thrust-weight ratio

With the development of the aero-engine direction to the high thrust-weight ratio, and turbine inlet gas temperature continuously growing, the ability to endure temperature of existing high temperature alloys has been close to the limit.

随着航空发动机向高推重比方向发展，涡轮前燃气温度不断提高，现有高温合金材料的承温状况都己接近极限。

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Nickel base single crystal superalloy is a key material blade for turbine engine blade having high thrust-weight ratio.

镍基单晶高温合金是高推重比发动机涡轮叶片的关键材料。

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So the research for titanium alloy and other advanced materials is carried out with SPF/ DB process, which has extraordinarily magnitude significance to reduce costs, improve component performance and increase the aircraft thrust-weight ratio.

因此，开展钛合金等先进材料的SPF/DB技术研究，对降低成本，提高构件性能，增加飞机推重比具有非常重要的意义。

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On the other hand, close loop model fuzzy control is studied for a classical thrust vector electrohydraulic servo control system with low damping ratio and improves dynamic performance of the system.

此外，本文根据电液位置伺服系统阻尼比低的特点，采用闭环模型模糊控制，改善了系统的动态性能。

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Aeroengine have been developing with high thrust-weight ratio, large load, high speed and high performance.

航空发动机一直向着高推重比、大载荷、高转速和高性能性发展。

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In hover, and rotor control angles and power required versus advance ratio in forward flight with constant thrust coefficient at trim condition.

等拉力系数配平前飞时，旋翼各操纵角～前进比曲线和前飞需用功率～前进比曲线与德国宇航院（DLR）的试验结果比较一致。

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While the traditional one has low thrust-weight ratio, and deceleration units are needed after drivers' revolving at high speed, both of which result in a complex transmission device and cumbrous structure.

传统的驱动器功重量比低，且驱动器高速运转后需要减速装置变速，致使传动系统复杂、结构累赘。

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The development of higher efficiency and larger thrust-weight ratio of aeroengine has put a further demand on the aerodynamic performance of compressor component.

航空发动机的高效率以及高推重比的发展方向对压气机部件性能提出了更高的要求。

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The drag of cavity decreases with increasing fuel equivalence ratio, and could be converted into the thrust, instead of drag, under combustion mode which is close to real statue of scramjet.

在实际超燃冲压发动机工况下，凹腔火焰稳定器的阻力随着当量比的增加而减小，并最终会表现为正推力。

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Analysis of the Effects of Parameter Small Deviations on a High Thrust-Weight Ratio Aeroengine Performance

参数小偏差对某高推重比航空发动机性能的影响分析

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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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Technical Improvement Scheme Analysis of Thrust-Weight Ratio 10 Aeroengine

推重比10一级发动机技术改进方案分析

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Counter-rotating turbine technology can have great advantages on improving the thrust-weight ratio, specific fuel consumption and the overall performance of an aeroengine, but it also brings a lot of pressing problems.

对转涡轮技术在提高涡轮航空发动机推重比、降低耗油率以及提高飞机的整机性能等方面具有明显的优势，但是同时也带来很多急需解决的问题。

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Current HETs designed based on similarity theory have structure characteristics of narrow channel width, large volume, and high weight, which cause the structure is not sufficiently optimized and hence the overall thrust-weight ratio is small.

由于目前以相似理论为基础设计出的霍尔推力器普遍具有窄放电通道，大体积，高重量等结构特点，使得高功率霍尔推力器结构不够优化，整体推重比较小。

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With the development of gas turbine engines towards high thrust-weight ratio and high power, pollutants discharged from turbine engines has increased steadily.

燃气涡轮发动机向大功率，高推重比方向发展的同时，排气污染也不断增加。

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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。

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Key Manufacturing Technologies of High Thrust-Weight Ratio Engine ( part 1)

21世纪航空制造技术将发生质的飞跃&谈高推重比发动机的关键制造技术（上）

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The relationships among thrust coefficient, torque coefficient, power coefficient and blade top speed ratio of the blade s mentioned above are calculated by optimum Glauert method.

采用优化Glauert方法，对上述3种叶片的推力系数、扭矩系数、功率系数与叶尖速比之间的关系进行了计算。

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Technical Approaches to Thrust-Weight Ratio 12~ 15 of Aeroengine

推重比12～15发动机技术途径分析

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Increasing turbine inlet gas temperature is one of important means to improve turbine efficiency and increase thrust-weight ratio.

提高涡轮前燃气温度是提高涡轮效率、增加推重比的重要手段之一。

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Through analysis, this article points out that how to handle the torque reserve, thrust reserve and speed reserve of the drill rig is the key for the improvement of the utilization ratio and reduction of designed head loss in the hydraulic system.

本文分析指出如何处理液压凿岩钻车的备用扭矩、备用推力和备用速度，是提高液压系统功率利用率，减少设计压力损失的关键。

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Based on the analysis of the requirements of high thrust-weight ratio engine, the feasibility of the new concept is demonstrated.

在分析当前高推重比发动机需求的基础上，结合目前国内外加力燃烧室的技术水平，根据新一代军用发动机的加力燃烧室进气参数，论证了该方案所具有的现实可行性。

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