Designing method of acceleration and deceleration control schedule for variable cycle engine

Studies show that different geometries of a Variable Cycle Engine(VCE)can be adjusted during the transient stage of the engine operation to improve the engine performance.However,this improvement increases the complexity of the acceleration and deceleration control schedule.In order to resolve this problem,the Transient-state Reverse Method(TRM)is established in the present study based on the Steady-state Reverse Method(SRM)and the Virtual Power Extraction Method(VPEM).The state factors in the component-based engine performance models are replaced by variable geometry parameters to establish the TRM for a double bypass VCE.Obtained results are compared with the conventional component-based model from different aspects,including the accuracy and the convergence rate.The TRM is then employed to optimize the control schedule of a VCE.Obtained results show that the accuracy and the convergence rate of the proposed method are consistent with that of the conventional model.On the other hand,it is found that the new-model-optimized control schedules reduce the acceleration and deceleration time by 45%and 54%,respectively.Meanwhile,the surge margin of compressors,fuel–air ratio and the turbine inlet temperature maintained are within the acceptable criteria.It is concluded that the proposed TRM is a powerful method to design the acceleration and deceleration control schedule of the VCE.

Integration of high-fidelity model of forward variable area bypass injector into zero-dimensional variable cycle engine model

Forward Variable Area Bypass Injector(FVABI)is one of key components which contributes to modulate the cycle parameters of Variable Cycle Engine(VCE)under various operation conditions.The modeling method of zero-dimensional FVABI was reviewed and its deficiency was analyzed based on FVABI flow characteristic.In order to improve the accuracy of VCE performance simulation,the high-fidelity modeling method of FVABI was developed based on its working characteristics.Then it was coupled with the zero-dimensional VCE model and the multi-level VCE model was built.The results indicate that the geometric and aerodynamic parameters can affect the interaction between the two airflows and the zero-dimensional FVABI model is too simple to predict the component performance accurately,especially when the FVABI inner bypass is chocked.Based on the performance curves for single bypass mode and the regression model of multi-scale support vector regression for double bypass mode,the high-fidelity model can predict FVABI performance accurately and rapidly.The integration of high-fidelity FVABI model into zerodimensional VCE model can be done by adjusting iterative variables and balance equations.The multi-level model has good convergence and it can predict VCE performance when the FVABI inner bypass is chocked.

A multi-fidelity simulation method research on front variable area bypass injector of an adaptive cycle engine

Front Variable Area Bypass Injector(Front-VABI) is a component of the Adaptive Cycle Engine(ACE) with important variable-cycle features. The performance of Front-VABI has a direct impact on the performance and stability of ACE, but the current ACE performance model uses approximate models for Front-VABI performance calculation. In this work, a multi-fidelity simulation based on a de-coupled method is developed which delivers a more accurate calculation of the Front-VABI performance based on Computational Fluid Dynamics(CFD) simulation. This simulation method proposes a form of Front-VABI characteristic and its matching calculation method between it and the ACE performance model, constructs a coupling method between the(2-D) Front-VABI model and the(0-D) ACE performance model. The result shows, when ACE works in triple bypass mode, the approximate model cannot account for the effect of FrontVABI pressure loss on Core Driven Fan Stage(CDFS) design pressure ratio, and the calculated error of high-pressure turbine inlet total temperature is more than 40 K in mode transition condition(the transition operating condition between triple bypass mode and double bypass mode). In double bypass mode, the approximate model can better simulate the performance of FrontVABI by considering the local loss of area expansion. This method can be applied to the performance-optimized design of Front-VABI and the ACE control law design during mode transition.

Analytical redundancy of variable cycle engine based on variable-weights neural network

In this paper, variable-weights neural network is proposed to construct variable cycle engine’s analytical redundancy, when all control variables and environmental variables are changing simultaneously, also accompanied with the whole engine’s degradation. In another word,variable-weights neural network is proposed to solve a multi-variable, strongly nonlinear, dynamic and time-varying problem. By making weights a function of input, variable-weights neural network’s nonlinear expressive capability is increased dramatically at the same time of decreasing the number of parameters. Results demonstrate that although variable-weights neural network and other algorithms excel in different analytical redundancy tasks, due to the fact that variableweights neural network’s calculation time is less than one fifth of other algorithms, the calculation efficiency of variable-weights neural network is five times more than other algorithms. Variableweights neural network not only provides critical variable-weights thought that could be applied in almost all machine learning methods, but also blazes a new way to apply deep learning methods to aeroengines.

Flow control of double bypass variable cycle engine in modal transition

To study the change mechanism and the control of the variable cycle engine in the process of modal transition,a variable cycle engine model based on component level characteristics is established.The two-dimensional CFD technology is used to simulate the influence of mode selection valve rotation on the engine flow field,which improves the accuracy of the model.Furthermore,the constant flow control plan is proposed in the modal transition process to reduce the engine installed drag.The constant flow control plan adopts the augmentation linear quadratic regulator control method.Simulation results indicate that the control method is able to effectively control the bypass ratio and demand flow of the variable cycle engine,and make the engine transform smoothly,which ensures the stable operation of the engine in modal transition and the constant demand flow of the engine.

基于冷气射流的涡轮流动主动控制数值模拟

针对变循环发动机在工作过程中进行涡轮流量调节的需求,以某涡轮的第一级作为研究对象,采用三维数值模拟的方式,对在导叶上不同射流位置、射流角度、射流流量的流场进行计算。结果表明:涡轮流量调节量对于射流位置十分敏感,在喉部上游附近的流量调节量最大;加入射流后涡轮损失增加,损失主要发生在射流于壁面上的流动区域;加入射流后,沿径向的大部分导叶出口气流角增大,从轮缘至轮毂导叶出口气流马赫数先增大后减小;涡轮流量调节效果与射流角度、射流流量成正比,当射流位于喉部附近、射流角度为90°、相对射流量为5%时,涡轮进口流量改变量达到13.03%,说明利用叶片表面射流,可以达到调节涡轮流量的目的。

涡轴-涡扇变循环发动机方案及性能匹配设计研究

针对旋转机翼式垂直起降高速巡航飞行器,提出了一种新概念结构形式的涡轴-涡扇变循环(TSFVCE)发动机,能够分别在涡轴和涡扇两种模态工作。首先对涡轴-涡扇变循环发动机的结构及工作模式进行了介绍,并建立基于变比热的部件级性能仿真模型;然后通过循环分析,确定发动机第二涵道比为3,Flade外涵风扇压比为1.98,第一涵道比为0.11,完成发动机设计点性能方案设计;最后分析了核心机驱动风扇(CDFS)可调机构对发动机性能影响机理,得出CDFS放气阀对发动机涡扇模态下的推力与涡轴模态下的功率影响较大,对涡扇模态的推力影响最大为61.5%,对涡轴模态的功率影响最大为33.3%,可利用此特性实现发动机在涡扇和涡轴模态下推力和功率输出的匹配。

高通流三外涵变循环发动机建模技术研究

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。

Numerical study of steady flow characteristics of a rear variable-area bypass injector with alternating area regulator

The mixing effectiveness of the airflow between the inner and outer bypass inlets of a Rear Variable-Area Bypass Injector(RVABI)is the key to the afterburner performance of variable cycle engines.This paper describes an optimized RVABI design based on an alternating area regulator to improve the velocity/temperature uniformity of the incoming flow at the afterburner.Compared with a classical RVABI,numerical simulations show that the proposed alternating RVABI performs better in terms of thermal mixing efficiency and total pressure loss in different variable cycle engine modes.Both the increasing air contact area between the inner and outer bypass of alternating structure RVABI,and a larger streamwise vortex in the inner bypass inlet due to the proposed alternating lobe structure in the RVABI contribute to the significantly increase of mixing effectiveness.Besides,the alternating regulator induces strong streamwise vortex,which helps to improve the airflow mixing with its vortex-induced velocity.The interaction between the streamwise vortex and azimuthal vortex further promises the velocity/temperature uniformity after the RVABI.With the increase of alternating lobe’s height ratio,the covering area of the streamwise vortex and the azimuthal vortex is enlarged,which further enhances the thermal mixing efficiency of the RVABI.This design gives an insight into the future design and optimization of RVABI.

变循环发动机后涵道引射器的研究现状与关键技术

变循环发动机是航空发动机的发展方向。相较于传统的航空发动机,变循环航空发动机在加力燃烧室中设置了后涵道引射器这一典型可调几何机构,以满足整机对气动匹配、推力和燃油经济性的需求。讨论了变循环发动机后涵道引射器的发展历程、布置位置、结构形式等,分析了后涵道引射器的结构特征和功能特点,点明了对加力燃烧室气动热力性能、结构尺寸的影响和对发动机推力、耗油率的影响。同时,结合后涵道引射器的发展历程和技术特征,指出了其在性能、结构和控制等方面需要深入研究的快速响应、精准控制和高可靠性等关键技术。通过对后涵道引射器的讨论和分析,以期为变循环发动机乃至未来涡轮基组合循环发动机的后涵道引射器性能和结构设计提供参考。

单外涵变循环发动机变几何特性仿真

为了研究单外涵变循环发动机变几何性能收益,建立了一种单外涵变循环发动机总体性能仿真模型,并通过算例验证了仿真模型的计算精度。根据不同飞行状态的发动机控制规律和最优控制目标,模拟生成3种变几何方案最佳变几何参数以及最佳节流特性和高度-速度特性。结果表明:在设定的控制规律下,相对发动机常规变几何方案(方案1),尾喷管、混合器与低压涡轮导向器可调的变几何方案(方案3)使发动机地面节流状态耗油率降低1.7%~3.0%,超声速巡航推力增大14%~29%,亚声速巡航耗油率降低0.9%~3.1%,在3种变几何方案中性能收益最大;尾喷管与混合器可调的变几何方案(方案2)使发动机地面节流状态耗油率降低1.2%~2.2%,超声速巡航推力增大3%~17%,亚声速巡航耗油率降低0.9%~1.2%,在3种变几何方案中性能收益居中。发动机变几何方案的选择应综合考虑结构复杂度、可靠性、质量等方面的代价与基于特定任务需求的总体性能收益的平衡。

Matching mechanism analysis on an adaptive cycle engine

As a novel aero-engine concept,adaptive cycle aero-engines（ACEs） are attracting wide attention in the international aviation industry due to their potential superior task adaptability along a wide flight regime.However,this superior task adaptability can only be demonstrated through proper combined engine control schedule design.It has resulted in an urgent need to investigate the effect of each variable geometry modulation on engine performance and stability.Thus,the aim of this paper is to predict and discuss the effect of each variable geometry modulation on the matching relationship between engine components as well as the overall engine performance at different operating modes,on the basis of a newly developed nonlinear component-based ACE performance model.Results show that at all four working modes,turning down the high pressure compressor variable stator vane,the low pressure turbine variable nozzle,the nozzle throat area,and turning up the core-driven fan stage variable stator vane,the high pressure turbine variable nozzle can increase the thrust at the expense of a higher high pressure turbine inlet total temperature.However,the influences of these adjustments on the trends of various engine components＇ working points and working lines as well as the ratio of the rotation speed difference are different from each other.The above results provide valuable guidance and advice for engine combined control schedule design.

变幅水位影响下高填方岸坡框架码头结构承载特性研究

库区周期性变幅水位引起高填方岸坡土体抗剪强度参数发生弱化,进而导致框架码头结构稳定性降低,因此有必要开展变幅水位条件下高填方岸坡框架码头结构承载特性研究。首先,基于已建立的变幅水位下岸坡稳定性简化计算方法,考虑土体饱和度与水位循环次数对土体强度参数的影响规律,建立了考虑渗透力、土体饱和度及变幅水位循环次数综合影响下的码头结构承载特性简化分析方法。然后,借助ABAQUS有限元软件,建立了高填方岸坡框架码头结构三维有限元计算模型,并将建立的方法应用于某实际码头工程承载特性分析。结果表明:饱和度、变幅水位循环次数与渗透力的共同作用对岸坡框架码头竖向承载能力影响并不明显,然而饱和度及水位循环次数的增加略微增大了码头结构水平向极限承载能力,撞击荷载作用下,岸坡土体饱和度为90%比饱和度为14%时码头结构水平极限承载力增加了6.4%,水位循环100次比水位循环1次时水平极限撞击能力增加了3.3%;考虑渗透力后饱和度及水位循环次数的变化对岸坡土体位移影响较大,其中岸坡塑性贯通区及位移变化最大区域集中在坡顶挡土墙下方与岸坡第1排、第2排桩基土体周围。

变循环调节机构发展现状及关键技术

变循环发动机可通过改变热力循环特性,实现更宽的工作范围和满足更多的战斗任务需求;调节机构是实现模式切换的执行机构,其设计技术发展伴随发动机整个研制历程。以变循环发动机跨代发展为主线,聚焦调节机构目标功能及结构方案演变,系统梳理了调节机构的发展历程、功能分类及设计要求。调节机构构型设计以低泄漏量、高调节精度、快速响应和可靠安装为总体要求,需进一步考虑未来发动机高热力负荷与紧凑布局引入的挑战与约束;在仿真分析方面,流固耦合分析应侧重解决几何特征复杂、结构柔性、空间跨度大、瞬态特征显著导致的网格畸变、收敛性降低问题,动力学仿真分析需重点聚焦关键件柔性变形、装配间隙、尺寸公差、传动摩擦等因素对机构卡滞、调节精度的影响;在试验验证方面,需进一步突破瞬态调节过程中温度、机械负载试验室模拟技术,加强试验室模拟验证能力,实现调节机构故障定位、误差归因。该研究对变循环调节机构设计、研制及相关理论、方法、技术发展具有一定指导意义。

基于H∞回路成形的变循环发动机多变量控制

为了进一步提升变循环发动机的性能,针对3输入3输出变循环发动机模型,利用相对增益矩阵(RGA)分析了发动机内部的耦合性;采用基于目标函数的2自由度H∞回路成形法设计了多变量控制器,并与传统单变量PI方法做了对比。仿真结果表明:多变量控制系统具有良好的扰动抑制能力和跟踪性能,且能够顺利实现模态转换;与单变量方法相比,在同等的穿越频率及相位裕度约束下,n1回路阶跃响应的超调量减小了95.3%、调节时间缩短了51.5%;πe回路的最大偏移量减小了89.69%、调节时间缩短了27.4%。表明多变量方法可以对变循环发动机进行有效控制且在跟踪控制过程中的性能更优,可以显著提升变循环发动机的性能。

涡轮级间混合架构的变循环发动机总体性能研究

为满足军用空优战斗机的超声速巡航和亚声速巡航需求,提出了一种涡轮级间混合的变循环发动机架构,该架构包含两种工作模式和八种变循环特征。首先阐述了本架构设计理念与任务目标;然后建立了部件级实时动态变循环发动机模型;最后,在经过特有的粒子群寻优算法对变循环发动机亚声速巡航油耗寻优,对比第四代涡扇发动机油耗产生了12.75%亚声速巡航收益。此外,即使在超声速巡航点本架构也实现了一定的油耗收益和推力提升。在超声速巡航和亚声速巡航之间,可实现0.29~0.82的涵道比大范围变化。结果表明,该架构有望成为一种适用于下一代空优战斗机的变循环发动机架构。

变循环发动机自适应无迹卡尔曼滤波器设计

针对变循环发动机健康参数估计问题,设计了一种自适应无迹卡尔曼滤波器。该算法通过最大化后验密度函数来建立过程噪声协方差和测量噪声协方差的自适应更新方程,以改善传统无迹卡尔曼滤波器设计中先验参数需要根据经验来设置,进而导致滤波器性能受人为因素影响较大的问题。以带核心机驱动风扇级的变循环发动机为对象,进行了不可测参数估计仿真试验,对所设计的自适应无迹卡尔曼滤波器算法进行了仿真对比验证。结果表明:在单参数退化条件下,健康参数平均估计误差不大于2%;多参数退化条件下,健康参数平均估计误差不大于1.8%;该算法性能优于增广卡尔曼滤波器、传统无迹卡尔曼滤波器,相较于传统无迹卡尔曼滤波器性能提升9.5%。

基于冷气预冷技术的高马赫数涡轮发动机建模与仿真研究

针对高马赫数涡轮发动机存在的涡轮部件热防护问题,以基于冷气预冷(CCA)技术的变循环涡扇发动机为例,通过建立燃油的热物性库、电动燃油泵和空气-燃油换热器的计算模型,改进燃烧室和涡轮的计算模型,发展了可控制涡轮叶片温度的变引气量整机性能计算模型。结果表明,在Ma3,20.9km的设计点,采用CCA技术能够将涡轮引气温度降低181K,相对引气量降低22.04%,并使推力和比冲分别提高2.03%,0.66%;在Ma3的节流状态下,控制涡轮叶片温度的发动机推力随转速降低而减小得更快,但是使空气-燃油换热器空气侧的温降最高达到240K,且总压损失明显降低;沿飞行轨迹,控制涡轮叶片温度的发动机在飞行马赫数大于1.8具有更大的推力,在飞行马赫数小于1.8具有更高的比冲。空气-燃油换热器在发动机最大热负荷状态的性能设计是影响引气温降和涡轮引气回流裕度的关键。

基于混合维度仿真的自适应循环发动机引射喷管安装性能研究

自适应循环发动机(Adaptive Cycle Engine,简称ACE)独特的三外涵道结构使引射喷管成为一种可行的排气系统方案。为准确评估各种工况下引射喷管与ACE匹配工作下的安装性能,提出了一种基于变可信度代理模型的ACE-引射喷管混合维度仿真方法。该方法搭配引射喷管高、低两种可信度的计算流体动力学(Computational Fluid Dynamics,简称CFD)仿真模型,建立了引射喷管变可信度代理模型。通过动态更新该代理模型,在引射喷管性能空间的匹配工作区域集中进行高可信度CFD仿真,高效准确地实现了引射喷管匹配状态下的安装性能评估。仿真结果发现,ACE引射喷管在亚声速巡航和超声速巡航状态下的安装推力系数分别为0.979和0.961,在跨声速区段采用中间状态加速时后体阻力系数达到最大,为0.25。亚声速巡航状态下主喷管流量系数最低,为0.896。应用本方法仅需180次低可信度CFD仿真以及173次高可信度CFD仿真即可完成共计33个ACE工作点的引射喷管安装性能计算。

空-油换热器对变循环航空发动机总体性能的影响研究

为解决变循环涡扇发动机涡轮前温度和涡轮冷却气体温度升高使得涡轮冷却效果降低的问题,以航空燃料作为冷源降低涡轮冷却气体温度,将空-油换热器应用在变循环发动机中,建立了变循环发动机的性能仿真模型。同时引入空油换热的冷却性能计算模型,评估采用超临界航空煤油作为冷却介质后,考虑航空煤油超临界喷射、燃烧、涡轮冷却、冷却空气流量、耗油率等参数及相关性能的影响,构建了以超临界航空煤油为纽带的燃烧/冷却热耦合的能量交互分析方法。利用所建立的变循环发动机仿真模型,开展了起飞、快速爬升、超声速巡航、超声速加力和最大推力5种典型飞行状态的总体性能计算,通过比对是否使用空-油换热器对涡轮静叶冷却的计算结果,分析了各个状态下空油换热对变循环发动机总体性能的影响。结果表明:在起飞状态时,采用空-油换热器可以较明显提升发动机总体性能,降低单位燃油消耗率1.86%和提升推力0.95%。因此,通过空-油换热器对变循环航空发动机涡轮冷却气体进行冷却可以有效提高发动机不同状态的性能水平。