turbofan

A design method of QFT robust controller for the turbofan engine based on the Diagonal Dominance Precompensation using the theory of linear matrix inequalities ( LMI) is presented in this thesis.

论文提出了一种基于LMI对角占优预补偿的航空发动机多变量控制系统QFT鲁棒控制器设计方法。

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Simulation results of LTR control for a turbofan engine show the effectiveness of the approach.

将此设计方法应用于某型涡扇发动机的LTR控制,取得了良好的控制效果.

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The results show that a turbofan engine with a small bypass ratio must be installed, and a suitable turbine entry temperature is obtained by optimization with life cycle cost.

结果表明宜采用小涵道比涡扇发动机，而且不考虑费用时涡轮前温度取值越高越好，考虑费用时则有最大值；

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Aerothermodynamic Model of Turbofan Engine With Matlab Description

涡扇发动机气动热力模型的Matlab表达

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A method," gross thrust model", is developed to determine gross thrust of jet engine and afterburning turbofan engine in flight testing.

提出了一种飞机飞行中发动机推力测定的总推力模型。

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An Investigation on Performance of Variable Vane Control Channel for a Turbofan Engine LPC

某涡扇发动机低压压气机叶片角度控制通道性能研究

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Performance optimization of high thrust-weight ratio turbofan engine

高推重比涡扇发动机性能寻优分析研究

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Stability Assessment Test Technology of a Turbofan Engine Inlet Temperature Distortion

某型涡扇发动机进口温度畸变的稳定性评定试验技术研究

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Preliminary analysis of thermodynamic cycle of an intercooled recuperated turbofan engine

中冷回热航空涡扇发动机热力循环初步分析

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Application of SQP to Multi-Object Optimization of Turbofan Engine Acceleration Control

利用SQP控制涡扇发动机加速过程的多目标最优化研究

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The Effect of Thrust Vector Control on the Performance of Turbofan Engine

矢量喷管控制对发动机性能的影响

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Key Technology of Modern High Bypass Ratio Turbofan Engine

现代高涵道比涡扇发动机关键技术

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The effects thrust vectoring angle and angular velocity of vectoring on turbofan engine operation were investigated.

研究了矢量喷管偏转角和偏转角速度对涡扇发动机工作的影响.

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Aerodynamic design characteristic of test cell for-high. by-pass ratio turbofan engine

大函道比涡扇发动机试车台气动力设计的特点

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The optimal control for turbofan engine acceleration control has been investigated. The optimal method used in this paper is Sequential Quadratic Programming ( SQP), one of the most successful methods for solving nonlinear constrained problem.

本文研究了采用非线性规划方法中的序列二次规划最优化方法解决涡轮风扇发动机加速过程的最优控制问题。

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An important concept on the phase of high performance military turbofan engine's designing, throttle ratio, is discussed in this paper.

强调论述了高性能加力涡扇发动机设计论证阶段的个重要概念节流比。

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Also, problems shown at low-altitude(≤ 2km) simulation were pointed out from the characteristics of altitude simulation test for turbofan engines. Technology improvement was proposed.

并根据涡轮风扇发动机高空模拟试验的特点，指出了SB101高空台对涡轮风扇发动机进行低空（≤km）模拟中存在的问题，对存在的问题提出了技术改造方案。

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Intermediate case is an important part of the turbofan engine components.

中介机匣是涡轮风扇发动机的重要承力部件.

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Based on these two real time models, the real time mathematical model of the turbofan engine with thrust vectoring nozzle was acquired.

在以上两个模型的基础上建立了带轴对称矢量喷管的涡扇发动机数学模型。

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Numerical Simulation of the Influence of Nozzle Area Control Accuracy on Turbofan Afterburning Performance

喷管面积调节精度对某型涡扇发动机加力性能影响的数值仿真

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The mathematical model of turbofan engine transient process with thrust vectoring nozzle was established.

建立带矢量喷管的涡扇发动机动态数学模型.

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[ 3]. The paper also points out that the inlet temperature of the turbofan after& burner is low and the temperature exponent of the stability parameter may be smaller than 1.

本文还指出涡轮风扇加力室进口温度低，稳定准则中的温度指数可能小于1。

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The method is applied to a turbofan engine control system, and is demonstrated to be feasibility.

应用于某型航空涡扇发动机控制系统设计, 仿真结果表明了其可行性.

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For correct and wide application of reduced thrust takeoff technique, the temperature characteristics of high bypass ratio turbofan engines and the takeoff performance of large aircrafts were analyzed.

为正确使用和推广减推力起飞技术，分析了高涵道比涡轮风扇发动机温度特性和大型民航机起飞性能。

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The cone gear spoke fracture is briefly described for a typical turbofan.

简要介绍了某型涡扇发动机中下垂直锥齿轮辐板断裂故障.

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The Temperature Distortion Generator ( TDG) design specifications, design technique and the technology of its fabrication were presented. The TDG was tested and calibrated using a turbojet engine and a turbofan engine.

介绍了航空发动机温度畸变试验装置设计技术与研制方法，主要设备及设计技术指标，以及用A型涡轮喷气发动机B型涡轮风扇发动机调试和对比试验结果。

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Application of SQP to acceleration control of turbofan engine

SQP方法在航空发动机加速过程控制中的应用研究

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Research of Turbofan Engine Transient Process with Thrust Vectoring Nozzle

带矢量喷管的涡扇发动机动态过程研究

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Chinese large aircraft turbofan engine must be verified through inclusive to obtain airworthiness certificate.

航空大国在民用和军用航空发动机规范中都有专门条文对包容性做出严格规定，我国自行研制的大飞机涡扇发动机，要取得适航证，就必须通过包容性验证。

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Abnormal vibration has been found on rear installation plane in a turbofan engine durability test.

在某民用涡轮风扇发动机的持久试车过程中,出现了发动机后安装面振动异常的现象.

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