CALCULATION OF TIP CLEARANCE SIZE EFFECTS FOR THE NASA ROTOR 37 COMPRESSOR BLADE  Fulltext 

[ Beheshti ] - Ph.D. Candidate Center of Excellence in Energy Conversion, School of Mechanical Engineering Sharif University of Technology, Tehran-Iran
[ Farhanieh ] - Professor Center of Excellence in Energy Conversion, School of Mechanical Engineering Sharif University of Technology, Tehran-Iran
[ Ghorbanian ] - Associate Professor Center of Excellence in Energy Conversion, School of Mechanical Engineering Sharif University of Technology, Tehran-Iran
[ Teixeira ] - Lecturer Center of Excellence in Energy Conversion, School of Mechanical Engineering Sharif University of Technology, Tehran-Iran

خلاصه مقاله:

Compressors often operate with a tip clearance larger than aerodynamically desired basically due to the changes of tip clearance during operations as well as manufacturing limitations. To assess the effects of tip gap size on the performance of an axial transonic compressor, the through flow in the tip gap region of NASA Rotor 37 compressor blade is numerically studied and compared to aerodynamic probe and laser
anemometer data. The computations show a good agreement. Results discuss how increasing the tip gap size degrades the efficiency, the pressure ratio and the overall performance of axial transonic compressors.

Tip clearance – Gap size – NASA rotor 37 – Transonic compressor – Turbomachinery