Name: a rapid method for modeling a variable cycle engine
Uploaded: 2019-08-13T13:00:00
Description: Watch this Scientific Journal Video about A Rapid Method for Modeling a Variable Cycle Engine at JoVE.com

这项研究由中央大学基础研究基金资助,赠款编号[No.NS2018017*

1. 建模前的准备
<ol><li>获得设计点性能。<ol>
<li>打开加斯图尔布 13.选择可变循环引擎。</li>
		<li>点击基本热力学。选择循环设计。打开演示VarCyc.CVC.</li>
		<li>获得发动机设计点性能。这些显示在窗口的右侧。</li>
	</ol>
</li>
	<li>获取组件映射。<ol>
<li>打开加斯图尔布 13.选择可变循环引擎。</li>
		<li>单击"<strong...

<ol>
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D-7901. , (1975).</li><li>Reed, J., Afjeh, A. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/entrez/query.fcgi?db=PubMed&cmd=Search&doptcmdl=Citation&defaultField=Title+Word&term=Development+of+an+interactive+graphical+propulsion+system+simulator.">Development of an interactive graphical propulsion system simulator.</a> The 30th Joint Propulsion Conference and Exhibit in Indianapolis, IN. , (1994).</li><li>Chapman, J. W., Lavelle, T. M., May, R., Litt, J. S., Guo, T. 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基于图形模拟环境,通过模块化分层架构和面向对象建模技术,可以快速构建 VCE 组件级模型。它为用户提供了一个友好的界面,它便于分析和设计模型19。
该方法的主要局限性是模型的执行效率。由于模型是用脚本语言编写的,因此每次运行时都需要重新编译模型。因此,执行效率不如系统语言。鉴于这一局限性,下一个关键的研究点是如何提高模型的执行效率。?...

现代飞机需求给推进系统带来了巨大的挑战,推进系统需要更智能、更高效、甚至更通用的飞机发动机。未来的军事推进系统还需要高速推力更高,在低速1、2、3、4时降低特定油耗。为了满足未来飞行任务的技术要求,通用电气(GE)于1955年提出了变循环发动机(VCE)概念。VCE是一种飞机发动机,可以通过改变某些部件的几何尺寸或位置来执行不同的热力学循环。洛克希德SR-71"黑鸟"由J58涡轮喷气式VCE提供动力,自1976年7月以来一直保持最快的空中呼吸载人飞机的世界纪录。这也证明了超音速飞行的许多潜在优势。在过去的50年里,GE改进并发明了其他几款VcE,包括双旁路VCE8、控制压力比发动机9和自适应循环发动机10。这些研究不仅涉及一般结构和性能验证,还涉及发动机11的控制系统。这些研究已经证明,VCE在亚音速飞行中可以像高旁路比涡轮风扇一样工作,就像低旁路比涡轮风扇一样,甚至像超音速飞行中的涡轮喷气式飞机一样。因此,VCE可以在不同的飞行条件下实现性能匹配。
在开发 VCE 时,将进行大量必要的验证工作。如果所有这些工作都是以物理方式进行的话,可能会花费大量的时间和花费。计算机仿真技术在开发新发动机时已经采用,不仅大大降低了成本,而且避免了潜在的风险。基于计算机仿真技术,发动机的开发周期将缩短近一半,所需设备数量将大幅减少15.另一方面,仿真在分析发动机行为和控制规律发展方面也起着重要的作用。为了模拟发动机的静态设计和非设计性能,美国宇航局刘易斯研究中心于1972年开发了一个名为GENENG16的程序。然后,研究中心开发了从GENENG衍生的DYNGEN 17,DYNGEN可以模拟涡轮喷气发动机和涡轮风扇发动机的瞬态性能。1989年,美国宇航局提出了一个叫做数值推进系统模拟(NPSS)的项目,它鼓励研究人员使用面向对象的编程来构建一个模块化和灵活的发动机模拟程序。1993年,John A. Reed通过面向对象的程序18,开发了基于应用可视化系统(AVS)平台的涡轮风扇发动机仿真系统(TESS)。
同时,基于图形编程环境的快速建模正在仿真中逐步应用。美国宇航局开发的热力学系统建模和分析工具箱(T-MATS)基于Matlab/Simulink平台。它是开源的,允许用户自定义内置组件库。T-MATS为用户提供了友好的界面,便于分析和设计内置的JT9D型号19。
在本文中,使用Simulink软件开发了一种VCE的动态模型。该协议的建模对象是双旁路 VCE。其原理图布局如图1所示。发动机可在单旁路和双旁路模式下工作。当模式选择阀 (MSV) 打开时,发动机在旁通比相对较大的亚音速条件下性能更好。当模式选择阀关闭时,VCE 具有较小的旁通比和更好的超音速任务适应性。为了进一步量化发动机的性能,基于组件级建模方法构建了双旁路 VCE 模型。

<table>
	<tbody>
		<tr>
			<td>Gasturb</td>
			<td>GasTurb GmbH</td>
			<td>Gasturb 13</td>
			<td></td>
		</tr>
		<tr>
			<td>MATLAB</td>
			<td>MathWorks</td>
			<td>R2017b</td>
			<td></td>
		</tr>
		<tr>
			<td>TMATS</td>
			<td>NASA</td>
			<td>1.2.0</td>
			<td></td>
		</tr>
	</tbody>
</table>

a rapid method for modeling a variable cycle engine

结合涡轮风扇和涡轮喷气发动机优势的可变循环发动机 (VCE) 被广泛认为是下一代飞机发动机。但是,开发 VCE 需要很高的成本。因此,在开发飞机发动机时,必须建立一个数学模型,这样可以避免大量的实际测试,并大大降低成本。建模在控制法发展中也至关重要。本文基于图形仿真环境,介绍了一种利用面向对象建模技术和模块化分层架构对双旁路可变周期引擎进行建模的快速方法。首先,在热力学计算的基础上建立了各分量的数学模型。然后,通过每个分量数学模型和 N-R 求解器模块的组合构建分层引擎模型。最后,在模型中进行了静态和动态仿真,仿真结果证明了建模方法的有效性。该方法构建的VCE模型具有结构清晰、实时观测等优点。

为了证明仿真模型的有效性,将静态仿真和动态仿真中选择的几个典型性能参数与Gasturb中的数据进行了比较。
在静态仿真中,我们将模型的几个关键性能参数与 Gasturb 中的这些参数进行比较,以验证静态模型的准确性。表 2显示了在双旁路操作模式下与 H=0 m、Ma=0、Wf=0.79334 kg/s 的设计点进行比较的结果。根据比较,模型和 Gasturb 之间的性能参数的最大?...

Watch this Scientific Journal Video about A Rapid Method for Modeling a Variable Cycle Engine at JoVE.com

A Rapid Method for Modeling a Variable Cycle Engine

在这里,我们提出一个协议,为可变循环引擎构建组件级数学模型。

可变循环引擎建模的快速方法

The variable cycle engines (VCE) that combine the advantages of turbofan and turbojet engines, are widely considered to be the next generation aircraft ...

这种方法帮助研究人员利用现有的发动机数据快速构建飞机发动机模型。此方法的这一主要优点是，对传统建模的编程技术没有很高的要求。在开始建模之前，打开 GasTurb13 并单击基本热力学。选择循环设计和打开演示变量周期。将显示发动机设计点性能参数。要获取组件映射，请在主窗口中单击"关闭设计、更多"和"标准贴图"。打开演示变量循环并选择 LPC、IPC、HPC、HPT 和 LPT。要对可变循环引擎的单个组件建模，请打开数据分析程序并单击 Simulink。双击空白模型，然后单击库以将函数放置到模型。双击功能。根据压缩机的工作原理描述压缩机的热力学方程。单击等式并粘贴以获取压缩机的输入和输出。重命名函数压缩器。在压缩器功能窗口中，右键单击函数名称并选择子系统和模型参考，然后从选择创建子系统以屏蔽模块。建模所有组件后，将每个组件的输出与下一个组件的输入组合在一起。此处显示双旁路操作模式下设计点的比较结果显示，模型和 GasTurb 之间的性能参数的最大误差是发动机压力比低于 2%，这是在单旁路操作模式下在关闭设计点进行比较的结果。在这些条件下，最大误差是低压轴的转速略低于4% 在此代表性的加速度下，在双旁路模式下处理的减速模拟显示燃油流量的输入。这些转速、气流和涡轮数据之前的温度表明，该模型能够执行加速、减速模拟。在此代表性实验中，变频发动机工作模式在五秒钟时从单旁路模式切换到双旁通模式，以防止发动机在切换过程中超过限速，对高压轴的转速应用了单可变闭环控制。在此测定中，高压轴的转速在切换过程中几乎保持不变。同样，在涡轮之前，燃油流量、转速、气流和温度的响应也得到观察。加速度、减速和模式切换仿真结果确认，两个动态仿真模型能够正常运行。学习如何选择特定或通用的工作方程很重要，因为常见的工作方程有助于正确设置模型。按照此程序，可以建造其他类型的飞机发动机或燃气轮机发动机模型。

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