One is the geared turbofan (GTF), a new type of jet engine from Pratt &Whitney, part of America’s United Technologies group.
一款是来自普惠公司的新型喷气发动机GTF，普惠隶属于美国联合技术公司。
One is the geared turbofan (GTF), a new type of jet engine from Pratt & Whitney, part of America's United Technologies group.
一款是来自普惠公司的新型喷气发动机GTF，普惠隶属于美国联合技术公司。
The solution devised by Pratt & Whitney (P&W), a division of United Technologies, is a “geared turbofan” engine called the PurePower PW1000G.
由普惠提供的解决方案，是名为PurePower PW1000G的齿轮传动涡扇发动机。 普惠是联合科技集团的一个分公司。
Both BA and KLM, after all, had direct experience of what flying through volcanic ash can do to a high-bypass turbofan jet engine.
毕竟，英航和荷航都有用高旁路涡轮风扇喷气式飞机引擎穿越火山灰的经验。
There are 190 C17As in service; the aircraft is propelled by four turbofan engines (of the same type used on the twin-engine Boeing 757) and can drop 102 paratroopers at once.
现在有190架c 17 A在服役。它由四个涡轮发动机驱动，和波音757所用发动机型号相同，一次能够运送102人。
The aircraft employs an adjustable, chin-mounted air intake that supplies air to the single Lyulka-Saturn AL-31FN afterburning turbofan jet engine.
J-10采用了一个可调节机腹进气口为一台留里卡-土星设计局的AL-31FN加力燃烧涡轮风扇发动机提供空气。
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准三维欧拉流动模型。
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。
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。
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。
The new starting model can be applied to other turbofan engine "s starting processes" numerical simulation and design.
可以把这个起动模型应用到其它涡扇发动机的起动过程的模拟和设计中。
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。
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。
The method was satisfactorily applied to the windmilling characteristics test of a turbofan engine.
该方法在某型涡扇发动机风车特性试验中得到了成功应用。
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。
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。
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。
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。
The digital turbofan engine model contains 10 state variables, 12 measurements, 6 control inputs and 8 component health parameters.
涡扇发动机数字模型包含10个状态变量、12个量测量、6个控制输入量以及8个健康状况参数。
The nozzle flow is composed of the main gas stream and the secondary air stream in order to simulate the nozzle of turbofan engine.
喷管中的气流由主流燃气和次流空气组成，用以模拟涡扇发动机的喷管。
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。
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。
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。
Based on a turbofan engine, the afterburner is replaced with pulse detonation combustor to form a turbofan-pulse detonation hybrid engine.
在涡扇发动机基础上，以脉冲爆震燃烧室代替普通加力燃烧室构成涡扇-脉冲爆震组合发动机。
Thermodynamics model of some turbofan engine was established. Working condition of Engine Electronic Controller (EEC) and main fuel pump regulator in laboratory were set up.
建立了某涡扇发动机气动热力学模型和该型发动机综合电子调节器、主燃油泵调节器的实验室工作环境。
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 multivariable neural network adaptive control is provided for a turbofan engine.
提出了一种发动机多变量神经网络控制方法。
On the basis of the thermodynamics model of two-spool turbofan engine, performance of two-spool turbofan engine was improved by after-burning between high and low turbines.
基于双轴涡扇发动机热力学模型，采用高低压涡轮间补燃的方法，实现了对发动机性能的改善。
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。
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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