片语

blade-tip turbine[动力]

blade-tip leaking flow叶顶泄漏流

blade-tip air-film hole叶片端部气膜孔

blade-tip drive桨尖喷气驱动

blade-tip inner clearance叶尖内部间隙

blade-tip loss桨叶叶尖损失

blade-tip leakage flow叶顶泄漏流

blade-tip with a new shape新型桨尖

英汉例句

• The way to improve total pressure efficiency by appropriate inclined cut of airfoil blade tip was studied.

  分析了对后拖式机翼型叶片的叶尖进行适当切割，可以提高全压效率的原因。

• The blade tip crack of the high pressure turbine is repaired by using the laser welding, which can reduce effectively the repair cost and increase the economic effectiveness of the engine repair.

  采用激光熔焊方法，修复了高压涡轮工作叶片叶尖裂纹，有效降低了发动机修理成本，提高了发动机修理的经济效益。

• This paper also presents the experimental results of effects of the blade tip clearance and the airfoil shape on the stall flutter boundary.

  此外还给出了两种叶尖间隙和两种叶型对失速颤振影响的实验结果。

• Seal coating sprayed is currently used to adjust the gap between the blade tip and engine casing and improve engine efficiency.

  采用喷涂封严涂层的方法调整叶片端部与发动机涡轮机壳之间的间隙以提高发动机效率。

• The mixture was ignited at the blade tip by an automobile sparking plug.

  被点燃的混合物在叶尖的汽车火花塞。

• The paper introduced typical structure of the close clearance seals for blade tip seals in modern aero-turbine and the research progress of gas film seal for gas turbine.

  本文介绍航空燃气轮机转子叶尖「紧间隙」密封的典型结构型式现状，转子内流系统应用气膜密封的有关研究进展。

• The blade tip eddy in axial fan without external duct is observed and caught during experiment.

  实验中观测并捕捉到了无外风筒时轴流通风机内的叶尖涡。

• The calculation method for radial clearance of turbine blade tip considering the effect of temperature and rotational speed is developed in this paper.

  给出了考虑温度和转速影响的涡轮叶尖径向间隙的分析计算方法。

• The gas exciting force caused by blade tip clearance may cause rotors unsteady under certain condition.

  转子偏心引起的气流激振力在一定条件下可能诱发转子失稳。

• The second technique involved using braided solder wick and a soldering iron with a blade tip to remove residual solder from the PCB pad.

  第二个技术工艺涉及到使用网状焊料芯吸法及有刀片尖的焊接烙铁来除去PC B焊盘上的残余焊料。

• In this paper, the influence of tip leakage flow on the 3-d viscous flow field is investigated for different blade tip gap shapes under the condition of rotating hub or stationary hub.

  本文针对几种不同形态的叶栅顶部间隙，在环壁转动与静止的不同情况下，研究间隙内的泄漏流动对三维粘性流场的影响。

• The measurements of hovering blade tip vortex and rotor wake were conducted to investigate the blade tip vortex formation and evolution, and its relationship with the rotor test states.

  为了详细研究悬停旋翼桨尖涡的形成与发展过程，以及旋翼状态参数与桨尖涡及其尾迹的关系，开展了桨尖涡及其尾迹的测量和研究。

• The advanced small gasturbines feature small mass flow ratio, short vanes and blades with low aspect, high second flow and blade tip leakage losses, and low efficiency.

  先进的小发动机涡轮的流量小，叶片短，展弦比低，二次损失及叶尖漏泄损失大，效率低，温度高冷效差。