and profile factor was 3%.     

Model and field testing of a heavy-duty gas turbine combustor

The results of stand and field testing of a combustion chamber for a heavy-duty 150 MW gas turbine are discussed. The model represented one of 14 identical segments of a tubular multican combustor constructed 1∶1 scale. The model experiments were executed at a lower pressure than that in a real gas turbine. Combustion efficiency, pressure loss factor, pattern factor, liner wall temperature, flame radiation, fluctuating pressure and NOx emission were measured at partial and full loads for both model and on-site testing. The comparison of these items in the stand and field test results led to has the development of a method of calculation and the improvement of gas turbine combustors.     

混烧燃烧器关键技术研究

油气混烧燃烧器用于解决采油厂生产石油伴生气不能充分利用,造成能源浪费和环境污染的难题。混烧时伴生气、燃油组成混合燃料参与燃烧。最佳空燃比是保证混合燃料充分燃烧的关键,正是由于现场石油伴生气产量的不稳定从而导致混烧的空燃比很难确定。文中在实验的基础上,结合理论推导,在伴生气流量数列化的基础之上,得出混合燃料与空气量的函数关系,并以此作为混烧燃烧器全自动燃烧控制的基础数据。通过实例运行表明,依据所得伴生气流量数列确定的空燃比进行混烧,火焰稳定、燃烧充分,燃烧产物符合GB/T19839-2005的规定。混烧技术拓宽了燃烧器燃料选择范围,节能环保,值得推广。     

Thermodynamic analysis of a novel compact power generation and waste heat operated absorption,ejector-jet pump refrigeration cycle

An R-152a ejector-jet pump refrigeration cycle and a LiBr-H₂O absorption refrigeration cycle have been integrated with a renewable energy power generator for making a proposed ‘novel compact cogeneration cycle’. The exergy analysis of this proposed cycle leads to a possible performance improvement. Nearly 71.12% of the input exergy is destructed due to irreversibilities in the different components. The useful exergy output is around 7.12%. The exhaust exergy lost to the environment is 21.76%, which is lower than the exhaust energy lost 37.6% of the input energy, while the useful energy output is approximately 19.3%. The refrigerants used and the exhaust gas emissions samples are found to be favourable for reducing the global environmental related problems. The results also show that the coupling of the entrainment ratios of the ejector and jet pump has great effect on the exergy and energy efficiency.     

一种耦合燃气轮机的富氧燃烧系统技术经济性能分析

提出一种燃气轮机与富氧燃烧耦合的动力系统,该系统利用烟气排烟余热和锅炉内设高温受热面加热压缩空气,使其推动燃气轮机涡轮做功,用燃气轮机的压气机替代空分系统的压缩机,实现空分系统和动力系统耦合,同时燃气轮机也是烟气CO2压缩机的原动机。对新系统进行热力学与经济性分析,对应计算系统净供电效率和供电成本。结果显示当工质在锅炉高温受热面中的吸热量占燃气轮机热耗的比β为0.8、燃气轮机效率ηgt为0.32时,新型耦合系统净效率可比常规富氧燃烧系统增加4.2%,供电成本降低0.044元/(k W·h)。     

Performance test and component characteristics evaluation of a micro gas turbine

This study aims to analyze engine performance and component characteristics of a micro gas turbine based on detailed measurement of various parameters. A test facility to measure performance of a micro gas turbine was set up and performance parameters such as turbine exit temperature, exhaust gas temperature, engine inlet temperature, compressor discharge pressure and temperature, and fuel and air flow rates were measured. The net gas turbine performance (power and efficiency based on the gas turbine shaft end) was isolated and analyzed. With the aid of measurement based simulation, component characteristic parameters such as turbine inlet temperature, compressor efficiency, turbine efficiency and recuperator effectiveness were estimated. Behaviors of the estimated characteristic parameters with operating condition change were examined and sensitivities of estimated parameters to the measured parameters were analyzed.     

Analysis of combustion and flame propagation characteristics of LPG and Gasoline fuels by laser deflection method

This work is to investigate the combustion characteristics and flame propagation of the LPG (liquified petroleum gas) and gasoline fuel. In order to characterize the combustion processes of the fuels, the flame propagation and combustion characteristics were investigated by using a constant volume combustion chamber. The flame propagation of both LPG and gasoline fuels was investigated by the laser deflection method and the high-speed Schlieren photography. The result of laser deflection method show that the error of measured flame propagation speed by laser method is less than5% compared with the result of high-speed camera. The flame propagation speed of the fuel is increased with the decrease of initial pressure and the increase of initial temperature in the constant volume chamber. The results also show that the equivalence ratio has a great effect on the flame speed, combustion pressure and the combustion duration of the fuel-air mixture.     

An experimental study on spray and combustion characteristics based on fuel temperature of direct injection bio-ethanol-gasoline blending fuel

This study investigated the spray and combustion characteristics of a direct injection spark ignition type system based on the changes in the temperature of the blended fuel (with bio-ethanol and gasoline). The test was performed in a chamber with a constant volume. The diameter and width of the chamber were 86 mm and 39 mm, respectively. The bio-ethanol test fuel was blended at volume ratios of 0 %, 10 %, 20 % and 100 %. The temperature of the fuel was set as −7, 25 and 35 °C. The fuel injection pressure and ambient pressure were set as 4.5 and 0.5 MPa, respectively. The shape and characteristics of the spray were investigated through a spray experiment. The increase in the fuel temperature changed its density and viscosity; this in turn increased spray penetration and spray area and increased the bio-ethanol blending ratio. The combustion visualization and experimental analysis indicated that the decrease in the fuel temperature and the increase in the bio-ethanol blending ratio led to the high viscosity and low heating value. This resulted in an increase in the ignition delay and a decrease in the rate of heat release. It is necessary to adjust the spray strategy and ignition timing to adopt bio-ethanol blended fuel as an alternative fuel.