Différences
Ci-dessous, les différences entre deux révisions de la page.
Les deux révisions précédentes Révision précédente Prochaine révision | Révision précédenteDernière révisionLes deux révisions suivantes | ||
ressources:logiciels:gene_aubes_nasa:geneaubeslisteaubes:rotor_4:accueil [2022/09/13 13:34] – [Original model] antoinelemery | public:modeles:rotor_04:accueil [2023/04/17 20:36] – [Propriétés matériau] solenekojtych | ||
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<btn type=" | <btn type=" | ||
<modal id=" | <modal id=" | ||
- | **[[https:// | + | **[[https:// |
</ | </ | ||
- | ===== Original model ===== | + | ===== About ===== |
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 19: | 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. | ||
- | * Original technical report [(cite:reid1978design>Reid. «Design | + | * Original technical report [(cite:janetzke1972design>Janetzke David C., Ball Calvin L. and Hager Roy D.«Performance |
- | author | + | author |
- | title = {Design and overall performance of four highly loaded, high speed inlet stages for an advanced high-pressure-ratio core compressor}, | + | |
- | institution = {NASA Lewis Research Center Cleveland, OH, United States}, | + | institution |
- | note | + | |
+ | number | ||
+ | | ||
+ | } | ||
</ | </ | ||
+ | |||
+ | |||
* Picture : | * Picture : | ||
- | {{ :ressources:logiciels: | + | {{ :public:modeles: |
< | < | ||
- | ===== Useful documents | ||
- | | + | <callout type=" |
- | * CSV file of the blade geometry : {{ :ressources:logiciels: | + | |
+ | * {{ :public:modeles: | ||
+ | * {{ :public:modeles: | ||
+ | </ | ||
+ | |||
+ | |||
+ | ===== Reference blade ===== | ||
+ | |||
+ | The **reference blade** is defined with multiple-circular arc profiles[(cite: | ||
- | ===== 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:rotor_4:gene_aubes_nasa_geom_rotor4.png?400 |}} |
- | ===== Aerodynamic design | ||
- | ^ ^ unit ^ values | + | ==== Aerodynamic design |
+ | |||
+ | ^ ^ unit ^ value ^ | ||
^ pressure ratio | [-] | 1.8 | | ^ pressure ratio | [-] | 1.8 | | ||
^ mass flow | ^ mass flow | ||
Ligne 51: | Ligne 64: | ||
^ rotative speed | [rad/ | ^ rotative speed | [rad/ | ||
- | ===== Material properties | + | ==== Material properties |
- | Rotor 4 is made of a 200-grade maraging steel | + | The material of rotor 4 is defined in the original NASA report. A 200-grade maraging steel is considered: |
- | ^ | + | ^ |
^ alloy | [-] | 18-Ni-200-maraging | ^ alloy | [-] | 18-Ni-200-maraging | ||
^ Young' | ^ Young' | ||
Ligne 62: | Ligne 75: | ||
^ yield stress | ^ yield stress | ||
- | First three natural frequencies (with clamped root) for the mesh: | ||
- | - <fc # | ||
- | - <fc # | ||
- | - <fc # | ||
- | ===== CAD ===== | + | ==== CAD model ==== |
- | {{ :ressources:logiciels:gene_aubes_nasa:geneaubeslisteaubes:rotor_4:gene_aubes_nasa_rotor4_cao.png?400 |}} | + | The CAD model is computed with the open source code OpenMCAD[(cite: |
+ | |||
+ | < | ||
+ | <col md=" | ||
+ | </ | ||
+ | <col md=" | ||
+ | {{ :public:modeles:rotor_04:4_intra.png? | ||
+ | < | ||
+ | </ | ||
+ | <col md=" | ||
+ | {{ :public:modeles: | ||
+ | < | ||
+ | </ | ||
+ | <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 | 1678.08 | ||
+ | | 2 | 2B | 6508.62 | ||
+ | | 3 | 1T | 8874.56 | ||
+ | |||
+ | |||
+ | |||
+ | |||
+ | ===== 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 | 1682.55 | ||
+ | | 2 | 2B | 6515.28 | ||
+ | | 3 | 1T | 8895.29 | ||
+ | |||
+ | |||
+ | * from the reduced order model: | ||
+ | |||
+ | ^ Mode ^ Type ^ Natural angular frequency (rad/ | ||
+ | | 1 | 1B | 1682.57 | ||
+ | | 2 | 2B | 6516.35 | ||
+ | | 3 | 1T | 8897.12 | ||
</ | </ | ||
- | + | ||
<pane id=" | <pane id=" | ||
<btn type=" | <btn type=" | ||
<modal id=" | <modal id=" | ||
- | **[[https:// | + | **[[https:// |
</ | </ | ||
- | ===== Modèle original | + | ===== À propos |
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 87: | Ligne 150: | ||
Ensuite, une autre série d' | Ensuite, une autre série d' | ||
- | * Rapport technique original [(cite:reid1978design>Reid. «Design and overall performance of four highly loaded, high speed inlet stages for an advanced high-pressure-ratio core compressor » 1978. {{ https:// | + | * Rapport technique original[(cite: |
- | author | + | @TechReport{janetzke1972design, |
- | title = {Design and overall performance of four highly loaded, high speed inlet stages for an advanced high-pressure-ratio core compressor}, | + | author |
- | institution = {NASA Lewis Research Center Cleveland, OH, United States}, | + | |
- | note | + | institution |
+ | | ||
+ | number | ||
+ | | ||
+ | } | ||
</ | </ | ||
+ | |||
* Photographie : | * Photographie : | ||
- | {{ :ressources:logiciels: | + | {{ :public:modeles: |
< | < | ||
- | ===== Documents utiles | + | <callout type=" |
+ | * [[https:// | ||
+ | * {{ : | ||
+ | * {{ : | ||
+ | </ | ||
- | * PDF du rapport | + | ===== Aube de référence ===== |
- | * Fichier CSV de la géométrie : {{ : | + | |
- | ===== Géométrie | + | L' |
+ | |||
+ | |||
+ | ==== Géométrie ==== | ||
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 5 est un alliage à base de nickel : un acier maraging de grade 200 | + | Le matériau du rotor 4 est un alliage à base de nickel : un acier maraging de grade 200, mais ses caractéristiques ne sont pas fournies. Les propriétés considérées sont : |
^ | ^ | ||
Ligne 131: | Ligne 205: | ||
^ limite élastique | ^ limite élastique | ||
- | Fréquences des trois premiers modes (noeuds de la base encastrés) pour le maillage : | ||
- | - <fc # | ||
- | - <fc # | ||
- | - <fc # | ||
- | ===== CAO ===== | + | ==== Modèle |
- | {{ :ressources: | + | Le modèle CAO est obtenu avec OpenMCAD[(cite:Kojtych_2022_gene_aubes)]. |
+ | < | ||
+ | <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 | 1678, | ||
+ | | 2 | 2F | 6508, | ||
+ | | 3 | 1T | 8874, | ||
+ | |||
+ | ===== 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 | 1682, | ||
+ | | 2 | 2F | 6515, | ||
+ | | 3 | 1T | 8895, | ||
+ | |||
+ | |||
+ | * pour le modèle réduit : | ||
+ | |||
+ | ^ Mode ^ Type ^ Pulsation propre (rad/ | ||
+ | | 1 | 1F | 1682, | ||
+ | | 2 | 2F | 6516, | ||
+ | | 3 | 1T | 8897, | ||
+ | |||
+ | |||
+ | </ | ||
+ | |||
+ | </ | ||
- public/modeles/rotor_04/accueil.txt
- Dernière modification : 2023/04/17 20:36
- de solenekojtych