Numerical method is utilized to investigate the effects of discrete micro air injection from casing shroud upstream blade tip leading edge on the rotor tip flow in a low-speed isolated axial compressor rotor at the operating condition near stall point.
本文采用数值模拟方法研究了近失速工况动叶顶部前缘附近喷气对低速轴流压气机孤立转子叶顶区域流动的影响。
The influence of air injection on the performance of compressor is analyzed by altering the mass flow rate, injection angle, yaw angle and collocation of injectors.
本文采用数值模拟方法研究了进口叶尖喷气对低速离心压气机稳定工作范围的影响。
In this paper,The effect of air injection on the resistance reduction of stepped planing boat by the several selected combinations of 2 longitudinal centers of gravity,2 forms of step,2 forms of spray strip,5 air flow rates,is investigated experimentally.
StateLaboratoryofHydrodynamicsofChina本文通过2种重心位置、2种断阶方式、2种防溅条形式、5种喷气流量的选择组合 ,研究了在断级滑行艇上气层减阻的实施途径及效果。
A propulsion operating principle was put forward based on the lift operating principle,which introduces a blade-tip jet technique that can enhance the power coefficient of wind turbines significantly,i.
在水平轴风力机升力型工作原理的基础上提出一种新的推力型工作原理,提供一项显著提高风力机风能利用系数的桨尖喷气技术,即充分利用传统升力型风力机风轮旋转离心力在除去整流罩的空心轮毂内产生的低压,将轮毂前方的气体吸入,并通过中空的桨叶,再从桨尖处预先设置的切向孔中与旋转方向反向喷出,从而产生推动风轮旋转的“辅助”转矩,并使发电量和风能利用系数大大提高。
Through analyzing work principle of the wind turbine, a new technique is proposed which uses a method of jet at the blade-tip of wind turbine to enhance the efficiency of wind turbine.
通过对风力机工作原理的分析，提出了一种利用叶尖喷气的方法来提高风力机效率的新型技术。
A new type of trajectory correction execute mechanism - micro impulse jet engine - was put forward that is used in the infantry rocket grenade.
本文针对弹道修正的特点,以单兵火箭弹道修正为应用背景,提出了一种新型弹道修正执行机构——微型脉冲喷气发动机。
The prepulses for the z-pinch neon gas-puff load and the single wire load were both analyzed using Pspice.
z箍缩负载分别采用氖气喷气负载及金属单丝负载。
Numerical simulations and tests were carried out to investigate the effect of ejection from different trailing edge slots of a turbine cascade.
以某涡轮叶栅为研究对象,采用试验和数值模拟相结合的方式研究了涡轮叶片尾缘不同喷气形式对叶栅性能的影响。
A turbine flow control technique using air ejection near blade trailing edge to achieve superior aerodynamic performance is proved numerically by CFD simulation.
研究结果表明:采用尾缘附近喷气的控制方法,能有效地控制涡轮叶片表面边界层分离,从而增大叶栅负荷,并降低气动损失。
Puffing gas can reduce the plasma temperature in the scrape o.
通过喷气和注入杂质获得的部分脱靶等离子体形成了动态气体靶。