| Les deux révisions précédentes Révision précédente Prochaine révision | Révision précédente |
| public:modeles:rotor_51a:accueil [2023/04/14 13:36] – [Fréquences propres] solenekojtych | public:modeles:rotor_51a:accueil [2023/04/14 14:25] (Version actuelle) – [À propos] solenekojtych |
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| ===== About ===== | ===== About ===== |
| This report presents the experimental performance for a fan in the series, designated fan stage 5lA. The 12-bladed, 50.8-centimeter-diameter fan was designed for a tip-sgeed of 243.8 meters per second. The design stage pressure rniio was 1.15 at a weight flow of 29.9 kilograms per second. The fan blade angles can be manually reset. Overall performance for both the rotor and the stage along with the blade-element performance of both rotor and stator are presented for the design rotor blade setting angle. | |
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| * Original NASA technical report [(cite:osborn1974performance> «Performance of a 1.15-pressure-ratio Axial-flow Fan Stage with a Blade Tip Solidity of 0.5» 1974. {{ https://ntrs.nasa.gov/citations/19740021256|pdf}})]: <code>@TechReport{osborn1974performance, | Rotor 51A is part of a research program designed to obtain experimental reference information for the selection of fans for propulsion systems for short-haul aircraft using |
| | the externally blown flap as the powered lift system. The rotor 51A is made of 12 blades and was designed for a tip-sgeed of 243.8 meters per second, a design efficiency of 0.863 and a pressure ratio of 1.15. However, experimental values are lower than expected design values (design efficiency: 0.836, pressure ratio: 1.111). The lower than design total pressure ratio was attributed to the failure to obtain the design energy input into the rotor. |
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| | * Original NASA technical report [(cite:osborn1974performance> Osborn W. M., Steinke R. «Performance of a 1.15-pressure-ratio Axial-flow Fan Stage with a Blade Tip Solidity of 0.5» 1974. {{ https://ntrs.nasa.gov/citations/19740021256|pdf}})]: <code>@TechReport{osborn1974performance, |
| author = {Osborn, Walter Martin and Steinke, Ronald J}, | author = {Osborn, Walter Martin and Steinke, Ronald J}, |
| date = {1974}, | date = {1974}, |
| <col md="6"> | <col md="6"> |
| {{ :public:modeles:rotor_51a:gene_aubes_nasa_image_rotor51a_a.jpg?259 |}} | {{ :public:modeles:rotor_51a:gene_aubes_nasa_image_rotor51a_a.jpg?259 |}} |
| <caption>Fig1. https://ntrs.nasa.gov/citations/19740021256 p.67 </caption> | <caption>Fig. 1 https://ntrs.nasa.gov/citations/19740021256 p.67 </caption> |
| </col> | </col> |
| <col md="6"> | <col md="6"> |
| {{ :public:modeles:rotor_51a:gene_aubes_nasa_image_rotor51a_b.jpg?200 |}} | {{ :public:modeles:rotor_51a:gene_aubes_nasa_image_rotor51a_b.jpg?200 |}} |
| <caption>Fig2. https://ntrs.nasa.gov/citations/19740021256 p.67 </caption> | <caption>Fig. 2 https://ntrs.nasa.gov/citations/19740021256 p.67 </caption> |
| </col> | </col> |
| </grid> | </grid> |
| <callout type="info" icon="true" title="Useful documents"> | <callout type="info" icon="true" title="Useful documents"> |
| * [[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor51a|downloadable models]] (Git project) | * [[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor51a|downloadable models]] (Git project) |
| * {{ :public:modeles:rotor_51a:rotor_51a.pdf |NASA technical report}}(.pdf) | * {{ :public:modeles:rotor_51a:rotor_51a.pdf |NASA technical report}} (.pdf) |
| * {{ :public:modeles:rotor_51a:rotor51a_original.csv |}}(.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_51a:rotor51a_original.csv |}} (.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|open source code}})] to generate reference blade models. |
| </callout> | </callout> |
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| ==== Aerodynamic design ==== | ==== Aerodynamic design ==== |
| ^ ^ unit ^ value ^ | ^ ^ units ^ values ^ |
| ^ pressure ratio | [-] | 1.111 | | ^ pressure ratio | [-] | 1.111 | |
| ^ mass flow | [kg/s] | 30.27 | | ^ mass flow | [kg/s] | 30.27 | |
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| ^ ^ unité ^ valeurs ^ | ^ ^ units ^ values ^ |
| ^ alloy | [-] | Ti-6Al-4V | | ^ alloy | [-] | Ti-6Al-4V | |
| ^ Young's modulus | [GPa] | 108 | | ^ Young's modulus | [GPa] | 108 | |
| First three natural frequencies (with clamped root) for the mesh computed with OpenMCAD[(cite:Kojtych_2022_gene_aubes)]: | First three natural frequencies (with clamped root) for the mesh computed with OpenMCAD[(cite:Kojtych_2022_gene_aubes)]: |
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| ^ Mode ^ <fc #ff0000>Type</fc> ^ Natural angular frequency (rad/sec) ^ Natural frequency (Hz) ^ | ^ Mode ^ Type ^ Natural angular frequency (rad/sec) ^ Natural frequency (Hz) ^ |
| | 1 | | 2578.588 | 410.395 | | | 1 | 1B | 2578.588 | 410.395 | |
| | 2 | | 8044.80 | 1280.37 | | | 2 | 2B | 8044.80 | 1280.37 | |
| | 3 | | 10763.98 | 1713.14 | | | 3 | 1T | 10763.98 | 1713.14 | |
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| * from the whole mesh: | * from the whole mesh: |
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| ^ Mode ^ <fc #ff0000>Type</fc> ^ Natural angular frequency (rad/sec) ^ Natural frequency (Hz) ^ | ^ Mode ^ Type ^ Natural angular frequency (rad/sec) ^ Natural frequency (Hz) ^ |
| | 1 | | 2560.66 | 407.541 | | | 1 | 1B | 2560.66 | 407.541 | |
| | 2 | | 8009.99 | 1 274.83 | | | 2 | 2B | 8009.99 | 1 274.83 | |
| | 3 | | 10726.52 | 1 707.18 | | | 3 | 1T | 10726.52 | 1 707.18 | |
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| * from the reduced order model: | * from the reduced order model: |
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| ^ Mode ^ <fc #ff0000>Type</fc> ^ Natural angular frequency (rad/sec) ^ Natural frequency (Hz) ^ | ^ Mode ^ Type ^ Natural angular frequency (rad/sec) ^ Natural frequency (Hz) ^ |
| | 1 | | 2560.75 | 407.556 | | | 1 | 1B | 2560.75 | 407.556 | |
| | 2 | | 8013.95 | 1275.46 | | | 2 | 2B | 8013.95 | 1275.46 | |
| | 3 | | 10729.8 | 1707.7 | | | 3 | 1T | 10729.8 | 1707.7 | |
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| ===== À propos ===== | ===== À propos ===== |
| Ce rapport présente les performances expérimentales d'un ventilateur de la série, désigné étage de ventilateur 5lA. Le ventilateur à 12 pales de 50,8 centimètres de diamètre a été conçu pour une vitesse de pointe de 243,8 mètres par seconde. La pression d'étage de conception était de 1,15 à un débit pondéral de 29,9 kilogrammes par seconde. Les angles des pales du ventilateur peuvent être réinitialisés manuellement. Performances globales pour le rotor. Les performances du rotor et du stator sont présentées pour l'angle de réglage des pales du rotor de conception. | |
| | Le rotor 51A fait partie d'un programme de recherche visant à obtenir des résultats expérimentaux de référence pour la sélection de soufflantes pour les avions court-courrier utilisant des volets à soufflage externe. Le rotor 51A possède 12 pales et a été conçu pour une vitesse de pointe de 243,8 mètres par seconde, un rendement de 0,863 et un taux de compression de 1,151 à vitesse nominale. Toutefois, les caractéristiques expérimentales effectivement mesurées sont inférieures (rendement de 0,836 et taux de compression de 1,111), en raison de l'impossibilité d'obtenir un apport d'énergie suffisant en entrée du rotor. |
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| * Rapport technique original [(cite:osborn1974performance)]: <code>@TechReport{osborn1974performance, | * Rapport technique original [(cite:osborn1974performance)]: <code>@TechReport{osborn1974performance, |
| <col md="6"> | <col md="6"> |
| {{ :public:modeles:rotor_51a:gene_aubes_nasa_image_rotor51a_a.jpg?259 |}} | {{ :public:modeles:rotor_51a:gene_aubes_nasa_image_rotor51a_a.jpg?259 |}} |
| <caption>Fig1. https://ntrs.nasa.gov/citations/19740021256 p.67 </caption> | <caption>Fig. 1 https://ntrs.nasa.gov/citations/19740021256 p.67 </caption> |
| </col> | </col> |
| <col md="6"> | <col md="6"> |
| {{ :public:modeles:rotor_51a:gene_aubes_nasa_image_rotor51a_b.jpg?200 |}} | {{ :public:modeles:rotor_51a:gene_aubes_nasa_image_rotor51a_b.jpg?200 |}} |
| <caption>Fig2. https://ntrs.nasa.gov/citations/19740021256 p.67 </caption> | <caption>Fig. 2 https://ntrs.nasa.gov/citations/19740021256 p.67 </caption> |
| </col> | </col> |
| </grid> | </grid> |
| * [[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor51a|modèles téléchargeables]] (lien vers projet Git) | * [[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor51a|modèles téléchargeables]] (lien vers projet Git) |
| * {{ :public:modeles:rotor_51a:rotor_51a.pdf |rapport technique original}} de la NASA (.pdf) | * {{ :public:modeles:rotor_51a:rotor_51a.pdf |rapport technique original}} de la NASA (.pdf) |
| * {{ :public:modeles:rotor_51a:rotor51a_original.csv |}} (.csv), utilisable en entrée de 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}})] pour générer l'aube de référence | * {{ :public:modeles:rotor_51a:rotor51a_original.csv |}} (.csv), utilisable en entrée de OpenMCAD[(cite:Kojtych_2022_gene_aubes>)] pour générer l'aube de référence |
| </callout> | </callout> |
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| ==== Caractéristiques aérodynamiques ==== | ==== Caractéristiques aérodynamiques ==== |
| ^ ^ unité ^ valeurs ^ | ^ ^ unités ^ valeurs ^ |
| ^ taux de compression | [-] | 1.111 | | ^ taux de compression | [-] | 1.111 | |
| ^ débit massique | [kg/s] | 30.27 | | ^ débit massique | [kg/s] | 30.27 | |