| 摘要 |
<p>#CMT# #/CMT# The process for making a relief forming disruption of a boundary layer on a wall surface of a compressor blade of gas turbine engine in which a fluid is passed, comprises applying laser shocks on the wall surface to create peaks (R 1, R 2) on edge of the surface as an impact of the shocks. The peaks constitute the disruptive relief. The impacts have a shape of square, rectangular, round or ellipse, and are adjacent or partially covered with one another. Energy applied in function of the impact zone is varied to obtain the disruptive relief with different height. #CMT#USE : #/CMT# The process is useful for making a relief forming disruption of a boundary layer on a wall surface of a compressor blade of gas turbine engine (claimed). #CMT#ADVANTAGE : #/CMT# The process ensures easy and efficient making of the relief with improved mechanical properties thus improving the flow of fluids along the wall surfaces and efficiency of the compressor blade of the gas turbine engine. #CMT#DESCRIPTION OF DRAWINGS : #/CMT# The figure shows a state of a surface of the part after the laser shock impact. I 0 : Central impact zone P : Part R 1, R 2 : Peaks.</p> |
