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。
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。
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。
In this paper, the chemical contents, microstructure, inclusion, grain size and fracture analysis of the second grade gas turbine blade were investigated.
对燃气轮机二级动叶片失效件进行了化学成分分析、金相组织观察、晶粒度测定、夹杂物检查及断口分析。
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。
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.
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。
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.
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。
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.
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。
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.
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。
Effects of squealer tips on blade aerodynamic performances and tip heat transfer in a gas turbine were investigated.
应用数值方法研究了燃气透平动叶顶部凹槽对动叶气动性能及叶顶传热的影响。
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 measurement under gas turbine operating conditions of disk and blade vibration characteristics constitutes one of the most difficult problems in gas turbine measurement techniques.
在运行条件下实测燃气轮机轮盘和叶片的振动特性，是燃气轮机参数测量中最困难的问题之一。
The cooling technique of the blade inner passage plays a significant role in the design of blades for gas turbine.
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。
Turbine blade including guide blade and work blade is one of the crucial heated end components of gas turbine engine to convert heat energy of burning gas to revolving mechanism kinetic energy.
航空发动机涡轮叶片，包括导向叶片和工作叶片，是将燃气的热能转换为旋转的机械动能的重要的热端部件。
It is very atrocious for turbine blade to revolve rapidly under concussion by high pressure erosive burning gas.
涡轮叶片在高压腐蚀性燃气的冲击下高速旋转，工作条件非常恶劣。
Logical life estimation for the blade of flue gas turbine is one of the most important methods used to protect catalytic cracking unit from failures during operation.
合理准确预测烟气轮机叶片寿命，是催化裂化装置安全运行的必要保障。
While the effect of blade thickening on gas turbine output is very much similar to that of blade deposition, the decrease of output will be evident.
而叶片增厚对燃气轮机输出功率的影响与燃机运行中的积垢非常相似，必然会引起功率下降。因而，本文从理论上阐明了某些燃气轮机出力不足的必然性。
While the effect of blade thickening on gas turbine output is very much similar to that of blade deposition, the decrease of output will be evident.
而叶片增厚对燃气轮机输出功率的影响与燃机运行中的积垢非常相似，必然会引起功率下降。因而，本文从理论上阐明了某些燃气轮机出力不足的必然性。
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