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| public:modeles:rotor_04:accueil [2023/02/24 20:46] – ikrambeghdadi | public:modeles:rotor_04:accueil [2023/03/01 12:02] – [Propriétés matériau] 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}})]: | * 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, |
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| <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}, |
| The geometry of rotor 4 is described in the [[https://ntrs.nasa.gov/citations/19720011348|original NASA report]] by the following tables. The length are in inches and the angles in degrees. | The geometry of rotor 4 is described in the [[https://ntrs.nasa.gov/citations/19720011348|original NASA report]] by the following tables. The length are in inches and the angles in degrees. |
| {{ :public:modeles:rotor_4:gene_aubes_nasa_geom_rotor4.png?400 |}} | {{ :public:modeles:rotor_4:gene_aubes_nasa_geom_rotor4.png?400 |}} |
| {{ :public:modeles:rotor_4:gene_aubes_nasa_geom_rotor3.png?400 |}} | |
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| ===== Aerodynamic design ===== | ===== Aerodynamic design ===== |
| ===== 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>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. |
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| ===== Propriétés matériau ===== | ===== Propriétés matériau ===== |
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| Le matériau du rotor 4 est un alliage à base de nickel : un acier maraging de grade 200 | Le matériau original du rotor 4 est défini dans le rapport de la NASA. Un acier maraging de grade 200 est considéré: |
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| ^ ^ unité ^ valeurs ^ | ^ ^ unité ^ valeurs ^ |
| ===== Aube initiale ===== | ===== Aube initiale ===== |
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| L'**aube initiale** est définie par des paramètres spécifiques au LAVA[(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}})]obtenus à partir du modèle CAO de l'aube de référence. L'aube initiale est classiquement utilisée comme point de départ dans le cadre de procédures d'optimisation; sa géométrie est similaire à celle de l'aube de référence. | L'**aube initiale** est définie par des paramètres spécifiques au LAVA[(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}})] obtenus à partir du modèle CAO de l'aube de référence. L'aube initiale est classiquement utilisée comme point de départ dans le cadre de procédures d'optimisation; sa géométrie est similaire à celle de l'aube de référence. |
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