涡轮叶片冷气掺混损失计算模型简化方法研究  

A Simplification Method for Computational Model of Cooling Losses from Turbine Vane

作　　者：王宇林 李志刚[1] 李军[1,2] WANG Yulin;LI Zhigang;LI Jun(Institute of Turbomachinery,Xi'an Jiaotong University,Xi'an 710049,China;Collaborative Innovation Center for Advanced Aero-Engine,Beijing 100191,China)

机构地区：[1]西安交通大学能源与动力工程学院叶轮机械研究所,西安710049 [2]先进航空发动机协同创新中心,北京100191

出　　处：《工程热物理学报》2024年第4期1001-1006,共6页Journal of Engineering Thermophysics

基　　金：国家科技重大专项资助项目(No.J2019-Ⅱ-0022-0043)。

摘　　要：本文采用CFD软件ANSYS CFX对某带冷气射流的燃气涡轮高热负荷叶片进行了数值模拟,提出了2种适用于不同情况的单排孔冷却叶片的计算模型简化方法,有效地简化了模型结构、节约了计算成本。该简化思路适用于带叶身气膜冷却直叶片的数值计算,另外,本文还提供了一种分块结构化网格生成方法。In this paper,numerical investigations were conducted on a high heat load blade of a gas turbine with film cooling injections by using CFD software ANSYS CFX.Two different simplification methods for computational model with single row of film holes were proposed for different situations,which could effectively simplify the model structure and save computational costs.This methodology could be applied on the numerical simulations of the straight blade with film cooling on vane surfaces.Additionally,a generation method of structured grid with multiple blocks was provided in this paper.

关 键 词：气膜冷却 计算模型简化 分块结构化网格 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程] TK474.4[动力工程及工程热物理—动力机械及工程]