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

Publish Year: 1384
نوع سند: مقاله کنفرانسی
زبان: English
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شناسه ملی سند علمی:

ISME13_540

تاریخ نمایه سازی: 21 اسفند 1385

Abstract:

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.

Keywords:

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

Authors

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

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