The Aerodynamic Effects of the Blade Lean on a High-Aspect-Ratio Transonic Axial Flow Rotor
In this study, the effect of tangential blade lean on the aerodynamic characteristics of low-transonic, high-aspect-ratio axial flow compressor rotor has been investigated by using the computational fluid dynamics. The B-Spline curvature with four control points of 25%, 50%, 75% and 100% of span hav...
| Main Authors: | , , |
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| Format: | Article |
| Language: | English |
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Islamic Azad University-Isfahan (Khorasgan) Branch
2018-06-01
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| Series: | International Journal of Advanced Design and Manufacturing Technology |
| Subjects: | |
| Online Access: | https://admt.isfahan.iau.ir/article_668238_2927ce8152b9f2bc25066f2bd6df2e29.pdf |
| _version_ | 1827791143554777088 |
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| author | Mansour Asghari Mohsen Agha Seyed Mirzabozorg Mahmood Adami |
| author_facet | Mansour Asghari Mohsen Agha Seyed Mirzabozorg Mahmood Adami |
| author_sort | Mansour Asghari |
| collection | DOAJ |
| description | In this study, the effect of tangential blade lean on the aerodynamic characteristics of low-transonic, high-aspect-ratio axial flow compressor rotor has been investigated by using the computational fluid dynamics. The B-Spline curvature with four control points of 25%, 50%, 75% and 100% of span have been used to define the blade stacking line. Various leaned rotors have been created by rotating the circumferential position of control points and they have been simulated by Computational Fluid Dynamics (CFD). At the best state, the leaned blade improves the adiabatic efficiency and total pressure ratio of compressor about 0.55% and 0.75%, respectively. The results show that, lean angle at 100% span has most effect in the peak adiabatic efficiency rather than lean angle at other control points. Also, the results indicate that, in low-transonic, high-aspect-ratio rotor blades, the tangential change of the stacking line only causes the reduction of secondary flow, while the previous studies on high-transonic low-aspect-ratio rotor blades, such as NASA Rotor 37 and NASA Rotor 67 revealed the movement of shock wave toward the downstream and the reduction of the secondary flow. |
| first_indexed | 2024-03-11T17:42:49Z |
| format | Article |
| id | doaj.art-5c6bd01950304d0b967895a5cda62d16 |
| institution | Directory Open Access Journal |
| issn | 2252-0406 2383-4447 |
| language | English |
| last_indexed | 2024-03-11T17:42:49Z |
| publishDate | 2018-06-01 |
| publisher | Islamic Azad University-Isfahan (Khorasgan) Branch |
| record_format | Article |
| series | International Journal of Advanced Design and Manufacturing Technology |
| spelling | doaj.art-5c6bd01950304d0b967895a5cda62d162023-10-18T09:07:40ZengIslamic Azad University-Isfahan (Khorasgan) BranchInternational Journal of Advanced Design and Manufacturing Technology2252-04062383-44472018-06-011128593668238The Aerodynamic Effects of the Blade Lean on a High-Aspect-Ratio Transonic Axial Flow RotorMansour AsghariMohsen Agha Seyed MirzabozorgMahmood AdamiIn this study, the effect of tangential blade lean on the aerodynamic characteristics of low-transonic, high-aspect-ratio axial flow compressor rotor has been investigated by using the computational fluid dynamics. The B-Spline curvature with four control points of 25%, 50%, 75% and 100% of span have been used to define the blade stacking line. Various leaned rotors have been created by rotating the circumferential position of control points and they have been simulated by Computational Fluid Dynamics (CFD). At the best state, the leaned blade improves the adiabatic efficiency and total pressure ratio of compressor about 0.55% and 0.75%, respectively. The results show that, lean angle at 100% span has most effect in the peak adiabatic efficiency rather than lean angle at other control points. Also, the results indicate that, in low-transonic, high-aspect-ratio rotor blades, the tangential change of the stacking line only causes the reduction of secondary flow, while the previous studies on high-transonic low-aspect-ratio rotor blades, such as NASA Rotor 37 and NASA Rotor 67 revealed the movement of shock wave toward the downstream and the reduction of the secondary flow.https://admt.isfahan.iau.ir/article_668238_2927ce8152b9f2bc25066f2bd6df2e29.pdfadiabatic efficiencyaxial flow compressorcfdhigh-aspect-ratiolow-transonic rotortangentially leaned |
| spellingShingle | Mansour Asghari Mohsen Agha Seyed Mirzabozorg Mahmood Adami The Aerodynamic Effects of the Blade Lean on a High-Aspect-Ratio Transonic Axial Flow Rotor International Journal of Advanced Design and Manufacturing Technology adiabatic efficiency axial flow compressor cfd high-aspect-ratio low-transonic rotor tangentially leaned |
| title | The Aerodynamic Effects of the Blade Lean on a High-Aspect-Ratio Transonic Axial Flow Rotor |
| title_full | The Aerodynamic Effects of the Blade Lean on a High-Aspect-Ratio Transonic Axial Flow Rotor |
| title_fullStr | The Aerodynamic Effects of the Blade Lean on a High-Aspect-Ratio Transonic Axial Flow Rotor |
| title_full_unstemmed | The Aerodynamic Effects of the Blade Lean on a High-Aspect-Ratio Transonic Axial Flow Rotor |
| title_short | The Aerodynamic Effects of the Blade Lean on a High-Aspect-Ratio Transonic Axial Flow Rotor |
| title_sort | aerodynamic effects of the blade lean on a high aspect ratio transonic axial flow rotor |
| topic | adiabatic efficiency axial flow compressor cfd high-aspect-ratio low-transonic rotor tangentially leaned |
| url | https://admt.isfahan.iau.ir/article_668238_2927ce8152b9f2bc25066f2bd6df2e29.pdf |
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