高通流三外涵变循环发动机建模技术研究  

Modeling technology of high-flow triple-bypass variable cycle engine

作　　者：张煜华 袁伟 邹涛 于兵[1] ZHANG Yuhua;YUAN Wei;ZOU Tao;YU Bing(College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Photoelectric Science and Technology Branch,AECC South Industry Co.,Ltd.,Zhuzhou 412002,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]中国航发南方工业有限公司光电科技分公司,湖南株洲412002

出　　处：《推进技术》2024年第8期35-43,共9页Journal of Propulsion Technology

基　　金：航空发动机及燃气轮机基础科学中心项目(2022-DB-V-002-001);南京航空航天大学研究生科研与实践创新计划项目(xcxjh20220213)。

摘　　要：高通流三外涵变循环发动机是航空发动机及燃气轮机基础科学中心提出的一种新的发动机概念构型。本文搭建了发动机部件级模型,采用了考虑容积效应的动态模型建模方法对发动机主要容腔进行建模。为保证建模的精度,考虑了第二外涵道中换热器与气体的动态换热,同时用总压恢复系数代替动量守恒方程,提升了模型计算的实时性。针对发动机在高空设计点情况下较高的涡轮前温度,引入了涡轮叶片的气膜冷却模型。仿真结果表明,经换热器换热后的高质量冷气可使涡轮的平均温降达到121 K;对比考虑容积效应的建模方法,传统建模方法在发动机过渡态的建模误差达到了17.1%。若要研究发动机的过渡态过程,容积效应一般不可忽略。The high-flow Triple-Bypass Variable Cycle Engine is a new engine concept proposed by the Basic Science Center for Aircraft Engines and Gas Turbines.This paper establishes component-level models of the engine.The dynamic modeling method that takes into account the volume effect is used to model the main chambers of the engine.To ensure the accuracy of the modeling,dynamic heat transfer between the heat exchang⁃er and the gas in the second bypass is considered,and the total pressure recovery coefficient is used instead of the momentum conservation equation to improve the real-time calculation of the model.To address the high tur⁃bine inlet temperature of the engine at high-altitude design points,a film cooling model for the turbine blades is introduced.Simulation results show that the high-quality cold air after the heat exchanger can reduce the average temperature drop of the turbine to 121 K.Compared to modeling methods that consider volume effects,traditional modeling methods have a modeling error of up to17.1%during engine transient operation.If one wants to study the transient process of the engine,volume effects are generally not negligible.

关 键 词：变循环发动机 容积效应 气膜冷却 换热器 动态模型 

分 类 号：V235.16[航空宇航科学与技术—航空宇航推进理论与工程]