jet engine in which a turbine drives air to the burner

the effects of 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。

modern low bypass ratio turbofan engine is the heart of the new fighter, whose performance and aerodynamic stability greatly affect the characteristics of the new fighter.

涡扇发动机作为现代战斗机的心脏，其性能和稳定性对战斗机的性能和稳定性能有很大的影响。

then the svms of small perturbation about steady points at ground and in flight and also the svm of large perturbation of ground acceleration for a turbofan engine are established by this method.

并应用这种方法建立了某型涡扇发动机在高空稳态工作点处的小偏离状态变量模型，以及地面加速过程的大偏离状态变量模型。

as an example, the development of a high bypass ratio turbofan engine was used to demonstrate how the constraints restrict design cycle parameters.

以发展大涵道比涡扇发动机为例，说明了约束条件对设计循环参数的限制。

a quasi three dimensional flow euler model with viscous force terms was constructed for integrated small turbofan engine systems.

建立了一体化弹用小涡扇发动机系统含粘性力项的準三维欧拉流动模型。

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。

fsqp algorithm based multivariable optimal control method for the acceleration process of turbofan engine is developed.

提出了一种基于fsqp算法的涡扇发动机多变量最优加速控制方法。

based on the configuration of turbofan engine and combining the concept of variable cycle engines, the collectivity configuration of variable cycle engine is analyzed.

基于涡扇发动机的结构平台，围绕变循环概念，分析了变循环发动机的原理与结构。

the development and design features of the high bypass ratio turbofan engine in foreign are comprehensively summarized.

较为系统地总结了国外大涵道比涡扇发动机的研制特点和设计特点。

the mission section, the constrain conditions, the weight composition of the maneuverable missile, and the model of used in turbofan engine maneuverable missile were presented.

简述了飞航导弹任务剖面、约束条件的给定、导弹的重量组成以及涡扇发动机模型。

mirage 2000 uses a snecma m53-p2 turbofan engine which provides 64 kn thrust and 98 kn with afterburn.

幻影2000的动力装置为一个snecma公司的m53-p2涡扇发动机，推力64千牛，加力推力98千牛。

the case study of a high bypass ratio turbofan engine has verified the feasibility of a three-layer back propagation network.

通过一个高涵道比涡扇发动机故障诊断的实例分析，验证了三层逆传播网络的可行性。

an artificial neural network based expert system has been developed and is applied to aircraft turbofan engine fault diagnosis.

介绍了人工神经网络专家系统在航空涡轮风扇发动机故障诊断上的应用。

a method for incorporating linear state inequality constraints in a kalman filter is proposed and applied to turbofan engine health estimation.

提出了一种加入线性不等式约束的卡尔曼滤波方法，并用于涡扇发动机的健康状况估计。

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。

a model of optimizing the turbofan engine performance by adjusting the key sections of components and the program based on the model were developed.

为了解决工程研制中某型涡扇发动机性能调整与优化问题，建立了关键截面调整对发动机特性影响的数学模型并开发了相应的程序。

in this paper, the flow and methods of reliability growth and assessment for a type of turbofan engine are presented.

本文给出了涡扇发动机可靠性增长分析与评估的流程与方法。

as the bypass ratio of turbofan engine is more and more high, fan noise is a more important part to the overall turbofan engine noise.

随着飞机广泛使用的涡轮风扇发动机涵道比的不断提高，风扇噪声在飞机总噪声中占有越来越突出的地位。