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Ci-dessous, les différences entre deux révisions de la page.
Les deux révisions précédentes Révision précédente Prochaine révision | Révision précédente Prochaine révisionLes deux révisions suivantes | ||
ressources:logiciels:gene_aubes_nasa:geneaubeslisteaubes:rotor_4:accueil [2022/06/06 12:25] – [Aerodynamic design] antoinelemery | public:modeles:rotor_04:accueil [2023/02/21 22:05] – [Fréquences propres] ikrambeghdadi | ||
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* [[# | * [[# | ||
<pane id=" | <pane id=" | ||
+ | |||
+ | |||
+ | <btn type=" | ||
+ | <modal id=" | ||
+ | **[[https:// | ||
+ | </ | ||
+ | |||
+ | ===== Original model ===== | ||
Rotor 4 is part of a research program to study the effects of blade row solidity on efficiency and stall margin of an axial-flow compressor rotor. It is one of a series of rotors designed with varying blade solidity achieved by changing the blade chord length : rotor 3 with a tip solidity of 1.3, rotor 4 with a tip solidity of 1.1 and rotor 5 with a tip solidity of 1.5. The results showed that the efficiency and pressure ratio were higher for a rotor with a blade tip solidity of 1.5 than for a rotor with a solidity of 1.1. | Rotor 4 is part of a research program to study the effects of blade row solidity on efficiency and stall margin of an axial-flow compressor rotor. It is one of a series of rotors designed with varying blade solidity achieved by changing the blade chord length : rotor 3 with a tip solidity of 1.3, rotor 4 with a tip solidity of 1.1 and rotor 5 with a tip solidity of 1.5. The results showed that the efficiency and pressure ratio were higher for a rotor with a blade tip solidity of 1.5 than for a rotor with a solidity of 1.1. | ||
Ligne 11: | Ligne 19: | ||
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. | ||
- | {{ :ressources: | + | * 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:// |
- | <caption>Fig1. https:// | + | |
- | + | < | |
+ | author | ||
+ | title = {Performance of 1380-foot-per-second-tip-speed axial-flow compressor rotor with blade tip solidity of 1.1}, | ||
+ | institution = {NASA Lewis Research Center Cleveland, OH, United States}, | ||
+ | note = {NASA-TM X-2449, url~: \url{https:// | ||
+ | </ | ||
- | ===== Useful documents | + | * Picture : |
+ | {{ : | ||
+ | < | ||
- | | + | |
- | * CSV file of the blade geometry : {{ :ressources:logiciels: | + | ===== Useful documents |
- | * CAD of the blade (mm) : {{ : | + | * [[https:// |
+ | | ||
+ | * CSV file of the blade geometry : {{ :public:modeles: | ||
===== Geometry ===== | ===== Geometry ===== | ||
The geometry of rotor 4 is described in the [[https:// | The geometry of rotor 4 is described in the [[https:// | ||
- | {{ :ressources:logiciels: | + | {{ :public:modeles: |
===== Aerodynamic design | ===== Aerodynamic design | ||
Ligne 41: | Ligne 57: | ||
===== Material properties | ===== Material properties | ||
+ | Rotor 4 is made of a 200-grade maraging steel | ||
+ | ^ | ||
+ | ^ alloy | [-] | 18-Ni-200-maraging | ||
+ | ^ Young' | ||
+ | ^ density | ||
+ | ^ Poisson' | ||
+ | ^ yield stress | ||
- | ===== CAD ===== | + | First three natural frequencies (with clamped root) for the mesh: |
+ | - <fc # | ||
+ | - <fc # | ||
+ | - <fc # | ||
- | {{ : | + | ==== CAD model ==== |
- | ===== Rotors of the same study ===== | + | 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 | 1F | 1018, | ||
+ | | 2 | 1T | 3542, | ||
+ | | 3 | 2F | 6094, | ||
+ | |||
+ | |||
+ | |||
+ | |||
+ | ===== 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 | 1F | 1019, | ||
+ | | 2 | 1T | 3539, | ||
+ | | 3 | 2F | 6074, | ||
+ | |||
+ | |||
+ | * from the reduced order model: | ||
+ | |||
+ | ^ Mode ^ Type ^ Natural angular frequency (rad/ | ||
+ | | 1 | 1F | 1019, | ||
+ | | 2 | 1T | 3540, | ||
+ | | 3 | 2F | 6075, | ||
- | ^ rotor n° ^ pressure ratio ^ mass flow (kg/ | ||
- | | 3 | ||
- | | 4 | ||
- | | 5 | ||
- | | 8 | ||
- | | 12 | 1.75 | 29.5 | 423 | 1.7 | ||
- | | 14 | 1.75 | 29.5 | 423 | 1.3 | ||
</ | </ | ||
- | + | ||
<pane id=" | <pane id=" | ||
+ | |||
+ | <btn type=" | ||
+ | <modal id=" | ||
+ | **[[https:// | ||
+ | </ | ||
+ | |||
+ | ===== Modèle original ===== | ||
Le rotor 4 fait partie d'un programme de recherche visant à étudier les effets de la solidité de la rangée d' | Le rotor 4 fait partie d'un programme de recherche visant à étudier les effets de la solidité de la rangée d' | ||
Ligne 65: | Ligne 145: | ||
Ensuite, une autre série d' | Ensuite, une autre série d' | ||
+ | * Rapport technique original [(cite: | ||
+ | @TechReport{janetzke1972design, | ||
+ | author | ||
+ | date = {1972}, | ||
+ | institution | ||
+ | title = {Performance of 1380-foot-per-second-tip-speed axial-flow compressor rotor with blade tip solidity of 1.1}, | ||
+ | number | ||
+ | url = {https:// | ||
+ | } | ||
+ | </ | ||
- | {{ :ressources: | + | * Photographie : |
+ | {{ :public:modeles: | ||
< | < | ||
===== Documents utiles | ===== Documents utiles | ||
- | + | * [[https:// | |
- | * PDF du rapport de la NASA : {{ :ressources:logiciels: | + | * PDF du rapport de la NASA : {{ :public:modeles: |
- | * Fichier CSV de la géométrie : {{ :ressources:logiciels: | + | * Fichier CSV de la géométrie : {{ :public:modeles: |
- | * CAO de l'aube (en mm) : {{ : | + | |
===== Géométrie ===== | ===== Géométrie ===== | ||
Ligne 80: | Ligne 170: | ||
La géométrie du rotor 4 est décrite dans le [[https:// | La géométrie du rotor 4 est décrite dans le [[https:// | ||
- | {{ :ressources:logiciels: | + | {{ :public:modeles: |
===== Caractéristiques aérodynamiques | ===== Caractéristiques aérodynamiques | ||
^ ^ unités | ^ ^ unités | ||
- | ^ taux de compression | + | ^ taux de compression |
- | ^ débit massique | + | ^ débit massique |
- | ^ vitesse en tête | [m/s] | 420.6 | | + | ^ vitesse en tête | [m/s] | 420,6 | |
- | ^ solidité en tête | + | ^ solidité en tête |
^ allongement | ^ allongement | ||
^ nombre d' | ^ nombre d' | ||
- | ^ vitesse de rotation | + | ^ vitesse de rotation |
===== Propriétés matériau | ===== Propriétés matériau | ||
+ | Le matériau du rotor 4 est un alliage à base de nickel : un acier maraging de grade 200 | ||
- | ===== CAO ===== | + | ^ |
+ | ^ alliage | ||
+ | ^ module d' | ||
+ | ^ masse volumique | ||
+ | ^ coefficient de Poisson | ||
+ | ^ limite élastique | ||
- | {{ :ressources:logiciels:gene_aubes_nasa:geneaubeslisteaubes: | + | Fréquences des trois premiers modes (noeuds de la base encastrés) pour le maillage |
+ | - <fc # | ||
+ | - <fc # | ||
+ | - <fc # | ||
- | ===== Rotors de la même étude | + | ==== Modèle CAO ==== |
- | ^ rotor n° ^ taux de compression | + | |
- | | 3 | + | |
- | | 4 | + | |
- | | 5 | + | |
- | | 8 | + | |
- | | 12 | 1.75 | + | |
- | | 14 | 1.75 | + | |
- | </ | + | |
- | </ | + | |
+ | 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 | ||
+ | | 2 | ||
+ | | 3 | ||
+ | |||
+ | ===== Aube initiale ===== | ||
+ | |||
+ | L' | ||
+ | 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' | ||
+ | |||
+ | |||
+ | ==== Fréquences propres ==== | ||
+ | Fréquences des trois premiers modes (noeuds du pied d'aube encastrés), | ||
+ | |||
+ | * pour le maillage complet : | ||
+ | |||
+ | ^ Mode ^ Type ^ Pulsation propre (rad/ | ||
+ | | 1 | 1F | 1019, | ||
+ | | 2 | 1T | 3539, | ||
+ | | 3 | 2F | 6074, | ||
+ | |||
+ | |||
+ | * pour le modèle réduit : | ||
+ | |||
+ | ^ Mode ^ Type ^ Pulsation propre (rad/ | ||
+ | | 1 | 1F | 1019, | ||
+ | | 2 | 1T | 3540, | ||
+ | | 3 | 2F | 6075, | ||
+ | |||
+ | |||
+ | </ | ||
+ | </ | ||
- public/modeles/rotor_04/accueil.txt
- Dernière modification : 2023/04/17 20:36
- de solenekojtych