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public:modeles:rotor_21:accueil [2022/09/16 10:13] – supprimée - modification externe (Unknown date) 127.0.0.1 | public:modeles:rotor_21:accueil [2023/04/05 09:04] (Version actuelle) – modification externe 127.0.0.1 | ||
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+ | ====== Rotor 21 ====== | ||
+ | |||
+ | < | ||
+ | * [[# | ||
+ | * [[# | ||
+ | <pane id=" | ||
+ | |||
+ | <btn type=" | ||
+ | <modal id=" | ||
+ | **[[https:// | ||
+ | </ | ||
+ | ===== About ===== | ||
+ | Rotor 21 is part of a research program to study the experimental performances of a stage when the design blade loading in the rotor tip region has been substantially reduced. In | ||
+ | order to produce the same overall pressure ratio as a reference stage (rotor 11), the blade loading levels in the midspan portion of the present rotor blade had to be relatively high. | ||
+ | |||
+ | * Original technical report [(cite: | ||
+ | author | ||
+ | date = {1978}, | ||
+ | institution | ||
+ | title = {Performance With and Without Inlet Radial Distortion of a Transonic Fan Stage Designed for Reduced Loading in the Tip Region}, | ||
+ | number | ||
+ | url = {https:// | ||
+ | </ | ||
+ | * Picture : | ||
+ | {{ : | ||
+ | < | ||
+ | |||
+ | |||
+ | <callout type=" | ||
+ | * [[https:// | ||
+ | * {{ : | ||
+ | * {{ : | ||
+ | </ | ||
+ | |||
+ | |||
+ | ===== Reference blade ===== | ||
+ | |||
+ | The **reference blade** is defined with multiple-circular arc profiles[(cite: | ||
+ | |||
+ | ===== Geometry ===== | ||
+ | |||
+ | The geometry of rotor 21 is described in the [[https:// | ||
+ | {{ : | ||
+ | |||
+ | ===== Aerodynamic design | ||
+ | |||
+ | ^ ^ unit ^ value ^ | ||
+ | ^ pressure ratio | [-] | 1.57 | | ||
+ | ^ mass flow | ||
+ | ^ tip speed | ||
+ | ^ tip solidity | ||
+ | ^ aspect ratio | [-] | 2.5 | | ||
+ | ^ number of blades | ||
+ | ^ rotative speed | [rad/ | ||
+ | |||
+ | ===== Material properties | ||
+ | |||
+ | The original material of the rotor 21 is not defined in the NASA report. A generic titanium Ti-6Al-4V is considered: | ||
+ | |||
+ | ^ | ||
+ | ^ alloy | [-] | Ti-6Al-4V | ||
+ | ^ Young' | ||
+ | ^ density | ||
+ | ^ Poisson' | ||
+ | ^ yield stress | ||
+ | |||
+ | |||
+ | ==== CAD model ==== | ||
+ | |||
+ | The CAD model is computed with the open source code OpenMCAD[(cite: | ||
+ | |||
+ | < | ||
+ | <col md=" | ||
+ | </ | ||
+ | <col md=" | ||
+ | {{ : | ||
+ | < | ||
+ | </ | ||
+ | <col md=" | ||
+ | {{ : | ||
+ | < | ||
+ | </ | ||
+ | <col md=" | ||
+ | </ | ||
+ | </ | ||
+ | |||
+ | |||
+ | ==== Natural frequencies ==== | ||
+ | |||
+ | |||
+ | First three natural frequencies (with clamped root) for the mesh computed with OpenMCAD[(cite: | ||
+ | |||
+ | ^ Mode ^ Type ^ Natural angular frequency (rad/ | ||
+ | | 1 | 1B | 1512.88 | ||
+ | | 2 | 2B | 5410.9 | ||
+ | | 3 | 1T | 8729.48 | ||
+ | |||
+ | |||
+ | |||
+ | ===== Initial blade ===== | ||
+ | |||
+ | The **initial blade** is defined with in-house LAVA parameters[(cite: | ||
+ | |||
+ | |||
+ | |||
+ | |||
+ | ==== Natural frequencies ==== | ||
+ | |||
+ | First three natural frequencies (with clamped root) | ||
+ | |||
+ | * from the whole mesh: | ||
+ | |||
+ | ^ Mode ^ Type ^ Natural angular frequency (rad/ | ||
+ | | 1 | 1B | 1507.80 | ||
+ | | 2 | 2B | 5410.47 | ||
+ | | 3 | 1T | 8689.96 | ||
+ | |||
+ | |||
+ | * from the reduced order model: | ||
+ | |||
+ | ^ Mode ^ Type ^ Natural angular frequency (rad/ | ||
+ | | 1 | 1B | 1507.89 | ||
+ | | 2 | 2B | 5411.17 | ||
+ | | 3 | 1T | 8691.72 | ||
+ | |||
+ | |||
+ | |||
+ | </ | ||
+ | |||
+ | |||
+ | <pane id=" | ||
+ | |||
+ | <btn type=" | ||
+ | <modal id=" | ||
+ | **[[https:// | ||
+ | </ | ||
+ | |||
+ | ===== À propos ===== | ||
+ | |||
+ | Le rotor 21 fait partie d'un programme de recherche visant à étudier les performances expérimentales d'un étage de soufflante lorsque la charge des aubes dans la région de l' | ||
+ | |||
+ | * Rapport technique original [(cite: | ||
+ | author | ||
+ | date = {1978}, | ||
+ | institution | ||
+ | title = {Performance With and Without Inlet Radial Distortion of a Transonic Fan Stage Designed for Reduced Loading in the Tip Region}, | ||
+ | number | ||
+ | url = {https:// | ||
+ | </ | ||
+ | * Photographie : | ||
+ | |||
+ | {{ : | ||
+ | < | ||
+ | |||
+ | |||
+ | |||
+ | <callout type=" | ||
+ | * [[https:// | ||
+ | * {{ : | ||
+ | * {{ : | ||
+ | </ | ||
+ | |||
+ | |||
+ | ===== Aube de référence ===== | ||
+ | |||
+ | L' | ||
+ | |||
+ | ===== Géométrie ===== | ||
+ | |||
+ | La géométrie du rotor 21 est décrite dans le [[https:// | ||
+ | |||
+ | {{ : | ||
+ | |||
+ | ===== Caractéristiques aérodynamiques | ||
+ | ^ ^ unités | ||
+ | ^ taux de compression | ||
+ | ^ débit massique | ||
+ | ^ vitesse en tête | [m/s] | 425 | | ||
+ | ^ solidité en tête | ||
+ | ^ allongement | ||
+ | ^ nombre d' | ||
+ | ^ vitesse de rotation | ||
+ | |||
+ | ===== Propriétés matériau | ||
+ | |||
+ | Le matériau original du rotor 21 n'est pas défini dans le rapport de la NASA. Un alliage de titane Ti-6Al-4v est considéré : | ||
+ | |||
+ | ^ | ||
+ | ^ alliage | ||
+ | ^ module d' | ||
+ | ^ masse volumique | ||
+ | ^ coefficient de Poisson | ||
+ | ^ limite élastique | ||
+ | |||
+ | |||
+ | ==== Modèle CAO ==== | ||
+ | |||
+ | Le modèle CAO est obtenu avec OpenMCAD[(cite: | ||
+ | |||
+ | < | ||
+ | <col md=" | ||
+ | </ | ||
+ | <col md=" | ||
+ | {{ : | ||
+ | < | ||
+ | </ | ||
+ | <col md=" | ||
+ | {{ : | ||
+ | < | ||
+ | </ | ||
+ | <col md=" | ||
+ | </ | ||
+ | </ | ||
+ | |||
+ | ==== Fréquences propres ==== | ||
+ | |||
+ | Fréquences des trois premiers modes (noeuds du pied d'aube encastrés) pour le maillage obtenu avec OpenMCAD[(cite: | ||
+ | |||
+ | ^ Mode ^ Type ^ Pulsation propre (rad/ | ||
+ | | 1 | 1F | 1512, | ||
+ | | 2 | 2F | 5410, | ||
+ | | 3 | 1T | 8729, | ||
+ | |||
+ | |||
+ | ===== Aube initiale ===== | ||
+ | |||
+ | L' | ||
+ | |||
+ | |||
+ | ==== Fréquences propres ==== | ||
+ | Fréquences des trois premiers modes (noeuds du pied d'aube encastrés), | ||
+ | |||
+ | * pour le maillage complet : | ||
+ | |||
+ | ^ Mode ^ Type ^ Pulsation propre (rad/ | ||
+ | | 1 | 1F | 1507, | ||
+ | | 2 | 2F | 5410, | ||
+ | | 3 | 1T | 8689, | ||
+ | |||
+ | |||
+ | * pour le modèle réduit : | ||
+ | |||
+ | ^ Mode ^ Type ^ Pulsation propre (rad/ | ||
+ | | 1 | 1F | 1507, | ||
+ | | 2 | 2F | 5411, | ||
+ | | 3 | 1T | 8691, | ||
+ | |||
+ | |||
+ | </ | ||
+ | |||
+ | </ | ||
+ | |||
+ | |||
+ | |||
+ | |||
+ | |||
+ | |||