Technical Memorandum of National Aerospace Laboratory
巻
195
ページ
13
発行年
1971-01
抄録（英）
To improve the performance of a gas turbine,it is required to raise the turbine inlet temperature;and at the same time the blade should be cooled to maintain material properties.Many methods are investigated to cool the turbine blade,for example,internal convection cooling,film cooling,film cooling and transpiration cooling.On the other hand,in order to obtain highly-loaded blades of the compressor,slotted blades are being investigated.Such situations as mentioned above are the same with respect to the aerodynamic behavior.It is,therefore,of interest to know the characteristics of jet flow on an aerofoil surface from the slots.In view of this fundamental situation,the influence of slot configuration and arrangement on the characteristics of jet flow was experimentally investigated,when the jet issued from the slot.
曲面壁上の噴流に対する噴出孔の形状,配列の効果について
naltm00195.pdf
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