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Ci-dessous, les différences entre deux révisions de la page.
Les deux révisions précédentes Révision précédente Prochaine révision | Révision précédente | ||
public:modeles:rotor_20:accueil [2022/09/16 14:10] – alainbatailly | public:modeles:rotor_20:accueil [2023/04/05 09:04] (Version actuelle) – modification externe 127.0.0.1 | ||
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Ligne 8: | Ligne 8: | ||
<btn type=" | <btn type=" | ||
<modal id=" | <modal id=" | ||
- | **[[https:// | + | **[[https:// |
</ | </ | ||
- | ===== Original model ===== | + | ===== About ===== |
Rotor 20 is part of a research program to study the effect of tip velocity ratio on compressors performances. It has been designed for a stage tip velocity ratio of 0.8. | Rotor 20 is part of a research program to study the effect of tip velocity ratio on compressors performances. It has been designed for a stage tip velocity ratio of 0.8. | ||
- | * Original technical report [(cite: | + | * Original technical report [(cite: |
- | author | + | author |
- | title = {Performance of a Transonic Fan Stage Designed for a Low Meridional Velocity Ratio}, | + | |
- | institution = {NASA Lewis Research Center Cleveland, OH, United States}, | + | institution |
- | note | + | |
+ | number | ||
+ | | ||
</ | </ | ||
* Picture : | * Picture : | ||
Ligne 27: | Ligne 29: | ||
- | ===== Useful documents | + | <callout type=" |
+ | * [[https:// | ||
+ | * {{ : | ||
+ | * {{ : | ||
+ | </ | ||
- | * PDF of the NASA report : {{ : | ||
- | * CSV file of the blade geometry : {{ : | ||
- | ===== Geometry | + | ===== Reference blade ===== |
+ | |||
+ | The **reference blade** is defined with multiple-circular arc profiles[(cite: | ||
+ | |||
+ | ==== Geometry | ||
The geometry of rotor 20 is described in the [[https:// | The geometry of rotor 20 is described in the [[https:// | ||
{{ : | {{ : | ||
- | ===== Aerodynamic design | + | ==== Aerodynamic design |
- | ^ ^ unit ^ values | + | ^ ^ unit ^ value ^ |
^ pressure ratio | [-] | 1.57 | | ^ pressure ratio | [-] | 1.57 | | ||
^ mass flow | ^ mass flow | ||
Ligne 48: | Ligne 56: | ||
^ rotative speed | [rad/ | ^ rotative speed | [rad/ | ||
- | ===== Material properties | + | ==== Material properties |
- | The original material of the rotor 20 is not defined in the NASA report. | + | The original material of the rotor 20 is not defined in the NASA report. |
- | Considered properties: Ti-6Al-4V, generic titanium : | + | ^ |
- | + | ||
- | ^ | + | |
^ alloy | [-] | Ti-6Al-4V | ^ alloy | [-] | Ti-6Al-4V | ||
^ Young' | ^ Young' | ||
Ligne 62: | Ligne 68: | ||
- | First three natural frequencies (with clamped root) for the mesh: | + | ==== CAD model ==== |
- | - <fc #c0c0c0>(1B)</fc>: 1441.5 rad/s | + | |
- | - <fc #c0c0c0>(2B)</fc>: 5124.4 | + | The CAD model is computed |
- | | + | |
+ | <grid> | ||
+ | <col md=" | ||
+ | </col> | ||
+ | <col md=" | ||
+ | {{ :public: | ||
+ | < | ||
+ | </col> | ||
+ | <col md="4"> | ||
+ | {{ : | ||
+ | <caption>suction side</caption> | ||
+ | </ | ||
+ | <col md=" | ||
+ | </ | ||
+ | </ | ||
+ | |||
+ | |||
+ | ==== Natural frequencies ==== | ||
+ | |||
+ | |||
+ | First three natural frequencies (with clamped root) for the mesh computed with OpenMCAD[(cite:Kojtych_2022_gene_aubes)]: | ||
+ | |||
+ | ^ Mode ^ Type ^ Natural angular frequency (rad/sec) ^ Natural frequency (Hz) ^ | ||
+ | | 1 | 1B | 1374.86 | ||
+ | | 2 | 2B | 5070.79 | 807.042 | ||
+ | | 3 | ||
+ | |||
+ | |||
+ | |||
+ | ===== Initial 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. | ||
+ | |||
+ | |||
+ | |||
+ | |||
+ | ==== Natural frequencies ==== | ||
+ | |||
+ | First three natural frequencies (with clamped root) | ||
+ | |||
+ | * from the whole mesh: | ||
+ | |||
+ | ^ Mode ^ Type ^ Natural angular frequency (rad/sec) ^ Natural frequency (Hz) ^ | ||
+ | | 1 | 1B | 1375.47 | 218.913 | ||
+ | | 2 | 2B | 5066.25 | ||
+ | | 3 | 1T | 7896.27 | ||
+ | |||
+ | |||
+ | * from the reduced order model: | ||
+ | |||
+ | ^ Mode ^ Type ^ Natural angular frequency (rad/ | ||
+ | | 1 | 1B | 1375.5 | ||
+ | | 2 | 2B | 5068.12 | ||
+ | | 3 | 1T | 7898.53 | ||
- | ===== CAD ===== | ||
- | {{ : | ||
</ | </ | ||
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<btn type=" | <btn type=" | ||
<modal id=" | <modal id=" | ||
- | **[[https:// | + | **[[https:// |
</ | </ | ||
- | ===== Modèle original | + | ===== À propos |
Le rotor 20 fait partie d'un programme de recherche visant à étudier l' | Le rotor 20 fait partie d'un programme de recherche visant à étudier l' | ||
- | * Rapport technique original [(cite: | + | * Rapport technique original [(cite: |
- | author | + | author |
- | title = {Performance of a Transonic Fan Stage Designed for a Low Meridional Velocity Ratio}, | + | |
- | institution = {NASA Lewis Research Center Cleveland, OH, United States}, | + | institution |
- | note | + | |
+ | number | ||
+ | | ||
+ | | ||
</ | </ | ||
* Photographie : | * Photographie : | ||
Ligne 94: | Ligne 154: | ||
< | < | ||
- | ===== Documents utiles | ||
- | | + | <callout type=" |
- | * Fichier CSV de la géométrie : {{ : | + | |
+ | * {{ : | ||
+ | * {{ : | ||
+ | </ | ||
- | ===== Géométrie | + | |
+ | ===== Aube de référence | ||
+ | |||
+ | L' | ||
+ | |||
+ | ==== Géométrie | ||
La géométrie du rotor 20 est décrite dans le [[https:// | La géométrie du rotor 20 est décrite dans le [[https:// | ||
Ligne 105: | Ligne 172: | ||
{{ : | {{ : | ||
- | ===== Caractéristiques aérodynamiques | + | ==== Caractéristiques aérodynamiques |
^ ^ unités | ^ ^ unités | ||
^ taux de compression | ^ taux de compression | ||
Ligne 115: | Ligne 182: | ||
^ vitesse de rotation | ^ vitesse de rotation | ||
- | ===== Propriétés matériau | + | ==== Propriétés matériau |
- | Le matériau original du rotor 20 n'est pas défini dans le rapport de la NASA. | + | Le matériau original du rotor 20 n'est pas défini dans le rapport de la NASA. Un alliage de titane Ti-6Al-4v |
- | + | ||
- | Propriétés considérées : | + | |
^ | ^ | ||
Ligne 128: | Ligne 193: | ||
^ limite élastique | ^ limite élastique | ||
- | Fréquences des trois premiers modes (noeuds de la base encastrés) pour le maillage : | ||
- | - <fc # | ||
- | - <fc # | ||
- | - <fc # | ||
- | ===== CAO ===== | + | ==== Modèle CAO ==== |
+ | |||
+ | Le modèle | ||
+ | |||
+ | < | ||
+ | <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 | 1374, | ||
+ | | 2 | 2F | 5070, | ||
+ | | 3 | 1T | 7887, | ||
+ | |||
+ | |||
+ | |||
+ | ===== 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 | 1375, | ||
+ | | 2 | 2F | 5066, | ||
+ | | 3 | 1T | 7896, | ||
+ | |||
+ | |||
+ | |||
+ | * pour le modèle réduit : | ||
+ | |||
+ | ^ Mode ^ Type ^ Pulsation propre (rad/ | ||
+ | | 1 | 1F | 1375, | ||
+ | | 2 | 2F | 5068, | ||
+ | | 3 | 1T | 7898, | ||
- | {{ : | ||
</ | </ | ||
</ | </ | ||
- | |||
- public/modeles/rotor_20/accueil.txt
- Dernière modification : 2023/04/05 09:04
- de 127.0.0.1