Turbine disk is the heart of aero engine.
涡轮盘是航空发动机的心脏。
Honeycomb segment was an important sealing structure of the aero engine.
蜂窝篦齿是航空发动机中的重要封严结构。
Based on this method, a digital tachometer design for aero engine was introduced.
在这个基础上，介绍了一种航空发动机数字转速表设计。
The operation performance of an aero engine fuel nozzle was tested and investigated.
本文对某型航空发动机燃油喷嘴的工作特性和雾化质量进行了试验研究。
This paper discusses how to realize the dynamic decoupling of aero engine by state feedback.
利用状态反馈实现了航空发动机的动态解耦。
The proposed method is illustrated by an example of assembly sequence planning of an aero engine.
最后应用飞机发动机装配实例验证该装配序列规划方法的有效性。
The flow-thermal coupling calculation of aero engine air system includes fluid network and thermal network.
发动机空气系统可分别建立流体网络与热网络进行耦合计算。
Critical technologies for aero engine prognostics and health management systems development were summarized.
总结归纳了航空发动机预测健康管理系统设计的关键技术。
The bearing, as one of the aero engine key component, plays a crucial role on the reliabilities of aero engine.
轴承作为航空发动机的关键部件之一，对发动机的可靠性起着决定性的作用。
The relative correlation distance entropy is applied to fault diagnosis and state recognition of aero engine rotor-case system.
将相对关联距离熵应用于航空发动机转子—机匣系统状态识别和故障诊断。
In this paper, a new variable structure control method, that is, Global variable structure control (GVSC), is introduced to aero engine control system.
针对直接驱动的交流永磁直线伺服系统，提出一种基于神经元补偿控制的全程滑模变结构控制策略。
Now, the system has been used in WS9 engine test in Xi'an Aero Engine Company.
目前本系统已经用于西安航空发动机（集团）有限公司的WS9发动机的试车工作。
Aero engine turbine rotor design is a repeated process that needs much time. There is much work to do to adjust the structural size.
航空发动机涡轮转子设计是一个反复协调的过程，其中存在着大量结构尺寸的调整工作。
The review is absolutely necessary matter and phase in the developing process of an aero-engine. The pertinent and effective review is a great help to the aero-engine being developed.
评审是航空发动机研制过程中一个必不可少，至关重要的阶段，组织缜密、有效地评审对于降低研制风险、缩短周期、减少反复将起到不可或缺的作用。
Movable bailie pressure distortion generator is an important device in aero-engine stability assessment tests.
可移动插板式压力畸变发生器是现代航空发动机稳定性评定试验中的一项关键设备。
Film cooling of the surface of a gas turbine blade was studied in a large-scale low-speed opening wind tunnel according to actual requirement of the design of aero-engine.
根据航空发动机设计的实际需要，在大尺寸低速叶栅传热风洞中对涡轮叶片表面的气膜冷却进行了综合性实验研究。
Blisk is a new integrated structure of blades and disk actually used in the aero-engine of high thrust-weight ratio.
整体叶盘是高推比航空发动机采用的新结构。
The model provides theoretical way for the research of the thermoacoustic oscillation in the aero-engine afterburner.
该模型的建立为预测航空发动机加力燃烧室振荡燃烧特性及控制规律提供了一种理论探索途径。
Turbine starter is a very important composing part for aero-engine, its work capability directly affects the reliability of aero-engine in start.
涡轮起动机是航空发动机的重要组成部分，其工作性能直接影响发动机的起动可靠性。
Finally, two time series and aero-engine spectrometric oil analysis data were used to verify this model.
最后，利用两组实际的航空发动机油样光谱分析数据对模型进行了验证。
An integration system is set up to meet the need for information integration in the process of mold design and manufacture and detection of aero-engine turbo blade by investment casting.
为满足航空发动机涡轮叶片精铸模具设计、制造、叶片铸件检测流程对信息集成的需求，提出构建精铸模具集成设计系统平台。
Combustion instability not only affects the stability of the aero-engine work, but also caused the combustion chamber flame tube thin-walled structure acoustic-vibration coupled fatigue.
燃烧不稳定不仅影响航空发动机的工作稳定性，而且还是造成燃烧室火焰筒薄壁结构声振耦合疲劳破坏的重要原因。
A new neural network adaptive control scheme is presented and its applications to aero-engine control system are researched.
本文研究神经网络自适应控制方法及其在航空发动机控制中应用。
Develop the general version management ante-type system which faces to the design process of aero-engine blade products.
开发面向设计过程的航空发动机叶片广义版本管理原型系统。
According to the calculating methods of current rotor structure dynamic characteristics, a general calculating program of analyzing aero-engine rotor system is developed.
结合现有的转子结构动力特性计算方法，开发出分析航空发动机转子系统动力特性的通用计算程序。
The effect of advanced fuel temperature on the high altitude ignition performance in the prechamber taken from an existent aero-engine at simulated high altitude facility was studied.
在高空模拟实验器上，利用已有的航空发动机预燃室点火器，研究了燃油预热增温对高空低压点火性能的影响。
To satisfy the need of blade geometry inspection and deviation analysis of aero-engine, a non-rigid registration algorithm based on deformation function is proposed.
为满足航空发动机精铸涡轮叶片壁厚偏差分析需要，提出了一种基于变形函数的精铸涡轮叶片检测模型非刚体配准算法。
Rotor unbalancing is one of the main causes of vibration and noise in aero-engine, especially in micro-turbojet engine, which affects work performance and fatigue life directly.
航空发动机尤其是高速旋转的微型涡喷发动机，不平衡是造成转子振动过大以及产生噪音的主要原因之一，直接影响发动机的工作性能和使用寿命。
Presented a new method based on the physical characteristic of aero-engine constraint for performance seeking control, which consists of active set method and generalized reduced gradient method.
提出了一种基于航空发动机约束物理意义的寻优方法，并将其应用于性能寻优控制之中。
Presented a new method based on the physical characteristic of aero-engine constraint for performance seeking control, which consists of active set method and generalized reduced gradient method.
提出了一种基于航空发动机约束物理意义的寻优方法，并将其应用于性能寻优控制之中。
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