曾军 1廖文轩 2张剑 1崔亭亭 1张晓晶 1王闰龙1
作者信息
- 1. 中国航发四川燃气涡轮研究院,成都 610500
- 2. 哈尔滨工业大学能源科学与工程学院,哈尔滨 150001
- 折叠
摘要
Abstract
Turbine blade interdisciplinary design involves coupling among multiple disciplines such as aerodynamics,structures,heat transfer,and strength.With the continuous increase in turbine inlet temperatures of aero-engines,traditional design methods face severe challenges.Conventional engineering methods typically adopt a sequential and decoupled design process for disciplines(including aerodynamics,heat transfer,and strength),applying various simplifications to computational models and methods.This paper conducts a multidisciplinary coupled simulation study focusing on the first-stage rotor blade of a two-stage turbine.To ensure the reliability of the verification method,grid independence verification and experimental validation of the turbine blade cooling effectiveness were first performed.Subsequently,a comparison was made between the results from the multidisciplinary coupled simulation method and those from the conventional engineering methods.The findings indicate that:in terms of aerodynamic performance calculation,the coupled simulation method and the engineering method show good consistency,with differences in all aerodynamic parameters(stage expansion ratio,stage efficiency,first-stage rotor full-annulus inlet/outlet flow rates,first-stage rotor inlet/outlet absolute Mach numbers,etc.)being within 1.30%.The temperature field distribution exhibits non-uniform differences,with blade surface temperature discrepancies of 0.41%(maximum),-7.63%(minimum),and-4.89%(average).In strength calculations,the differences in maximum radial displacement and axial displacement of the blade body are-10.20%and-7.24%,respectively,while the maximum discrepancy in vibration characteristic frequencies(static and dynamic frequencies)is 1.50%.These differences primarily arise because the multidisciplinary coupled simulation method is based on high-fidelity geometric models and fully three-dimensional computational techniques,retains detailed structures such as film cooling holes,and better accounts for the multi-field coupling effects of aerodynamics,thermodynamics,and structures,thereby providing an effective approach for the design of air-cooled turbine blades.关键词
涡轮叶片/多学科耦合/冷却结构/流动换热/强度振动Key words
turbine blade/multidisciplinary coupling/cooled structure/flow and heat transfer/strength vibration分类
航空航天
