Différences
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 | ||
public:modeles:rotor_04:accueil [2023/03/19 20:27] – [Fréquences propres] ikrambeghdadi | public:modeles:rotor_04:accueil [2023/03/19 21:56] – ikrambeghdadi | ||
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</ | </ | ||
- | ===== 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. | ||
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The **reference blade** is defined with multiple-circular arc profiles[(cite: | 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:// | ||
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- | ===== Aerodynamic design | + | ==== Aerodynamic design |
- | ^ ^ unit ^ values | + | ^ ^ unit ^ value ^ |
^ pressure ratio | [-] | 1.8 | | ^ pressure ratio | [-] | 1.8 | | ||
^ mass flow | ^ mass flow | ||
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^ rotative speed | [rad/ | ^ rotative speed | [rad/ | ||
- | ===== Material properties | + | ==== Material properties |
Rotor 4 is made of a 200-grade maraging steel | Rotor 4 is made of a 200-grade maraging steel | ||
- | ^ | + | ^ |
^ alloy | [-] | 18-Ni-200-maraging | ^ alloy | [-] | 18-Ni-200-maraging | ||
^ Young' | ^ Young' | ||
Ligne 177: | Ligne 177: | ||
- | ===== Géométrie | + | ==== Géométrie ==== |
La géométrie du rotor 4 est décrite dans le [[https:// | La géométrie du rotor 4 est décrite dans le [[https:// | ||
Ligne 183: | Ligne 183: | ||
{{ : | {{ : | ||
- | ===== Caractéristiques aérodynamiques | + | ==== Caractéristiques aérodynamiques |
^ ^ unités | ^ ^ unités | ||
^ taux de compression | ^ taux de compression | ||
Ligne 194: | Ligne 194: | ||
- | ===== Propriétés matériau | + | ==== Propriétés matériau |
Le matériau original du rotor 4 est défini dans le rapport de la NASA. Un acier maraging de grade 200 est considéré: | Le matériau original du rotor 4 est défini dans le rapport de la NASA. Un acier maraging de grade 200 est considéré: |
- public/modeles/rotor_04/accueil.txt
- Dernière modification : 2023/04/17 20:36
- de solenekojtych