| Les deux révisions précédentes Révision précédente Prochaine révision | Révision précédente Prochaine révisionLes deux révisions suivantes |
| public:modeles:rotor_04:accueil [2023/03/19 21:56] – ikrambeghdadi | public:modeles:rotor_04:accueil [2023/03/28 09:35] – solenekojtych |
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| Then, another series of tests has been conducted with blade tip solidities of 1.3 (rotor 14), 1.5 (rotor 8), and 1.7 (rotor 12). Tip solidity are being changed by varying the number of blades while maintaining the same velocity diagrams and flow path. These stages were designed such that the tip solidity of both the rotor and stator blades are the same. | Then, another series of tests has been conducted with blade tip solidities of 1.3 (rotor 14), 1.5 (rotor 8), and 1.7 (rotor 12). Tip solidity are being changed by varying the number of blades while maintaining the same velocity diagrams and flow path. These stages were designed such that the tip solidity of both the rotor and stator blades are the same. |
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| * Original technical report [(cite:janetzke1972design>Janetzke. «Performance of 1380-foot-per-second-tip-speed axial-flow compressor rotor with blade tip solidity of 1.1 » 1972. {{ https://ntrs.nasa.gov/citations/19720011348|pdf}})]: <code>@TechReport{janetzke1972design, | * Original technical report [(cite:janetzke1972design>Janetzke David C., Ball Calvin L. and Hager Roy D.«Performance of 1380-foot-per-second-tip-speed axial-flow compressor rotor with blade tip solidity of 1.1 » 1972. {{ https://ntrs.nasa.gov/citations/19720011348|pdf}})]: <code>@TechReport{janetzke1972design, |
| author = {Janetzke, David C. and Ball, Calvin L. and Hager, Roy D.}, | author = {Janetzke, David C. and Ball, Calvin L. and Hager, Roy D.}, |
| date = {1972}, | date = {1972}, |
| * [[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor04|downloadable models]] (Git project) | * [[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor04|downloadable models]] (Git project) |
| * {{ :public:modeles:rotor_4:rotor4.pdf | NASA technical report}} (.pdf) | * {{ :public:modeles:rotor_4:rotor4.pdf | NASA technical report}} (.pdf) |
| * {{ :public:modeles:rotor_4:rotor4_original.csv | geometrical parameters file}} (.csv), usable as input of OpenMCAD[(cite:Kojtych_2022_gene_aubes>Kojtych S., Batailly A. «OpenMCAD, an open blade generator: from Multiple-Circular-Arc profiles to Computer-Aided Design model» 2022. {{ https://hal.science/hal-03923093|code en libre accès}})] to generate reference blade models. | * {{ :public:modeles:rotor_4:rotor4_original.csv | geometrical parameters file}} (.csv), usable as input of OpenMCAD[(cite:Kojtych_2022_gene_aube>] to generate reference blade models. |
| </callout> | </callout> |
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| <col md="4"> | <col md="4"> |
| {{ :public:modeles:rotor_04:4_intra.png?200 |}} | {{ :public:modeles:rotor_04:4_intra.png?200 |}} |
| <caption>intrados</caption> | <caption>pressure side</caption> |
| </col> | </col> |
| <col md="4"> | <col md="4"> |
| {{ :public:modeles:rotor_04:4_extra.png?200 |}} | {{ :public:modeles:rotor_04:4_extra.png?200 |}} |
| <caption>extrados</caption> | <caption>suction side</caption> |
| </col> | </col> |
| <col md="2"> | <col md="2"> |
| ===== Initial blade ===== | ===== Initial blade ===== |
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| The **initial blade** is defined with in-house LAVA parameters[(cite:Kojtych_2022_Methodology>Kojtych S. //et al//. “Methodology for the Redesign of Compressor Blades Undergoing Nonlinear Structural Interactions: Application to Blade-Tip /Casing Contacts" 2022. Journal of Engineering for Gas Turbines and Power, Vol.145, No.5. {{ https://hal.archives-ouvertes.fr/hal-03795257|pdf}})] obtained from CAD model of the reference vane. The initial blade is conventionally used as a starting point in optimization procedures; its geometry is similar to that of the reference blade. | The **initial blade** is defined with in-house LAVA parameters[(cite:Kojtych_2022_Methodology)] computed from the reference blade CAD model. The initial blade is usually used as starting point for an optimization process. Its geometry is similar to the one of the reference blade. |
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| Ensuite, une autre série d'essais a été menée avec des solidité en tête de 1,3 pour le rotor 14, 1.5 pour le rotor 8 et 1.7 pour le rotor 12. Ces solidités sont modifiées en faisant varier le nombre d'aubes tout en conservant les mêmes triangles de vitesse et le même trajet d'écoulement. Ces étages ont été conçus de manière à ce que la solidité en tête du rotor et du stator soit la même. | Ensuite, une autre série d'essais a été menée avec des solidité en tête de 1,3 pour le rotor 14, 1.5 pour le rotor 8 et 1.7 pour le rotor 12. Ces solidités sont modifiées en faisant varier le nombre d'aubes tout en conservant les mêmes triangles de vitesse et le même trajet d'écoulement. Ces étages ont été conçus de manière à ce que la solidité en tête du rotor et du stator soit la même. |
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| * Rapport technique original [(cite:janetzke1972design>Janetzke. «Performance of 1380-foot-per-second-tip-speed axial-flow compressor rotor with blade tip solidity of 1.1 » 1972. {{ https://ntrs.nasa.gov/citations/19720011348|pdf}})]: <code> | * Rapport technique original[(cite:janetzke1972design>)] : <code> |
| @TechReport{janetzke1972design, | @TechReport{janetzke1972design, |
| author = {Janetzke, David C. and Ball, Calvin L. and Hager, Roy D.}, | author = {Janetzke, David C. and Ball, Calvin L. and Hager, Roy D.}, |
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| </pane> | </pane> |
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