片语

turbine rotor blade涡轮叶片

Turbine movable blade动叶涡轮

a turbine rotor blade透平动叶片

turbine cooling blade涡轮冷却叶片

turbine long blade汽轮机长叶片

Turbine fixed blade water定叶水涡轮

turbine bucket[动力] 涡轮机叶片；汽轮机叶片，透平叶片；轮机斗

turbine engine blade涡轮发动机叶片

Turbine moving blade转叶涡轮

Turbine movable blade water动叶水涡轮

英汉例句

• this paper is based on stress analysis of directionally solidified turbine blade with the finite element method. the reliability analysis method with a simple failure model is proposed.

  本文在正交异性材料定向结晶涡轮叶片的应力有限元分析的基础上，以一种简单的破坏模式列出了可靠度的计算方法。

• practical machining has shown that this algorithm is concise and stable, and is engineeringly friendly for turbine blade manufacturing.

  实际加工证明，此算法简洁、稳定，适合涡轮叶片加工的工程需要。

• the author provides a method and sequence for the analytical calculation of turbine blade throat path dimension.

  本文介绍了用解析法计算涡轮叶片喉道尺寸的方法和步骤。

• the wall thickness of the hollow aeroengine turbine blade is a critical parameter for ensuring its strength.

  航空发动机空心涡轮叶片的壁厚是保证叶片强度的一个关键参数。

• the surface of a gas turbine blade was cooled by four rows of cylindrical holes in the experiment.

  实验中对涡轮叶片采用四排气膜孔的冷却方案，气膜孔为圆柱形。

• with the use of holography, the mode, amplitude and phase distribution of gas turbine blade vibration can be determined.

  利用全息照相，我们可以得到燃气轮机叶片振动时的振型、振幅和相位分布。

• this study can be useful in turbine blade cooling design.

  为涡轮叶片的冷却结构设计提供了依据。

• here「s one of the turbine blade segments.

  这里的涡轮叶片部分之一。

• sand making core of turbine blade for aluminum alloy is more difficult.

  涡轮叶片铸件的难点是叶片砂芯的制作。

• this paper studies the problem of tradeoff optimization between damage of reusable liquid propellant rocket engine」s turbine blade and control input sequences during the start-up process.

  针对可重复使用液体火箭发动机起动过程，研究了系统控制输入序列的变化对以涡轮叶片为代表的关键部件累积损伤的影响。

• we find the turbine blade is on the complicated stress status, so four different rules for achieving equivalent stress are used to contrast.

  针对涡轮叶片处于复杂应力状态的情况，分别采用四种不同的等效应力合成準则参照对比，探索其合成方法。

• the heat transfer and characteristics of the fluid flow in the duct of the trailing edge of the turbine blade with parted pin-fin arrays were experimentally investigated.

  本文对具有断裂结构扰流柱的涡轮叶片尾缘楔型通道的流动与换热过程进行了实验研究。

• numerical simulation was used to investigate the heat transfer of a typical turbine blade cooling configuration of ribbed passage and staggered pin fin arrays.

  用数值模拟的方法对一种典型的涡轮叶片尾缘冷却结构进行了数值计算，该冷却结构由横肋通道和交错扰流柱排构成。

• the re-aluminizing technique and coating structure of gas turbine blade made of alloy m38g are studied.

  研究了涡轮叶片材料m38g合金渗稀土-铝涂层的工艺过程和组织结构。

• in this paper, heat transfer and fluid flow in passage for trailing edge of turbine blade with pin-fin arrays is studied numerically.

  本文应用湍流模型对涡轮叶片尾缘针肋通道的换热与流动进行了二维数值模拟研究。

• heat transfer in channel for trailing edge of turbine blade with pin-fin arrays is studied numerically.

  对涡轮叶片尾缘针肋通道的换热进行了数值模拟研究。

• the research results may also help to improve the fabrication processes of directional turbine blade solidification.

  研究结果对于定向凝固涡轮叶片设计、分析方法的完善和成形工艺的改进具有重要意义。

• as one of the core parts of aeronautic engine, turbine blade has increasingly complicated inner structure, which exceedingly obstacles the parting design of precise casting mould of turbine blade.

  涡轮叶片是飞机发动机的核心部件之一，其内部结构日趋复杂，这给涡轮叶片精铸模具的分模设计带来了很大的困难。

• and this paper takes optimization of the turbine blade as an example to verify the effectiveness and maneuverability of the system.

  并以涡轮叶片为例进行优化设计，验证了系统的可行性和可操作性。

• the specific calculation of an existing steam turbine blade row has demonstrated the validity and correctness of the calculation method and procedures.

  通过对某一实际蒸汽透平叶片排的计算，证明计算方法是成功的，计算程序是正确的。

• indian defence ministry sources said the single crystal turbine blade technology, originally denied to indian scientists, has been offered to india by eurojet via the ej200 engine.

  印度国防部消息人士说，单晶涡轮叶片技术，最开始被印度的科学家否认，但现已由eurojet公司通过ej200发动机提供给印度。

• 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。

• improvement of the physics performance of blade is obtained by reconstructing the large size surface of turbine blade based on calculation geometry.

  用计算几何的方法重构大型涡轮叶片曲面，可提高叶片的物理学性能；