一种燃气涡轮叶片气热性能实验台

A Gas Turbine Test Facility of Blade Aerothermal Performance

随着行业对燃气轮机和航空发动机的性能需求日益增加,研发高效率、长寿命、低排放和大推重比的先进燃气轮机和航空发动机十分紧迫。由于燃气涡轮叶栅内部流动非常复杂,呈现出高度三维流动特征,因此数值仿真和理论分析难以得到准确、可靠的研究结果,必须要有实验研究,为其提供实验数据加以验证。本文介绍了一种新型燃气涡轮叶片气热性能实验台,该实验台具备实现主流温度阶跃上升能力,采用瞬态红外测量技术(IR)可完成不同入射角度、不同节距叶栅、不同类型叶栅(静叶和动叶)的叶栅流动、传热和冷却性能研究。该实验台采用模块化设计,可以实现实验叶栅方便、快速更换,并且开设有实验观察平台,可提供可视化观测和红外温度测量,运用瞬态红外测量技术(IR)和双线性回归(DLRT)数据处理方法研究叶栅传热和冷却特性;同时,在该实验台进行了吹风实验,实验结果表明该实验台达到了设计要求,可以进行旁通气路和实验气路瞬态切换。

With the increasing demands of gas turbines performance and aero-engines performance in industry,it's urgent to develop the advanced gas turbines with higher eficient,longer operation life,lower emissions and larger thrust-to-wcight ratio.Due to the complicated and three-dimensional(3D)flow field in blade passage,acquiring accurate and reliable results are difficult by numerical simulations and theoretical analysis,so it's necessary to carry out experiment research.This paper presents a novel gas turbine test facility of blade aerothermal performance,which can provide transient step rise of mainstream temperature and carry out fow,heat transfer and film cooling studies at different incidence angles,different pitch cascades and different types cascades(vane and blade)by Infrared measurement technology.To achieve the goal of rapidity and ease build,the test section is modularly designed and constructed.In addition,the optical ports are designed to provide visualization measurements and Infrared temperature measurements.The wall temperature is measured by Infrared technology and the heat transfer and film cooling performance are investigated by the data reduction of Dual Linear Regression Technique(DLRT).Simultaneously,the benchmark aerodynamic measurements were carried out and the results indicate the design goals are acquired and transient switching between bypass line and test line can be performed.