脉冲爆震燃烧室与涡轮联合三维流动数值仿真研究  

3D flow numerical simulation for the united pulsed detonation combustor and turbine parts

作　　者：杨杰 彭畅新 王凌羿 YANG Jie;PENG Chang-xin;WANG Ling-yi(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;Hunan Key Laboratory of Turbomachinery on Medium and Small Aero-Engine,Zhuzhou 412002,China;Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]中小型航空发动机叶轮机械湖南省重点实验室,湖南株洲412002 [3]西北工业大学动力与能源学院,西安710072

出　　处：《燃气涡轮试验与研究》2023年第1期1-9,共9页Gas Turbine Experiment and Research

摘　　要：采用脉冲爆震燃烧室的涡轮发动机是涡轮发动机未来的技术发展方向之一。为了厘清脉冲爆震燃烧环境下涡轮的气动性能与流场特征,为脉冲爆震涡轮发动机涡轮的气动设计提供技术支撑,对脉冲爆震燃烧室与涡轮开展了部件联合非定常流动数值仿真分析。结果表明,由于脉冲爆震波的产生,涡轮内工作介质的比定压热容、比热比等物性参数,功率、效率等性能参数,气流角、马赫数等气动参数,均发生了剧烈的变化,涡轮动叶进口的气流攻角和出口绝对气流角的变化达到150°。爆震波产生后气动参数与性能参数会激增到峰值,并在之后的约0.010s内会有量值减小的多个脉冲尖峰值。爆震波产生后的约0.020s后,涡轮内气流发生反向,从而不产生功率。涡轮的高效率时间区间为爆震波产生后的约0.010 s内,在其他时间段,涡轮的气动状态严重偏离设计点,涡轮发出功率较少,效率较低。The turbine engine with a pulsed detonation combustor is one of the technology developing trends for the future turbine engines.To clarify the aerodynamic performance and flow features of the turbine under pulsed detonation combustion environment,and to support the aerodynamic design for the turbines in pulsed detonation turbo engines,a unsteady flow numerical simulation for the united pulsed detonation combustor and turbine parts was conducted.The results show that because of the generation of the pulsed detonation wave,the physical parameters such as constant pressure specific heat and specific heat ratio of the working medium have sharply changed,so have the performance parameters such as power and efficiency and the aerodynamic parameters such as flow angle and Mach number.The changes of the incidence at the blade inlet and the absolute flow angle at the blade outlet have reached as high as 150 degrees.After the generation of the pulsed detonation wave,the aerodynamic parameters and performance parameters will increase to the peak values quickly,and will experience some little peak values during the following about 0.010 s period.After about 0.020 s period from the pulsed detonation wave generation,the turbine flow has reversed and generates no power.The turbine high efficiency time span is the 0.010 s period from the pulsed detonation wave generation;during other time span,as the working status is far from the design status,the power and efficiency are low.

关 键 词：航空发动机 脉冲爆震 燃烧室 涡轮 三维非定常 爆震波 数值仿真 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程] V235.22