本文的实验结果对于航空发动机涡轮叶片冷却结构设计具有参考价值。
The experimental results are valuable reference for aero-engine turbine blade cooling designers.
通过分析三菱M701F燃气轮机叶片冷却技术的冷却原理和运行方式，为燃气轮机的安全高效运行提供参考。
This essay analyzes the cooling principle and the mode of operation of the M701F gas turbine blade cooling technology to verify its efficiency in enhancing the safety of the gas turbine.
根据燃气轮机透平叶片冷却的实际情况，引入并完善叶片冷却的计算模型，并采用文献报道的数据验证计算模型的正确性。
Based on the gas turbine blade's practical cooling condition, a blade cooling computation model is introduced and perfected, and its validity is verified using reported data.
本文以航空发动机涡轮叶片冷却为应用背景，对一种基于彻体力场下热驱动理论的新型冷却技术展开了首次研究，并从机理上验证了此新型冷却技术的强化冷却效果。
In this thesis, a new cooling technique, which is based on the theory of thermally driven, was studied at the background of turbine blade's cooling design in aero-engine.
如果冷凝器叶片被污垢堵塞或者叶片弯曲，这会影响到冷凝器的冷却制冷剂效率。
If the condenser fins are clogged with dirt or bent over, it will affect the ability of the condenser to cool the refrigerant.
通风盘式时制动器在两侧有叶片，空气在泵的作用下流动使制动盘冷却。
Vented disc brakes have a set of vanes, between the two sides of the disc, that pumps air through the disc to provide cooling.
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.
为涡轮叶片的冷却结构设计提供了依据。
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.
叶片内部通道冷却技术在航空发动机叶片的设计中占有重要的位置。
The cooling technique of the blade inner passage plays a significant role in the design of blades for gas turbine.
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.
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.
着重叙述的是叶片的冷却技术对提高透平初温的影响。
This essay mainly specifies the impacts of the blade cooling technique on the turbine initial temperature.
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.
结果表明，采用局部加热冷却的方法可以有效地减小叶片危险区域的残余拉应力峰值。
The result shows that the method of local heating-cooling can decrease the residual tensile stress peak in dangerous area of the blade.
本实验选取航空发动机涡轮叶片中段内部冷却通道为研究对象，对不同肋间距的横肋变截面U型通道的换热特性进行了研究。
The experiment has studied the heat transfer characteristic inside U shaped variable cross-section channels with different rib pitches, The channel is the middle part of a gas turbine blade.
冷却时在叶片的中部y方向残余拉应力有较大增加。
When cooling, the residual tensile stress in the Y direction in the middle of blade increased.
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.
冷却叶片16风的原因周围的空气冷却，其中有有益的效果会加以说明。
The cooling of the blade 16 causes ambient wind air to be cooled which has useful effects as will be described.
涡轮叶片之间冷却空气缝隙的堵塞主要是因为存在高比表面积的超细粒子。
Clogging up of the cooling air slits in the turbine blades is primarily caused by ultrafine particles with a high specific surface area.
高性能工业冷却风扇采用了30英寸直径的叶片。
High Performance Industrial Cooling Fan features a 30 "blade diameter."
为确保堆芯的充分冷却和防止汽轮机叶片的损坏，将SG水位控制在合理的位置是十分重要的。
Properly controlling the water level of SG is very important in order to secure the sufficient cooling source of nuclear reactor and prevent the damage of turbine blades.
本文对涡轮叶片尾缘中具有束腰结构扰流柱的冷却通道的传热和流动阻力特性进行了实验研究，重点研究了雷诺数、扰流柱的束腰比以及不同组合的影响。
The heat transfer and characteristics of the fluid flow in the duct with waist-shaped pin - fin arrays for the trailing edge of the turbine blade were experimentally investigated.
按照涡轮叶片复合冷却的全过程，本文由三部分组成。
In view of the whole process of composite cooling on a turbine blade, this paper is composed of three parts.
涡轮叶片内部冷却特性直接影响到叶片的壁面温度分布，必须对其展开详细的研究。
The temperature distribution of the nozzle guide vanes are affected greatly by the flow and heat transfer of the internal cooling passages.
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.
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.
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.
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