gas turbine blade造句

• Factors influencing gas turbine blade and vane's life
  影响燃气轮机动静叶寿命的几个因素
• 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。
• 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。
• The mass flow rate coefficients, the heat transfer coefficients and the film effectiveness of cylindrical holes of different part of a gas turbine blade were studied experimentally in the different mainstream reynolds number
  实验中对涡轮叶片上不同部位的圆柱型气膜孔在不同主流雷诺数下的流量系数、气膜孔下游的换热系数和冷却效率进行了实验研究。
• This paper mainly introduces the main failure types of compressor metal components, the inspection and evaluation scope and project of compressor metal components, the materials of gas turbine blades and failure types, etc
  主要介绍了压气机金属部件断裂失效事故的主要类型、压气机部件金属技术监督检查与评估的范围及项目、压气机叶片材料与失效方式等内容，与同行共同探讨。
• 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 . the surface of a gas turbine blade was cooled by cylindrical holes in the experiment, with the hole number of fifteen in stator and eight in rotor
  应航空发动机设计的要求，在大尺寸低速叶栅传热风洞中分别对发动机涡轮导向叶片和动叶表面的气膜冷却特性进行了研究，具体研究在不同气膜孔出流时，在不同主流雷诺数和吹风比情况下叶片表面局部换热系数的分布规律。
• 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 . the surface of a gas turbine blade was cooled by cylindrical holes in the experiment, with the hole number of fifteen in stator and eight in rotor
  应航空发动机设计的要求，在大尺寸低速叶栅传热风洞中分别对发动机涡轮导向叶片和动叶表面的气膜冷却特性进行了研究，具体研究在不同气膜孔出流时，在不同主流雷诺数和吹风比情况下叶片表面局部换热系数的分布规律。
• Above all, the surface of the gas turbine blade including stator and rotor heat transfer coeficience with no film cooling hole was studied with the main stream reynolds number of 150000, 200000 50000, 300000, 350000, 400000 . then, the heat transfer coefficience when all cooling holes opened and only one cooling hole opened was studied partly . and it's studied how the mainstream reynolds number, blowing ratio and the position of holes affect the heat transfer coefficience of the surface of blade
  对导叶和动叶，都是先研究了在150000，200000，250000，300000，350000，400000雷诺数下，没有气膜冷却时的表面换热系数分布，然后研究了气膜孔全打开和只打开单排孔时的表面换热系数分布曲线，重点研究来流雷诺数，吹风比和不同孔位出流对换热系数分布的影响规律。