基于混合网格的涡扇发动机动力特性模拟
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- 英文论文题名：Simulation of Turbofan Engine with Power based on Unstructured Grid
- 论文作者：谭伟伟 ; 聂智军 ; 郝海兵 ; 颜洪
- 英文论文作者：Tan Weiwei ; Nie Zhijun ; Hao Haibing ; Yan Hong ; Aeronautics Computing Technique Research Institute Xi'an
- 年：2016
- 作者机构：中航工业西安航空计算技术研究所;
- 论文关键词：Navier-Stokes方程 ; 混合网格 ; 涡扇发动机 ; 动力特性
- 英文论文关键词：Navier-stokes equations ; hybrid grid ; turbofan engine ; dynamic performiance
- 会议召开时间：2016-10-31
- 会议录名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛文集（下册）
- 英文会议录名称：Discovery,Innovation and Communication——Proceedings of 7th CSAA Science and Technology Youth Forum
- 语种：中文
- 分类号：V235.13
- 学会代码：ZGHU
- 会议名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛
- 会议地点：中国广东中山
- 主办单位：中国航空学会
- 学会名称：中国航空学会
- 页数：6
- 文件大小：1321k
- 原文格式：O
- 会议级别：全国
摘要
基于非结构/混合网格并行计算软件,以等熵流动原理为出发点,结合发动机短舱入口及远场特征边界条件,建立了一种新的涡扇发动力动力特性计算模型。通过与Navier-Stokes方程耦合求解,数值模拟了轴对称超高涵道比涡扇模型(CRUF)和轴对称涡轮动力模型(TPS)进排气流场,计算结果与文献中的发动机动力特性模型计算结果以及实验数据进行比较,三者吻合较好,从而验证了本文构造的涡扇发动机动力特性计算模拟的正确性、可靠性以及工程实用性。
Based on unstructured/hybrid grid parallel CFD Solver and the isentropic flow principle,a new numerical turbofan engine model was constructed by introducing farfield characteristic boundary condition and engine inlet/exhaust boundary conditions,in which the total pressure ratio and total temperature ratio at exhaust plane and the mass flow at inlet are specified.Incorporating the new boundary conditions into the solving of Navier-Stokes equations,the flow around an axisymmetric ultra-high bypass ratio turbofan simulator CRUF and a turbine powered simulator(TPS) were simulated.Compared with the experiment data,the numerical results show that the engine inlet and exhaust flowfields are accurately simulated by the newly presented boundary conditions.The validity and reliability of the numerical method simulating turbofan engine with power is verified as well.
Based on unstructured/hybrid grid parallel CFD Solver and the isentropic flow principle,a new numerical turbofan engine model was constructed by introducing farfield characteristic boundary condition and engine inlet/exhaust boundary conditions,in which the total pressure ratio and total temperature ratio at exhaust plane and the mass flow at inlet are specified.Incorporating the new boundary conditions into the solving of Navier-Stokes equations,the flow around an axisymmetric ultra-high bypass ratio turbofan simulator CRUF and a turbine powered simulator(TPS) were simulated.Compared with the experiment data,the numerical results show that the engine inlet and exhaust flowfields are accurately simulated by the newly presented boundary conditions.The validity and reliability of the numerical method simulating turbofan engine with power is verified as well.
引文
[1]谭兆光,陈迎春,李杰,张淼.机体/动力装置一体化分析中的动力影响效应数值模拟[J].航空动力学报,2009.8,24(8):1766-1772.
[2]Henderson W P,Patterson J C,Propulsion Installation Characteristics of Turbofan Transports[J].AIAA,1983:87.
[3]Hirose N,Asai K,Ikawa K.3-D Euler Flow Analysis of Fanjet Engine and Turbine Powered Simulator with Experimental Comparison in Transonic Speed[J].AIAA,1989-1835.
[4]Deese J E,Agarwal R K,Calculation of Axisymmetric Inlet Flowfield Using the Euler Equations[J].AIAA,83-1853,1983.
[5]刘李涛,杨永,李喜乐.外吹式动力吹气襟翼N-S方程数值模拟分析[J].航空计算技术,2008,38(3):61-64.
[6]郝海兵,李蔷薇,梁益华,颜洪.涡扇发动机带动力数值模拟[J].航空计算技术,2013,43(3):13-17.
[7]谭伟伟.混合网格Navier-Stokes方程并行计算软件开发与应用研究[D],硕士学位论文,中国航空研究院,2011.3.
[8]E Obert.Aerodynamic Design of Transport Aircraft[M].Delft University Press,Netherlands.
[9]Reinhard Kiock,Heinz Hoheisel.Design of Axisasymmetric Nacelle for the Counter Rotating Ultra-HighBypass Fan Simulator[R].DLR FB-93-52,1993.
[10]Hirose N,Asai K,Ikawa K.Transonic 3-D Euler Analysis of Flows around Fan-jet Engine and T.P.S.(Turbine Powered Simulator)[R].NAL TR-1045,1989.
[2]Henderson W P,Patterson J C,Propulsion Installation Characteristics of Turbofan Transports[J].AIAA,1983:87.
[3]Hirose N,Asai K,Ikawa K.3-D Euler Flow Analysis of Fanjet Engine and Turbine Powered Simulator with Experimental Comparison in Transonic Speed[J].AIAA,1989-1835.
[4]Deese J E,Agarwal R K,Calculation of Axisymmetric Inlet Flowfield Using the Euler Equations[J].AIAA,83-1853,1983.
[5]刘李涛,杨永,李喜乐.外吹式动力吹气襟翼N-S方程数值模拟分析[J].航空计算技术,2008,38(3):61-64.
[6]郝海兵,李蔷薇,梁益华,颜洪.涡扇发动机带动力数值模拟[J].航空计算技术,2013,43(3):13-17.
[7]谭伟伟.混合网格Navier-Stokes方程并行计算软件开发与应用研究[D],硕士学位论文,中国航空研究院,2011.3.
[8]E Obert.Aerodynamic Design of Transport Aircraft[M].Delft University Press,Netherlands.
[9]Reinhard Kiock,Heinz Hoheisel.Design of Axisasymmetric Nacelle for the Counter Rotating Ultra-HighBypass Fan Simulator[R].DLR FB-93-52,1993.
[10]Hirose N,Asai K,Ikawa K.Transonic 3-D Euler Analysis of Flows around Fan-jet Engine and T.P.S.(Turbine Powered Simulator)[R].NAL TR-1045,1989.