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ressources:logiciels:gene_aubes_nasa:geneaubeslisteaubes:rotor_4:accueil [2022/05/12 15:32] – antoinelemery | public:modeles:rotor_04:accueil [2022/09/16 14:13] – alainbatailly | ||
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Ligne 7: | Ligne 7: | ||
+ | <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. | |
+ | 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: | ||
+ | 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:// | ||
+ | </ | ||
+ | * Picture : | ||
+ | {{ : | ||
+ | < | ||
+ | |||
+ | |||
===== Useful documents | ===== Useful documents | ||
- | * PDF of the NASA report : {{ :ressources:logiciels: | + | * PDF of the NASA report : {{ :public:modeles: |
- | * CSV file of the blade geometry : {{ :ressources:logiciels: | + | * CSV file of the blade geometry : {{ :public:modeles: |
- | * CAD of the blade : {{ : | + | |
===== 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 34: | Ligne 49: | ||
^ aspect ratio | [-] | 3 | | ^ aspect ratio | [-] | 3 | | ||
^ number of blades | ^ number of blades | ||
+ | ^ rotative speed | [rad/ | ||
===== Material properties | ===== Material properties | ||
+ | Rotor 4 is made of a 200-grade maraging steel | ||
+ | ^ | ||
+ | ^ alloy | [-] | 18-Ni-200-maraging | ||
+ | ^ Young' | ||
+ | ^ density | ||
+ | ^ Poisson' | ||
+ | ^ yield stress | ||
- | ===== CAO ===== | + | First three natural frequencies (with clamped root) for the mesh: |
+ | - <fc # | ||
+ | - <fc # | ||
+ | - <fc # | ||
+ | ===== CAD ===== | ||
- | {{ :ressources:logiciels: | + | {{ :public:modeles: |
- | ===== Rotors of the same study ===== | + | </ |
+ | |||
+ | <pane id=" | ||
- | ^ rotor n° ^ mass flow (kg/s) ^ aspect ratio ^ dedicated page ^ | + | <btn type=" |
- | | 3 | + | <modal id=" |
- | | 4 | + | **[[https://gitlab.lava.polymtl.ca/ |
- | | 5 | + | </modal> |
- | | 12 | 30.7 | 6.5 | + | |
- | | 14 | 30.7 | 6.5 | + | |
- | </ | + | ===== Modèle original ===== |
- | <pane id=" | + | |
+ | Le rotor 4 fait partie d'un programme de recherche visant à étudier les effets de la solidité de la rangée d' | ||
+ | |||
+ | |||
+ | Ensuite, une autre série d' | ||
- | {{ :ressources:logiciels:gene_aubes_nasa:geneaubeslisteaubes: | + | * Rapport technique original [(cite: |
+ | 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:// | ||
+ | </ | ||
+ | * Photographie : | ||
+ | {{ :public:modeles: | ||
< | < | ||
Ligne 62: | Ligne 99: | ||
===== Documents utiles | ===== Documents utiles | ||
- | * 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 : {{ : | + | |
===== Géométrie ===== | ===== Géométrie ===== | ||
Ligne 70: | Ligne 106: | ||
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 | ||
===== Propriétés matériau | ===== Propriétés matériau | ||
+ | Le matériau du rotor 5 est un alliage à base de nickel : un acier maraging de grade 200 | ||
+ | |||
+ | ^ | ||
+ | ^ alliage | ||
+ | ^ module d' | ||
+ | ^ masse volumique | ||
+ | ^ coefficient de Poisson | ||
+ | ^ limite élastique | ||
+ | |||
+ | Fréquences des trois premiers modes (noeuds de la base encastrés) pour le maillage : | ||
+ | - <fc # | ||
+ | - <fc # | ||
+ | - <fc # | ||
===== CAO ===== | ===== CAO ===== | ||
- | {{ :ressources:logiciels: | + | {{ :public:modeles: |
- | ===== Rotors de la même étude ===== | ||
- | ^ rotor n° ^ solidité en tête ^ allongement | ||
- | | 3 | ||
- | | 4 | ||
- | | 5 | ||
- | | 12 | 1.7 | ||
- | | 14 | 1.3 | ||
</ | </ | ||
</ | </ |
- public/modeles/rotor_04/accueil.txt
- Dernière modification : 2023/04/17 20:36
- de solenekojtych