报道了用热线风速仪和流动可视化技术对带有横向扩展型孔的燃气轮机气膜冷却叶片紊流流场进行的研究。
Hot wire measurements and flow visualization are presented for studying the turbulent flow field over a flat gas turbine film cooling blade with lateral expanded holes.
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。
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.
以带气膜冷却孔的航空燃气涡轮发动机涡轮叶片为研究背景，引入了等效概念对密布小孔结构进行了详细的应力-应变分析。
An equivalent no-perforated plate concept is introduced in the stress-strain analysis for densely-distributed film cooling holes on turbine blades of gas turbine engines.
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。
The surface of a gas turbine blade was cooled by four rows of cylindrical holes in the experiment.
采用实验和数值计算相结合的方法，研究了非定常尾迹对叶片头部气膜冷却的影响。
Secondly, the effects of unsteady wakes on film cooling at the leading edge of blade were investigated by experiments and numerical simulations.
本文用数值方法计算了无气膜冷却涡轮叶片上包括前驻点的整个型面上的换热系数。
Several problems involved in the prediction of heat transfer coefficient on the turbine blade profiles without film cooling are studied in this paper for the purpose of improving the accuracy.
着重介绍了气膜冷却、涡轮叶片内流冷却技术和气膜孔流量系数的研究进展。
Particular emphasis is given to the development of film cooling, internal cooling technologies and film hole discharge coefficients.
对叶片弦中区内部有、无冲击射流的气膜出流冷却方式中，冷气侧气膜孔局部换热特性进行了实验研究。
Experimental investigation of the turbine blade local heat transfer characteristics at the inner side of the mid-chord region near film holes was conducted, with and without impingement cooling.
采用放大的半圆柱状表面模拟涡轮叶片前缘的形状，对叶片前缘单排及两排圆柱形孔的气膜冷却效率进行了测量。
Film cooling effectiveness of hole rows on leading edge of turbine blade has been studied experimentally. The model is a blunt body with a half cylinder leading edge with two flat side walls.
为了探讨在不同径向角下动量比和湍流度对圆柱形气膜孔流动和换热的影响规律，采用数值模拟方法，研究了涡轮叶片的冷却效率。
The cooling effectiveness of cylindrical gas-film cooling holes was numerically investigated, which was determined at different radial angles, momentum ratio and turbulent intensity.
研究了基于叶片弦长的主流雷诺数和二次流-主流流量比对冷却效率的影响，并与叶片上圆柱形孔排的气膜冷却效率分布进行了对比。
The influences of re based on the blade chord length and coolant-gas flux ratio are tested, and comparison is made between the effect of the converging-expanding hole rows and cylindrical hole rows.
采用数值模拟的方法，研究了涡轮叶片尾缘斜劈缝气膜冷却的流场特性，及其对叶背面尾缘温度分布的影响。
Numerical methods are used to investigate the film cooling effect of turbine guide vane's trailing edge.
本文通过水模拟实验，对涡轮叶片气膜冷却时射流的流场进行了研究。
The flow field of film-cooled turbine vane is investigated in this paper with the help of water simulation.
结果表明，叶片前缘压力面侧布置的气膜孔对叶片压力面有很好的冷却效果；
The results show that the cooling effectiveness on concave side is better than suction side with laying film cooling holes in concave side at leading edges of turbine blade.
根据计算结果重点对前缘气膜冷却复杂三维流动以及整个叶片的气膜冷却特性进行分析。
Analysis of simulation results emphasizes on the complex 3d flow due to cooling near leading edge and blade cooling characteristics.
根据计算结果重点对前缘气膜冷却复杂三维流动以及整个叶片的气膜冷却特性进行分析。
Analysis of simulation results emphasizes on the complex 3d flow due to cooling near leading edge and blade cooling characteristics.
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