上海交通大学
硕士学位论文
姓名：***
申请学位级别：硕士
专业：航空宇航推进理论与工程利路防水接头
指导教师：***
20060201
航空发动机变比热容热力计算和系统级仿真研究
摘要
航空发动机是一种非常复杂的非线性系统压气机涡轮涉及到流体力学
云海os
材料力学燃烧电机等学科先生产每一部件再设计这样一个反复迭代的过程耗费大量资金和宝贵时间计算机仿真已成为航空发动机研究中的得力工具提高设计水平降低成本和研发周期等
非因果联系和多领域等特点
在已有的模块库的基础上
建立和完善仿真程序库通过容积法
这样可以避免传统的迭代计算中
其中采用基于典型特性图的缩放方法进行计算
数码彩扩机
无热胆饮水机前者试验数据难获得
只要缩放系数不是很大
而且具有通用性
为了得到更精确的仿真计算结果
航空发动机中压力风门执行器
和组分的复杂函数气体经过燃烧室和燃油混合燃烧后
而且随着余气系数不同物性也不一样
为了计算方便
由燃料与理论空气量完全燃烧而成的分别考虑他们的比热容比如进气道可把其工质看成燃气为零的混合气体
然后对每一模块建立变比热容的数学计算模型
跟用软件Ｇａｓｔｕｒｂ和定比热计算的结果相比较
最后对常见的发动机系统
涡轮轴涡轮风扇等进行系统建模仿真
非设计点仿真计算包括速度特性
还有过渡工作状态加速
接通加力与断开加力等仿真
通用性可行性和便捷性等
模块化建模仿真Ｍｏｄｅｌｉｃａ
RESEARCH FOR THERMODYNAMIC CALCULATION BY VARIABLE SPECIFIC HEAT CAPACITY AND SYSTEM-LEVEL SIMULATION OF AEROENGINE
ABSTRACT
Aeroengine is one kinds of complicated nonlinear system, which consists of inlet, compressor, combustor, turbine, nozzle etc. And it involves many disciplines, such as fluid dynamics, aerodynamics, mechanics of materials, heat transfer, control and electrical engineering. In traditional design, every component is produced and assembled to be a system, then tested and redesigned. The iterations of the design process typically consume plenty of time and money. With the development of computer technique, computer simulation has been a powerful tool for aeroengine research, which can optimize design, improve the designing skill, reduce the work of experiment, the numbers of aeroengine, cost, research cycle and so on.
According to the concept of modular modeling means, the new object-oriented and non-casual language
空调控制板
Dymola. Thus the traditional iterative calculation, the difficulties of equation linearization and high-level groups of equations’ calculation are avoided. As for the simulation of the compressor and turbine models, a general way is proposed base on the representative performance maps scaling because the approaches of traditional system simulation depend on the samples too much and it’s difficult to get the experiments’ data. The simulation results prove this means is reasonable so long as the scaling coefficients are not too large.
Besides, in order to get more accurate simulation results, a mathematical model for calculating variable specific heat capacity of aroengine and the means how to calculate the model are given in the paper. During the working process of aircraft engine, the specific heat is the function of temperature , pressure & components ,but relies on the pressure less.The mixture gas coming from combustor is composed of heterogeneity, which becomes more complicated with the different ratio of fuel and air. If each component is taken into account, the ways for calculating will be difficult, even impossible. The following means is found to facilitate the situation: the working medium is looked as the mixture of air an d pure burning gas (sufficient combustion of fuel and air), whose v ariable specific heats are considered respectively. In this way
Gasturb and constant specific heat
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