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1、1,【】 三 菱 燃 气 轮 机 技术人员培训资料,June, 2005,2,目录,1.概述 2.燃气轮机的性能 3.三菱燃气轮机构造上的特点 4.M701F燃气轮机的详细结构 5.材料 6.透平内叶片的冷却技术 7.冷却系统 高速冷却,3,1.性能表,4,三菱燃汽轮机的高性能化,5,有效的结构设计,Torque Pins Between Compressor Disks 压气机叶轮之间的传扭小圆柱,在透平之间的 齿状耦合 Curvic Coupling Between Turbine Disks,切向支撑结构 Tangential Strut,Easy Blade Exchange 动叶换装
2、容易的叶根结构,External Cooler for Rotor Cooling Air 用于冷却轴系的外部冷却系统,Cold End Drive 低温部的轴动力驱动装置,6,F型燃气轮机,7,燃气轮机的性能,第2章,8,燃气轮机的原理,9,燃气轮机的构成简图,10,燃气轮机循环性能,11,大气温度对燃机的影响,12,三菱燃气轮机构造上的特点,第3章,13,燃气轮机的基本结构,14,经过长验证的可靠性设计,特 点,D 型,F型,G型,H型,驱动轴 低温端,双轴承支撑,4級透平,多支型燃烧器,机匣 水平分离结构,第一级静叶 单片组装构造,轴系冷却方式 (经外部制冷和除尘后再导入),蒸汽 冷却,
3、D 型, 型, 型, 型,15,“F” 型燃气轮机的设计特点 (1/3),16,PROVEN FEATURES,Curvic Coupling,Spindle Bolt,Disc,“F” 型燃气轮机的设计特点 (2/3),17,PROVEN FEATURES,ROTOR COOLING,“F” 型燃气轮机的设计特点 (3/3),18,三菱燃气轮机的详细结构,第4章,19,进气缸部分,20,进气导叶的机械原理,21,22,推力轴承的结构,主推力,转子旋转方向,推力瓦,隔离圈,喷嘴,转子 推力盘,水平板,为了防止组装错误，发电机侧和燃机侧的轴瓦和喷油嘴的尺寸均不同。参见图5 止推轴承。,图5 止推
4、轴承,23,支撑轴承的结构,24,密封,25,压气机组件,26,压气机气缸,#14 Bleed Manifold,27,压气机气缸,压气机气缸是分两半制造的铸钢件，在水平中分面处用螺栓固定。这样组成一个易于拆卸、组装、检查和维护的组件。压气机气缸装有压气机隔板和第6、11和14级压气机抽气口。抽出的空气用于冷却和密封以及用作机组启动和停止时的防喘控制措施,28,压气机的隔离环,29,压气机转子,30,压气机动叶结构与安装图,压气机叶片由不锈钢制成，这为所有的振动模态提供了阻尼。“燕尾”式叶根设计为切向主振型提供了根部阻尼。关于燕尾形的布置，参见图。叶片用键在主轴上固定，使得在不影响其它级的情况
5、下拆卸任一级。转子组件有17列叶片。它们用于压缩进气，以提供所需的气流和压力。 压气机叶片 定位键 燕尾形叶根 压气机轮盘,31,燃烧器部分 (干式低 NOx 型燃烧器),Pilot Nozzle,Pilot Nozzle Swirler,32,燃烧筒的分布 (干式低 NOx 型),33,点火装置和火焰探测器的位置,点火装置,火焰探测器,34,燃烧器的内筒 (干式低 NOx 型),35,燃料喷嘴 (低 Nox型),36,燃烧器的尾筒 (干式低 NOx 型),37,火炎联接管,38,旁路阀 (1/2),39,旁路阀 (2/2),40,透平缸的组装,41,透平静叶的组装,42,透平孔探测仪开孔和热
6、电偶,43,力矩管的密封,44,压气机 / 透平内段的密封结构,45,弹性支撑,46,Exhaust Casing,Exhaust Diffuser,排气缸和切向筋的结构,Brg. box,Brg. Oil Supply,Thermocouples for Blade pass temperature measurement,47,排气总缸结构,48,燃气轮机的转子,49,压气机动叶组装,50,透平转子的组装,51,第5章,材 料,52,燃气轮机中所使用的主要材料,53,透平动叶材料,54,透平静叶材料,55,燃烧器材料,56,CoNiCrAIY涂层,57,隔热涂层 (TBC),58,涂层结构
7、,59,第6章,透平内叶片的冷却技术,60,M701F型备有冷却机能的动叶与静叶,61,透平初温的发展,62,三菱高效率燃气轮机的趋势图,63,高温透平的技术,M701F,M701D,64,耐高温材料的发展趋势图,65,透平冷却静叶的发展,501F/701F,501D/701D,66,透平冷却动叶的发展,501F/701F,501D/701D,67,隔热涂层 (TBC),68,先进的透平冷却技术,M701F,M701D,M701F,M701D,69,冷却型式,70,薄膜冷却,71,分流型冷却,72,冲击冷却,73,绕流型冷却,Turbulator,74,第一级静叶,75,第一级动叶,Showe
8、r Head Film Cooling,Pin Fin Cooling,76,第二级静叶,77,第二级动叶,Slot hole,Turbulator,Cooling Air,78,第三级静叶,79,第三级动叶,80,第四级静叶,81,第四级动叶,82,第7章,冷却系统,83,冷却气体系统,84,冷却气体的流向,85,透平转子内的空气流向,TURBINE ROTOR COOLING AIR FLOW,86,透平内密封空气流向,87,透平外密封空气流向,PREVENTION OF HOT GAS REVERSE FLOW,88,1. 对动静叶的冷却型式是高效率燃气轮机的主要的技术之一 2.更先进的
9、冷却体系是作为提高透平初温的必然条件,结论,89, 学员选修,高 速 冷 却,90,Characteristics of blade tip clearance,A. Characteristics of tip clearance are estimated for the entire operational conditions including cold start and very hot start. B. Reduction of clearance is observed at compressor blade ring right and left side while t
10、he engine restarts under very hot condition due to oval deformation (). C. Reduction of clearance is observed at turbine casing bottom side during re-starting due to “cat back” deformation ().,: “Cat back“ deformation (Turbine side clearance is critical.),: Oval deformation (Compressor side clearanc
11、e is critical.),Rotor,Blade ring,Rotor,Casing,Bottom side Clearance,91,Oval deformation of compressor blade ring at rear stage,Compressor Blade Ring,Just after the shut down of GT, the rear stage compressor blade ring is shrunk rapidly accompanied with oval deformation due to rapid cooling. The rear
12、 stage compressor tip clearance each at right and left becomes critical due to the oval deformation. If the GT is re-started or spin under such a condition, rubbing is anticipated. Therefore, it is strongly recommended to re-start or spin the GT after 1 hour when rapid shrinkage is recovered.,92,“Ca
13、t back” deformation of the gas turbine casing,“Cat back” deformation of the gas turbine casing is caused by the casing metal temperature gradient between top and bottom halves. The casing metal temperature gradient is caused by natural convection. Hot air inside the casing is convected upward. Natur
14、al convection inside the casing occurs after shut down of the gas turbine (GT). After a while if the GT is restarted, minimum clearance occurs at bottom side due to the distortion.,93,Countermeasure,In order to reduce the casing thermal distortion, it is recommended to carry out the spin cooling ope
15、ration after gas turbine shut down. In order to monitor the casing metal temperature difference after shut down and to optimize the spin cooling procedure, thermocouples are installed on each top and bottom casings as shown below. Casing metal temperature gradient between top and bottom will be redu
16、ced due to spin cooling operation and casing distortion will be minimized. Bottom clearance will be restored due to reduced casing distortion.,94,Reliability enhancement by spin cooling,MHI established the following guideline for spin cooling and recommend to carry out the spin cooling operation aft
17、er shut down. 1) The GT cannot be restarted or spun within 1 hour after the shut down so as to avoid the compressor blade tip rubbing due to the compressor blade ring oval deformation. (Zone A in Figure 1) 2) The GT can be restarted during 16 hours after the shut down without spin cooling, provided
18、the casing metal temperature difference is within the criteria. (Zone B in Figure 1) Criteria for turbine casing: 60C / for combustor casing: 35C 3) If the GT is planned to restart during 630 hours after the shut down, the spin cooling operation is required. Because the casing metal temperature diff
19、erence is estimated to exceed the criteria during this period without spin cooling. (Zone C in Figure 1) 4) After approx.30 hours from the shut down, the GT can be restarted without spin cooling operation, provided the casing metal temperature difference reduces within criteria level due to natural cooling. (Zone D in Figure 1) 5) In case of the restart timing of the GT is not predicted, it is recommended to carry out the spin cooling operation according to the standard procedure.,Time after GT shut down,Figure 1 : Trend of GT casing metal temperature difference without spin cooling,