Dynamic analysis of flow field at the end of combustor simulator
This study was carried out in order to extend database knowledge about the flow field characteristics and define the various flow field contours inside a combustor simulator. The modern gas turbine industries try to get higher engine efficiencies. Brayton cycle is a key to achieve this purpose. Acco...
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my.utm.468362017-11-01T04:17:13Z http://eprints.utm.my/id/eprint/46836/ Dynamic analysis of flow field at the end of combustor simulator Kianpour, E. Che Sidik, Nor Azwadi Seyyed, Mohsen Agha Bozorg, Mirza TK Electrical engineering. Electronics Nuclear engineering This study was carried out in order to extend database knowledge about the flow field characteristics and define the various flow field contours inside a combustor simulator. The modern gas turbine industries try to get higher engine efficiencies. Brayton cycle is a key to achieve this purpose. According to this cycle industries should increase the turbine inlet temperature to get more engine efficiency and power. However the turbine inlet temperature increasing creates an extremely harsh environment for the downstream critical components such as turbine vanes. In this research a three-dimensional representation of a true Pratt and Whitney aero-engine which studied before in Virginia University was simulated and analyzed to collect essential data. This combustor simulator combined the interaction of two rows of dilution jets, which were staggered in the stream wise direction and aligned in the span wise direction, with that of filmcooling along the combustor liner walls. The overall findings of the study indicate that three-component velocity measurements showed the dilution jet-mainstream interaction produced shear forces and as a result a counter-rotating vortex pair was created. The highest turbulent kinetic energy was found at the top of recirculating region due to the interaction of the second row of dilution jets and mainstream flow. Furthermore, the centers of the counter-rotating vortex pair were spread relatively far apart due to the opposing dilution jets. Along the dilution jet centerline, negative stream wise velocities were measured indicating the recirculation region just downstream of the jet. Into the combustor exit, the acceleration of the flow increased and thereby the uniformity of the velocity profile enhancement was found as well. Penerbit UTM Press 2012 Article PeerReviewed Kianpour, E. and Che Sidik, Nor Azwadi and Seyyed, Mohsen Agha and Bozorg, Mirza (2012) Dynamic analysis of flow field at the end of combustor simulator. Jurnal Teknologi (Sciences and Engineering), 58 (SUP. 2). pp. 1-12. ISSN 0127-9696 http://dx.doi.org/10.11113/jt.v58.1540 |
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TK Electrical engineering. Electronics Nuclear engineering Kianpour, E. Che Sidik, Nor Azwadi Seyyed, Mohsen Agha Bozorg, Mirza Dynamic analysis of flow field at the end of combustor simulator |
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This study was carried out in order to extend database knowledge about the flow field characteristics and define the various flow field contours inside a combustor simulator. The modern gas turbine industries try to get higher engine efficiencies. Brayton cycle is a key to achieve this purpose. According to this cycle industries should increase the turbine inlet temperature to get more engine efficiency and power. However the turbine inlet temperature increasing creates an extremely harsh environment for the downstream critical components such as turbine vanes. In this research a three-dimensional representation of a true Pratt and Whitney aero-engine which studied before in Virginia University was simulated and analyzed to collect essential data. This combustor simulator combined the interaction of two rows of dilution jets, which were staggered in the stream wise direction and aligned in the span wise direction, with that of filmcooling along the combustor liner walls. The overall findings of the study indicate that three-component velocity measurements showed the dilution jet-mainstream interaction produced shear forces and as a result a counter-rotating vortex pair was created. The highest turbulent kinetic energy was found at the top of recirculating region due to the interaction of the second row of dilution jets and mainstream flow. Furthermore, the centers of the counter-rotating vortex pair were spread relatively far apart due to the opposing dilution jets. Along the dilution jet centerline, negative stream wise velocities were measured indicating the recirculation region just downstream of the jet. Into the combustor exit, the acceleration of the flow increased and thereby the uniformity of the velocity profile enhancement was found as well. |
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Kianpour, E. Che Sidik, Nor Azwadi Seyyed, Mohsen Agha Bozorg, Mirza |
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Kianpour, E. Che Sidik, Nor Azwadi Seyyed, Mohsen Agha Bozorg, Mirza |
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Kianpour, E. |
title |
Dynamic analysis of flow field at the end of combustor simulator |
title_short |
Dynamic analysis of flow field at the end of combustor simulator |
title_full |
Dynamic analysis of flow field at the end of combustor simulator |
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Dynamic analysis of flow field at the end of combustor simulator |
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Dynamic analysis of flow field at the end of combustor simulator |
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dynamic analysis of flow field at the end of combustor simulator |
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Penerbit UTM Press |
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2012 |
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http://eprints.utm.my/id/eprint/46836/ http://dx.doi.org/10.11113/jt.v58.1540 |
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