水下小型特种燃气轮机轮盘热-流耦合仿真分析
|
摘要
文中针对水下小型特种燃气轮机高温高速来流、涡轮盘高转速的情况下,流体域使用剪切压力传输(SST) k-ω湍流模型,固体域采用共轭传热的方法对轮盘及其流道温度场进行仿真,并将得到的温度场加载到强度分析中,对最恶劣工况下轮盘所受热应力、变形量进行仿真计算。计算结果表明:在采用3喷嘴数时涡轮盘温度达到极值,且反向排气可有效降低涡轮盘表面温度,但其做功能力将被限制。在不采取任何冷却措施的情况下,轮盘最高温度已超出材料最大耐受温度,在轮盘最高温度极值区域有较大的伸长率,且轮盘在高温高转速下最大应力值已超出材料的许用应力。应在涡轮盘温度较高的区域对轮盘采取一定的冷却措施。文中所做研究可为燃气轮机安全设计提供参考。
For the high temperature and high-speed incoming flow of small and special underwater gas turbines and the high rotary speed of the turbine disk, the temperature field of the disk and its channel are simulated by using the shear stress transport(SST) k-ω turbulence model for the fluid domain and the conjugate heat transfer method for the solid domain. Then, the temperature field is loaded into the strength analysis to simulate the thermal stress and deformation of the disk under the worst conditions. Calculation results show that the turbine disk temperature reaches the extreme value when the number of nozzles is 3; and the reverse exhaust can effectively reduce the surface temperature of the turbine disk, but its function will be limited. Without any cooling measures, the maximum temperature of the disk exceeds the maximum temperature tolerance of the material, and there is a large disk elongation in its extreme temperature range,moreover, the maximum stress value of the disk at high temperature and high rotary speed exceeds the allowable stress of the material. Therefore, certain cooling measures should be taken for the disk areas where the temperature is higher.This research may provide a reference for safety design of gas turbines.
For the high temperature and high-speed incoming flow of small and special underwater gas turbines and the high rotary speed of the turbine disk, the temperature field of the disk and its channel are simulated by using the shear stress transport(SST) k-ω turbulence model for the fluid domain and the conjugate heat transfer method for the solid domain. Then, the temperature field is loaded into the strength analysis to simulate the thermal stress and deformation of the disk under the worst conditions. Calculation results show that the turbine disk temperature reaches the extreme value when the number of nozzles is 3; and the reverse exhaust can effectively reduce the surface temperature of the turbine disk, but its function will be limited. Without any cooling measures, the maximum temperature of the disk exceeds the maximum temperature tolerance of the material, and there is a large disk elongation in its extreme temperature range,moreover, the maximum stress value of the disk at high temperature and high rotary speed exceeds the allowable stress of the material. Therefore, certain cooling measures should be taken for the disk areas where the temperature is higher.This research may provide a reference for safety design of gas turbines.
引文
[1]查志武,史小峰.鱼雷热动力技术[M].北京:国防工业出版社,2006.
[2]York W D,Laylek J H.Three-Dimensional Conjugate Heat Transfer Simulation of an Internally-Cooled Gas Turbine Vane[C]//2003 International Joint Power Generation Conference.Atlanta,USA:ASME,2003:351-356.
[3]Kusterer K,Haledon T,Bohn D.Improvement of a Film-Cooled Blade by Application of the Conjugate Calculation Technique[J].ASME Journal of Turbo Machinery,2006,128(3):572-578.
[4]秦江,孙红闯,白新阳,等.油冷涡轮动叶方案中旋转冷却效应分析[J].推进技术,2017,38(2):399-407.Qin Jiang,Sun Hong-chuang,Bai Xin-yang,et al.Analysis of Rotating Cooling Effects with Oil for Turbine Blade[J].Journal of Propulsion Technology,2017,38(2):399-407.
[5]郭晓杰,顾伟,竺晓程,等.航空収动机热端部件二次流动和传热耦合方法研究[J].燃气轮机技术,2014,27(2):40-45.Guo Xiao-jie,Gu Wei,Zhu Xiao-cheng,et al.Coupling Computational Approach of Secondary Flow and Heat Transfer in Aero-engine Hot Components[J].Gas Turbine Technology,2014,27(2):40-45.
[6]Verdicchio J A,Chew J W,Hills N J.Coupled Fluid Solid Heat Transfer Computation for Turbine Discs[C]//ASMETurbo Expo 2001:Power for Land,Sea,and Air.New Orleans,Louisiana,USA:ASME,2001:V003T01A079.
[7]刘振侠,张丼芬.采用热-流耦合方法对气冷涡轮叶片换热的计算[J].西北工业大学学报,2007,25(2):315-319.Liu Zhen-xia,Zhang Li-fen.Numerical Study of Heat Transfer Using Heat-Flow Coupling Method for Turbine Blade with Air Cooling[J].Journal of Northwestern Polytechnical University,2007,25(2):315-319.
[8]张超.燃气透平导叶气热耦合实验与数值研究[D].北京:中国科学院研究生院(工程热物理研究所),2012.
[9]陈雄,李映坤,刘锐,等.基于耦合传热的双脉冲収动机热防护层受热分析[J].推进技术,2016,37(1):83-89.Chen Xiong,Li Ying-kun,Liu Rui,et al.A Study of Thermal Protection Layer in Dual Pulse Motor Based on Conjugate Heat Transfer Method[J].Journal of Propulsion Technology,2016,37(1):83-89.
[10]伊进宝,赵卫兵,师海潮.部分进气燃气涡轮机叶轮流场数值模拟[J].鱼雷技术,2010,18(6):456-460.Yi Jin-bao,Zhao Wei-bing,Shi Hai-chao.Numerical Simulation on Inner Flow Field of Gas Turbine with Partial Inlet Flow[J].Torpedo Technology,2010,18(6):456-460.
[2]York W D,Laylek J H.Three-Dimensional Conjugate Heat Transfer Simulation of an Internally-Cooled Gas Turbine Vane[C]//2003 International Joint Power Generation Conference.Atlanta,USA:ASME,2003:351-356.
[3]Kusterer K,Haledon T,Bohn D.Improvement of a Film-Cooled Blade by Application of the Conjugate Calculation Technique[J].ASME Journal of Turbo Machinery,2006,128(3):572-578.
[4]秦江,孙红闯,白新阳,等.油冷涡轮动叶方案中旋转冷却效应分析[J].推进技术,2017,38(2):399-407.Qin Jiang,Sun Hong-chuang,Bai Xin-yang,et al.Analysis of Rotating Cooling Effects with Oil for Turbine Blade[J].Journal of Propulsion Technology,2017,38(2):399-407.
[5]郭晓杰,顾伟,竺晓程,等.航空収动机热端部件二次流动和传热耦合方法研究[J].燃气轮机技术,2014,27(2):40-45.Guo Xiao-jie,Gu Wei,Zhu Xiao-cheng,et al.Coupling Computational Approach of Secondary Flow and Heat Transfer in Aero-engine Hot Components[J].Gas Turbine Technology,2014,27(2):40-45.
[6]Verdicchio J A,Chew J W,Hills N J.Coupled Fluid Solid Heat Transfer Computation for Turbine Discs[C]//ASMETurbo Expo 2001:Power for Land,Sea,and Air.New Orleans,Louisiana,USA:ASME,2001:V003T01A079.
[7]刘振侠,张丼芬.采用热-流耦合方法对气冷涡轮叶片换热的计算[J].西北工业大学学报,2007,25(2):315-319.Liu Zhen-xia,Zhang Li-fen.Numerical Study of Heat Transfer Using Heat-Flow Coupling Method for Turbine Blade with Air Cooling[J].Journal of Northwestern Polytechnical University,2007,25(2):315-319.
[8]张超.燃气透平导叶气热耦合实验与数值研究[D].北京:中国科学院研究生院(工程热物理研究所),2012.
[9]陈雄,李映坤,刘锐,等.基于耦合传热的双脉冲収动机热防护层受热分析[J].推进技术,2016,37(1):83-89.Chen Xiong,Li Ying-kun,Liu Rui,et al.A Study of Thermal Protection Layer in Dual Pulse Motor Based on Conjugate Heat Transfer Method[J].Journal of Propulsion Technology,2016,37(1):83-89.
[10]伊进宝,赵卫兵,师海潮.部分进气燃气涡轮机叶轮流场数值模拟[J].鱼雷技术,2010,18(6):456-460.Yi Jin-bao,Zhao Wei-bing,Shi Hai-chao.Numerical Simulation on Inner Flow Field of Gas Turbine with Partial Inlet Flow[J].Torpedo Technology,2010,18(6):456-460.
© 2004-2018 中国地质图书馆版权所有 京ICP备05064691号 京公网安备11010802017129号 地址：北京市海淀区学院路29号 邮编：100083 电话：办公室：(+86 10)66554848；文献借阅、咨询服务、科技查新：66554700 |