外并联式TBCC组合发动机的建模与特性分析

发布时间：2018-01-01 22:23

本文关键词：外并联式TBCC组合发动机的建模与特性分析　出处：《哈尔滨工业大学》2016年硕士论文　论文类型：学位论文

【摘要】：TBCC组合发动机由于其地面自起动、工作马赫数范围宽、可重复使用等优点已成为双级入轨(TSTO)中最有希望的第一级动力系统。而外并联式TBCC组合发动机由于其涡轮发动机和冲压发动机有相互独立的工作通道而具有更好的可控性已成为主流研究对象。本文通过建立外并联式TBCC组合发动机模型对发动机特性随发动机控制变量的变化规律和发动机的控制规律进行了研究。首先,根据组合发动机在飞行包线上三个不同工作模态,建立了组合发动机不同工模态发动机模型和组合发动机模型。对于涡轮发动机模态,根据涡轮发动机的组成由涡轮发动机的部件模型组合得到涡轮发动机模型。对于冲压发动机模态,根据冲压发动机在超燃模态、亚燃模态和进气道不起动3种模态时发动机的流场特性建立了冲压发动机模型。转级模态通过涡轮发动机和冲压发动机进气道面积变化的配合特点组合得到组合发动机模型。然后,根据得到的发动机模型,仿真分析了组合发动机在飞行包线不同工作模态时发动机特性随发动机控制变量的变化规律。在涡轮发动机模态,分析了压气机喘振裕度、压气机增压比和发动机推力等参数随涡轮转速、加力方式和尾喷管喉部截面面积的变化规律。在冲压发动机模态,分析了冲压发动机模态转换对应的4种临界状态时的燃油当量比、喉道比和进气道扩张比的空间分布规律以及亚燃和超燃模态时燃烧室出口温度和发动机推力随燃油当量比、喉道比和进气道扩张比的变化规律。转级模态则是分析了涡轮发动机进气道开度改变时涡轮发动机特性的变化规律。最后根据建立的发动机模型和发动机特性分析结果,利用模型建立了发动机模型稳态状态参数数据库。利用数据库对选定的发动机推力设计规律在一定的约束条件下进行了组合发动机不同工作模态控制规律设计,以及在对应控制规律下发动机特性的变化规律分析,利用所得控制规律对组合发动机模型进行了验证。
[Abstract]:TBCC engine due to the ground from the start, Maher number range, can be reused has become a dual stage to orbit (TSTO) first stage power system is the most hopeful. But because of the combination of parallel type TBCC engine turbine engine and ramjet engine working channel is independent and has better controllability has become the main research object. Through the establishment of external parallel TBCC engine model of engine control characteristics with the change rule of the engine and engine control variables are studied. Firstly, based on a combination of engine in envelope three different modes, a combination of different working modes of engine engine model and combined engine model for the turbine engine mode, according to the composition of the turbine engine by turbine engine mode by a combination of component model of turbine engine Type. For ramjet mode, according to the ramjet engine in supersonic combustion mode, ramjet mode and unstart 3 flow characteristics of engine modal established ramjet model. With the combination of modal transfer characteristics of turbine engine and ramjet inlet area change combined engine model. Then, according to the engine models. And simulation analysis of the combined engine in the flight envelope of different working modes when the engine performance changes with engine control variables. In the modal analysis of the turbine engine, compressor surge margin, compressor pressure ratio and engine thrust parameters such as turbine speed, variation of loading method and nozzle throat area. In ramjet mode analysis of the equivalent of 4, fuel ramjet mode transition critical state corresponding to the ratio of the throat and into the channel The spatial distribution of airway expansion ratio and ramjet and scramjet mode when the exit temperature of the combustor and the thrust of the engine with fuel equivalence ratio, variation ratio and expansion ratio of the laryngeal inlet. Transfer is analyzed the modal characteristics of turbine engine turbine engine inlet opening changes. Finally, according to the engine and engine model the characteristics of the analysis results, using the model of engine model steady state parameter database. Using the database engine thrust design rules selected under certain constraints of control law designing combined engine in different working modes, and the analysis of characteristics of engine in the corresponding control law under the changing rules of the control law was verified the combination of the engine model.

【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：TK401

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