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- W2363175940 abstract "This paper numerically simutates three rows holes of a high-pressure gas turbine stator on the leading edge.The injection angles of the row of holes are 30°,45°,60° and 90° to the radial direction,respectively,the lateral direction angles are all 90 deg.The pretreatment technology is used in dividing mesh grid.It also analyzes the influence of the leading edge of film cooling effect on the surface aerodynamic parameters and cooling efficiency on condition that the cooling mass flow is 1.25% of main flow and compares and studies the association between the different mass flow rate and flow losses,the efficiency of the turbine stage.The results show that when the radial jet angle decreases,the vibration amplitude of pressure and mach number near the area of cooling hole is weakened,the temperature of the blade decreases with Cooling mass flow increases,but the amplitude of temperature gradually decreases.The total pressure loss coefficient and energy loss coefficient increases with the mass flow increase.The stator inlet flow and efficiency of turbine stage are decreased with the cooling mass flow increased." @default.
- W2363175940 created "2016-06-24" @default.
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- W2363175940 date "2013-01-01" @default.
- W2363175940 modified "2023-09-25" @default.
- W2363175940 title "Numerical Investigation on Influence of Different Angles Holer on Aerodynamic Performance of Turbine" @default.
- W2363175940 hasPublicationYear "2013" @default.
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