某型燃气轮机进气系统内流场的数值分析  

Numerical Simulation on Interior Flow Field for a Gas Turbine Inlet System

作　　者：徐鑫[1] 刘常青[1] 孙勇 张亚东[1] 

机构地区：[1]中航工业沈阳发动机设计研究所,沈阳110015 [2]中航工业发动机有限责任公司,北京100028

出　　处：《航空发动机》2014年第2期51-55,75,共6页Aeroengine

基　　金：燃气轮机工程研究项目资助

摘　　要：为了揭示燃机进气系统内的流动特性,并为进气系统的性能预测、优化设计提供理论依据,以某型燃气轮机的进气系统为研究对象,基于混合网格的SIMPLE算法和标准的k-ε湍流模型,运用FLUENT软件对燃气轮机进气系统内的流场进行数值模拟,并从压力分布、气流角分布2个方面进行分析。结果表明:对气动性能产生重要影响的损失区域主要集中在进气外环上方和支板附近,蜗壳内锥的绕流分离也是损失源之一。应进行尽可能消除进气外环上方的气流分离,同时将绕流分离控制在一定范围内的优化设计和改进。In order to reveal the main characteristics of the inlet system,and provide the theoretical basis for the performance prediction and the optimization design of the inlet system,taking the inlet system of a gas turbine as a research subject,the interior flow field of the inlet system for gas turbine was simulated by FLUENT based on SIMPLE algorithm and standard k-ε turbulence model of mixed grid.The distribution of pressure and angle of flow were analyzed.The results show that the loss area of an important effect on the aerodynamic performance mainly concentrates on the top of airscoop and around the baffles,and the flow separation around inner cone is also one of the sources of losses.Therefore,the way of improving inlet system is eliminating the flow separation on top of airscoop and keeping the flow separation under control.

关 键 词：进气系统 流场 性能预测 优化设计 κ-ε湍流模型 燃气轮机 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]