Différences
Ci-dessous, les différences entre deux révisions de la page.
Les deux révisions précédentes Révision précédente Prochaine révision | Révision précédente | ||
public:modeles:rotor_08:accueil [2023/02/21 23:47] – [Modifier - Pane] ikrambeghdadi | public:modeles:rotor_08:accueil [2023/04/05 09:04] (Version actuelle) – modification externe 127.0.0.1 | ||
---|---|---|---|
Ligne 8: | Ligne 8: | ||
<btn type=" | <btn type=" | ||
<modal id=" | <modal id=" | ||
- | **[[https:// | + | **[[https:// |
</ | </ | ||
- | ===== Original model ===== | + | ===== About ===== |
Rotor 8 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 to further study the effects of solidity : rotor 8 with a tip solidity of 1.5, rotor 12 with a tip solidity of 1.7 and rotor 14 with a tip solidity of 1.3. 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. | Rotor 8 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 to further study the effects of solidity : rotor 8 with a tip solidity of 1.5, rotor 12 with a tip solidity of 1.7 and rotor 14 with a tip solidity of 1.3. 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: | + | * Original technical report [(cite: |
author | author | ||
date = {1973}, | date = {1973}, | ||
Ligne 29: | Ligne 29: | ||
< | < | ||
- | |||
- | ===== Useful documents | + | <callout type=" |
* [[https:// | * [[https:// | ||
- | * PDF of the NASA report : {{ : | + | * {{ : |
- | * CSV file of the blade geometry : {{ : | + | * {{ : |
+ | </ | ||
+ | |||
+ | |||
+ | ===== Reference blade ===== | ||
+ | |||
+ | The **reference blade** is defined with multiple-circular arc profiles[(cite: | ||
- | ===== Geometry | + | ==== Geometry ==== |
The geometry of rotor 8 is described in the [[https:// | The geometry of rotor 8 is described in the [[https:// | ||
Ligne 42: | Ligne 47: | ||
{{ : | {{ : | ||
- | ===== Aerodynamic design | + | ==== Aerodynamic design |
- | ^ ^ unit ^ values | + | ^ ^ unit ^ value ^ |
^ pressure ratio | [-] | 1.75 | | ^ pressure ratio | [-] | 1.75 | | ||
^ mass flow | ^ mass flow | ||
Ligne 53: | Ligne 58: | ||
^ rotative speed | [rad/ | ^ rotative speed | [rad/ | ||
- | ===== Material properties | + | ==== Material properties |
- | The original material of the rotor 8 is not defined in the NASA report. | ||
- | Considered properties: | + | The material of rotor 8 is not defined in the original NASA report. A generic titanium |
- | ^ | + | ^ |
^ alloy | [-] | Ti-6Al-4V | ^ alloy | [-] | Ti-6Al-4V | ||
^ Young' | ^ Young' | ||
Ligne 66: | Ligne 70: | ||
^ yield stress | ^ yield stress | ||
- | First three natural frequencies (with clamped root) for the mesh: | ||
- | - <fc # | ||
- | - <fc # | ||
- | - <fc # | ||
- | ===== CAD ===== | + | ==== CAD model ==== |
+ | |||
+ | 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 | ||
+ | | 2 | ||
+ | | 3 | ||
+ | |||
+ | |||
+ | |||
+ | ===== 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 | 1778.69 | ||
+ | | 2 | 2B | 6413.56 | ||
+ | | 3 | 1T | 8747.83 | ||
+ | |||
+ | * from the reduced order model: | ||
+ | |||
+ | ^ Mode ^ Type ^ Natural angular frequency (rad/ | ||
+ | | 1 | 1B | 1778.75 | ||
+ | | 2 | 2B | 6416.20 | ||
+ | | 3 | 1T | 8750.91 | ||
- | {{ : | ||
</ | </ | ||
+ | |||
<pane id=" | <pane id=" | ||
Ligne 81: | Ligne 137: | ||
<btn type=" | <btn type=" | ||
<modal id=" | <modal id=" | ||
- | **[[https:// | + | **[[https:// |
</ | </ | ||
- | ===== Modèle original | + | ===== À propos |
Le rotor 8 fait partie d'un programme de recherche visant à étudier les effets de la solidité des rangées d' | Le rotor 8 fait partie d'un programme de recherche visant à étudier les effets de la solidité des rangées d' | ||
Ligne 103: | Ligne 159: | ||
- | ===== Documents utiles | + | <callout type=" |
* [[https:// | * [[https:// | ||
- | * PDF du rapport de la NASA : {{ : | + | * {{ : |
- | * Fichier CSV de la géométrie : {{ : | + | * {{ : |
+ | </ | ||
- | ===== Géométrie | + | |
+ | |||
+ | ===== Aube de référence | ||
+ | |||
+ | L' | ||
+ | |||
+ | ==== Géométrie | ||
La géométrie du rotor 8 est décrite dans le [[https:// | La géométrie du rotor 8 est décrite dans le [[https:// | ||
Ligne 114: | Ligne 177: | ||
{{ : | {{ : | ||
- | ===== Caractéristiques aérodynamiques | + | ==== Caractéristiques aérodynamiques |
^ ^ unités | ^ ^ unités | ||
^ taux de compression | ^ taux de compression | ||
Ligne 125: | Ligne 188: | ||
- | ===== Propriétés matériau | + | ==== Propriétés matériau |
- | Le matériau original du rotor 8 n'est pas défini dans le rapport de la NASA. | + | Le matériau original du rotor 8 n'est pas défini dans le rapport de la NASA. Un alliage de titane Ti-6Al-4v |
- | + | ||
- | Propriétés considérées : | + | |
^ | ^ | ||
Ligne 138: | Ligne 199: | ||
^ limite élastique | ^ limite élastique | ||
- | |||
- | Fréquences des trois premiers modes (noeuds de la base encastrés) pour le maillage : | ||
- | - <fc # | ||
- | - <fc # | ||
- | - <fc # | ||
Ligne 153: | Ligne 209: | ||
</ | </ | ||
<col md=" | <col md=" | ||
+ | {{ : | ||
< | < | ||
</ | </ | ||
<col md=" | <col md=" | ||
+ | {{ : | ||
< | < | ||
</ | </ | ||
Ligne 169: | Ligne 225: | ||
^ Mode ^ Type ^ Pulsation propre (rad/ | ^ Mode ^ Type ^ Pulsation propre (rad/ | ||
- | | 1 | 1F | 1018,5 | 162,1 | | + | | 1 | 1F | 1779,57 | 283,228 | |
- | | 2 | + | | 2 |
- | | 3 | + | | 3 |
Ligne 185: | Ligne 241: | ||
^ Mode ^ Type ^ Pulsation propre (rad/ | ^ Mode ^ Type ^ Pulsation propre (rad/ | ||
- | | 1 | 1F | 1019,1 | 162,2 | + | | 1 | 1F | 1778,69 | 283,088 | |
- | | 2 | + | | 2 |
- | | 3 | + | | 3 |
Ligne 193: | Ligne 249: | ||
^ Mode ^ Type ^ Pulsation propre (rad/ | ^ Mode ^ Type ^ Pulsation propre (rad/ | ||
- | | 1 | 1F | 1019,1 | + | | 1 | 1F |
- | | 2 | + | | 2 |
- | | 3 | + | | 3 |
- | </ | ||
</ | </ | ||
+ | </ | ||
- public/modeles/rotor_08/accueil.1677041250.txt.gz
- Dernière modification : 2023/04/05 08:59
- (modification externe)