经过十年努力，部分分析家相信，中国终于开始用上了自己的涡扇发动机，这一先进战机不可缺少的技术。
After decades of effort, some analysts believe, China is finally beginning to use its own turbofan engines, an essential technology for advanced fighters.
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。
The solution devised by Pratt & Whitney (P&W), a division of United Technologies, is a “geared turbofan” engine called the PurePower PW1000G.
相较上世纪六十年代声音巨大的喷气式飞机一台现代的涡扇发动机噪音水平降低了80%油耗也下降了一半同时温室气体排放量也有所下降。
Compared with a rowdy 1960s jet, a modern turbofan is some 80% quieter and burns as little as half as much fuel—thus producing fewer greenhouse gases.
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 method was satisfactorily applied to the windmilling characteristics test of a turbofan 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。
Based on a turbofan engine, the afterburner is replaced with pulse detonation combustor to form a turbofan-pulse detonation hybrid engine.
涡扇叶片采用空心结构，由钛合金制造。
建立了带推力矢量的涡扇发动机数学模型。
A mathematical model of turbofan engine with thrust vector control was established.
建立带矢量喷管的涡扇发动机动态数学模型。
The mathematical model of turbofan engine transient process with thrust vectoring nozzle was established.
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。
In this paper, the flow and methods of reliability growth and assessment for a type of turbofan engine are presented.
本文的内容为后续的微涡扇发动机部件设计研究奠定了基础。
The content of this article for follow-up of micro-components turbofan engine research laid the foundation for design.
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 effects of thrust vectoring angle and angular velocity of vectoring on turbofan engine operation were investigated.
起动模型可以应用到其它涡扇发动机的起动过程模拟和设计中。
The new starting model can be applied to other turbofan engine's starting processes' numerical simulation and design.
研究了在外场更换和修理某型涡扇发动机各级风扇叶片的技术。
The field replacing and repairing technologies of various stages fan blades for an turbofan engine were studied.
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。
FSQP algorithm based multivariable optimal control method for the acceleration process of turbofan engine is developed.
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。
A quasi three dimensional flow Euler model with viscous force terms was constructed for integrated small turbofan engine systems.
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。
The new starting model can be applied to other turbofan engine "s starting processes" numerical simulation and design.
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。
The nozzle flow is composed of the main gas stream and the secondary air stream in order to simulate the nozzle of turbofan engine.
本文采用基于LQR的PID控制算法，设计某型号涡扇发动机控制系统。
In this paper, the optimal PID control system for aero-engine was designed using LQR (Linear-Quadratic Regulator) 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.
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。
The case study of a high bypass ratio turbofan engine has verified the feasibility of a three-layer back propagation network.
本文将此方法成功应用于某涡扇发动机，取得了良好的效果，验证了本方法的可行性。
This method has been successfully applied to a turbofan engine and the simulation results show the feasibility and effectiveness of the proposed method.
提出了一种带模糊补偿的神经网络辨识器，并应用在某型涡扇发动机转速控制系统中。
A new neural network algorithm with fuzzy logic compensation was proposed and applied to an aero-engine rotating speed control system.
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。
A method for incorporating linear state inequality constraints in a Kalman filter is proposed and applied to turbofan engine health estimation.
基于各部件特性进行涡扇发动机小偏差模型研究时，需用到风扇和压气机的通用特性图。
The general characteristic maps of fan and Compressor is necessary for turbofan engine little deviation modeling which based on component characteristics.
采用实验方法对某型弹用涡扇发动机涡轮低压导向器原型和改型进行了详细的低速风洞实验。
Detailed flow field measurements were conducted in a low speed wind tunnel for both original and modified LGV's which are used in turbofan engines.
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。
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.
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。
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.
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 digital turbofan engine model contains 10 state variables, 12 measurements, 6 control inputs and 8 component health parameters.
MK2型的机身和尾部结构将进行延寿和重新组装，包括采用重新设计的新型机翼和BR 710涡扇发动机。
MK2 fuselage and empennage structure would be re-lifed and reassembled, with redesigned wings and BR710 turbofan engines.
MK2型的机身和尾部结构将进行延寿和重新组装，包括采用重新设计的新型机翼和BR 710涡扇发动机。
MK2 fuselage and empennage structure would be re-lifed and reassembled, with redesigned wings and BR710 turbofan engines.
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