某燃气涡轮气动设计及通用特性曲线计算
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摘要
针对燃气轮机中涡轮的设计,介绍了杭汽燃气涡轮气动设计体系,并阐述了冷却涡轮掺混损失计算方法和几种效率定义方法。通过一维热力设计和S2流面完全径向平衡方程设计,设计出了三级燃气涡轮。应用计算流体力学软件CFX对所设计的涡轮进行了不带冷气的性能分析,应用源项法对带冷气的涡轮进行了性能分析。通过三维计算,得到了新设计的三级涡轮的折合流量、折合转速、效率的特性曲线;并为涡轮的进一步气动优化设计和强度振动校核打下了基础。计算结果显示:设计的涡轮气动性能良好,变工况性能宽,基本达到了设计要求;不带冷却涡轮效率91%,带冷却的涡轮效率89.7%。
Aiming at the problem of gas turbine design,Turbine aerodynamic design system of Hangzhou steam turbine corporation was introduced. Moreover,computathonal method for mixing loss of cooled turbine and others method for defining the effieiency were elaborted.Through design concept of one dimensional thermal and S2 steam surface full radial equilibrium equation,a three stage turbine was acquired.CFD method was used to calculate the parameter in order to evaluate aerodynamic performance of the designed uncooled turbine,the aerodynamic performance of the designed cooled turbine was also evaluated through a source term method. Through three-dimensional calculated,the characteristics curve such as peduced flow rate,reduced rotary speeds and efficiency of the designed turbine was got. The achievements of this paper also layed the good foundation for further aerodynamic optimization and strength vibration check. The result indicates: the designed turbine achieves 91% total efficiency without cooling and 89. 7% total efficiency with cooling,it reaches the design target.
Aiming at the problem of gas turbine design,Turbine aerodynamic design system of Hangzhou steam turbine corporation was introduced. Moreover,computathonal method for mixing loss of cooled turbine and others method for defining the effieiency were elaborted.Through design concept of one dimensional thermal and S2 steam surface full radial equilibrium equation,a three stage turbine was acquired.CFD method was used to calculate the parameter in order to evaluate aerodynamic performance of the designed uncooled turbine,the aerodynamic performance of the designed cooled turbine was also evaluated through a source term method. Through three-dimensional calculated,the characteristics curve such as peduced flow rate,reduced rotary speeds and efficiency of the designed turbine was got. The achievements of this paper also layed the good foundation for further aerodynamic optimization and strength vibration check. The result indicates: the designed turbine achieves 91% total efficiency without cooling and 89. 7% total efficiency with cooling,it reaches the design target.
引文
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[3]冯国泰,顾中华,温风波,等.燃气涡轮机气冷涡轮气动设计体系设计思想及其应用[J].工程热物理学报,2009,30(11):1841-1848.
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[7]YOUNG J B,WILCOCK R C.Modeling the air-Cooled Gas turbine:Part II-Coolant Flows and Losses[J].Turbomachinery,2002,124(2):214-221.
[8]KURZKE J.Performance modeling methodology:efficiency definitions for cooled single and multistage turbines[R].The Netherlands:Internatinal Gas Turbine Institute,2002.
[2]航空发动机设计手册第10册涡轮[M].北京:航空工业出版社,2001.
[3]冯国泰,顾中华,温风波,等.燃气涡轮机气冷涡轮气动设计体系设计思想及其应用[J].工程热物理学报,2009,30(11):1841-1848.
[4]HARTSEL J E.Prediction of effects of mass-transfer cooling on the blade-row efficiency of turbine airfoils[R].San Diego,AIAA 10th Aerospace Sciences Meeting,1972.
[5]DENTON J D.Loss Mechanisms in Turbomachines[J].Turbomachinery,1993,115(4):621-656.
[6]YOUNG J B,WILCOCK R C.Modeling the air-Cooled Gas turbine:Part I-General Thermodynamics[J].Turbomachinery,2003,124(2):207-213.
[7]YOUNG J B,WILCOCK R C.Modeling the air-Cooled Gas turbine:Part II-Coolant Flows and Losses[J].Turbomachinery,2002,124(2):214-221.
[8]KURZKE J.Performance modeling methodology:efficiency definitions for cooled single and multistage turbines[R].The Netherlands:Internatinal Gas Turbine Institute,2002.