共查询到18条相似文献,搜索用时 156 毫秒
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在燃气-蒸汽联合循环机组中,燃气轮机在不同工况下的排烟温度不同,使得整个燃气轮机联合循环机组启动过程主蒸汽温度波动频繁,从而引起汽轮机启动过程中各金属部件温差增大,热应力和热变形也随着增加。GE公司的6F.03燃气轮机的温度匹配功能和汽轮机热应力计算监控模块相结合,可以通过实时控制主蒸汽温度实现对汽轮机转子热应力的有效监视和控制,减少设备损坏。 相似文献
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以30 kW燃气轮机发电机组为研究对象,基于MATLAB/Simulink平台搭建了微型燃气轮机发电机组各部件及系统仿真模型,研究了微型燃气轮机、发电机和电力变换装置的控制策略。考虑了电力变换过程的损耗影响,设计了微型燃气轮机发电机组的“机-网”功率匹配控制策略。研究了负荷大幅度阶跃突变时“机-电”动态变换规律和功率匹配特征,采用模糊PID控制改善了机组的动态响应特性。结果表明:燃气轮机负载从30 kW突降至15 kW的过程中,模糊PID控制体现出较好的控制性能。相比常规PID控制机组的暂态过程震荡幅度明显减小,其发电功率的稳定速度提高了24.5%,电功率的超调减小9.6%,转速变化更加平缓,透平入口温度的震荡幅度减小20.7%,机组功率因数的恢复速度提高36.0%。 相似文献
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针对某型发电燃气轮机在负载突变过程中可转导叶角度与压气机转速互相耦合、控制失稳的问题,提出了“功率前馈”控制策略——即根据负载功率对可转导叶角度进行调整。首先,通过粒子群寻优算法,将压气机喘振裕度作为目标,对不同工况下的导叶角度进行寻优匹配;其次,采用“功率前馈”对燃气轮机突增负荷和甩负荷过程中的导叶角度进行调节;最后,以船用发电型间冷燃气轮机为研究对象,建立三转子燃气轮机整机模型,针对突变工况过程可转导叶角度的控制规律开展研究。结果表明:采用“功率前馈”控制模式,在突增负荷过程中,动力涡轮转速超调量减小11%,高压涡轮进口温度降低了3%;在甩负荷过程中动力涡轮转速超调量减少10%,高压涡轮进口温度超调量降低11.9%,低压压气机最小喘振裕度由0.87%提高至9.1%。 相似文献
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燃气轮机加减速过程通常采用核心机升转速率控制,优点是加速时间稳定,测量参数精度高。随着用户对机动性要求变高,基于升转速率的控制模型无法识别燃气轮机状态,给燃气轮机加减速过程带来风险。航空发动机依据各部件间的相互匹配关系,采用油压比进行加减速控制,具备快速加减速的能力。根据燃气轮机相似原理,提出一种基于瞬态过程的各部件之间流量平衡方法,计算燃气轮机加减速供油规律。理论分析及仿真验证表明,基于油压比的控制模式能够识别燃气轮机工作状态,控制模式与升转速率控制方法相比更优。研究成果可为燃气轮机瞬态控制规律设计提供参考。 相似文献
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燃气轮机进口可转导叶(IGV)控制是燃气轮机安全经济运行的基础,也是燃气轮机控制中的难点。文中从IGV的工作机理出发,深入分析了燃气轮机运行全过程中,IGV控制对喘振防止、排气温度降低和压气机耗功降低的重要作用。同时,给出了燃气轮机启停和正常运行工况时的IGV控制策略。 相似文献
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As the need for clean coal technology grows, research and development efforts for integrated gasification combined cycle (IGCC) plants have increased worldwide. An IGCC plant couples a gas turbine with a gasification block. Various technical issues exist in designing the entire system. Among these issues, the matching between the gas turbine and the air separation unit is especially important. In particular, the operating condition of a gas turbine in an IGCC plant may be very different from that of its original design. In this study, we analyzed the impact of the use of syngas on operating conditions of the gas turbine in an IGCC plant. We evaluated the performance of a gas turbine under operating limitations in terms of compressor surge and turbine metal temperature. Although a lower degree of integration may theoretically allow higher gas turbine power output and efficiency, it causes a reduction in compressor surge margin and overheating of the turbine metal. The turbine overheating problem may be solved using several methods, such as a reduction in the firing temperature or an increase in the turbine cooling air. The latter yields a much smaller performance penalty. To achieve an acceptable margin for the compressor surge, either further reduction in the firing temperature or further increase in the coolant is required. Ventilation of some of the nitrogen generated by the air separation unit, i.e., a reduction of the nitrogen supply to the combustor, is another option. Coolant modulation yields the lowest performance penalty. Reduction of the nitrogen supply provides much greater system power output than control of the firing temperature. For nitrogen flow and firing temperature controls, there are optimal levels of integration degrees in terms of net system power output and efficiency. 相似文献
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西气东输工程燃气轮机驱动压缩机组控制系统负荷控制功能不完善,造成机组在压力自动控制模式下,燃机、压缩机的转速和排气温度等重要参数在运行过程中极不稳定,并呈现周期性振动特性,对燃机重要部件造成严重的低周疲劳损伤。本文对机组的控制方式进行了研究,分析了机组功率、转速、排气温度波动的机理,通过合理调整控制器参数解决了机组关键参数波动的问题,显著改善了机组的运行稳定性和可靠性,对于提高机组的使用寿命、降低热部件的疲劳损耗具有主要作用。所做工作对机组控制系统的设计和调整具有参考价值。 相似文献
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在燃机运行过程中对排温度分散度的监视非常重要。本文分析了造成排烟温度分散度大的一般原因,阐述了排烟温度分散度大对燃机热部件的危害,同时还对控制系统中排烟温度分散度允许值的计算方法进行了简单的说明,最后对在运行过程中如何对排烟温度分散度进行监视进行了说明。 相似文献
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F. Haglind 《Energy》2010
The part-load performance of gas and steam turbine combined cycles intended for naval use is of great importance, and it is influenced by the gas turbine configuration and load control strategy. This paper is aimed at quantifying the effects of variable geometry on the gas turbine part-load performance. Subsequently, in another paper, the effects of variable geometry on the part-load performance for combined cycles used for ship propulsion will be presented. Moreover, this paper is aimed at developing methodologies and deriving models for part-load simulations suitable for energy system analysis of various components within gas turbines. Two different gas turbine configurations are studied, a two-shaft aero-derivative configuration and a single-shaft industrial configuration. When both gas turbine configurations are running in part-load using fuel flow control, the results indicate better part-load performance for the two-shaft gas turbine. Reducing the load this way is accompanied by a much larger decrease in exhaust gas temperature for the single-shaft gas turbine than for the two-shaft configuration. As used here, the results suggest that variable geometry generally deteriorates the gas turbine part-load performance. 相似文献