Différences
Ci-dessous, les différences entre deux révisions de la page.
| Les deux révisions précédentes Révision précédente Prochaine révision | Révision précédente | ||
| public:modeles:rotor_67:accueil [2023/04/05 09:04] – modification externe 127.0.0.1 | public:modeles:rotor_67:accueil [2023/04/14 12:36] (Version actuelle) – [Fréquences propres] solenekojtych | ||
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| Ligne 15: | Ligne 15: | ||
| To reduce fan noise, an advanced, two-stage, high-pressure-ratio fan having widely spaced blade rows was build and tested. Rotor 67 is the rotor of the first stage of this fan. But, the overall efficiency of this two-stage fan was approximately 5 percentage points less than its design value. Analysis of the test results indicated that the first-stage stator and the second stage had potential for good performance but were hampered mainly by the dampered first-stage rotor. The dampers were responsible for large radial gradients of total pressure and deviation angle across a large portion of the blade height, resulting in mismatches in later blade rows. To improve performance of the first stage as well as the stage matching, the original two-stage fan was reconfigured with a newly designed first-stage rotor. Lower-aspect-ratio blading was selected for the rotor to eliminate both the need for part span dampers and their associated penalties on aerodynamic performance. | To reduce fan noise, an advanced, two-stage, high-pressure-ratio fan having widely spaced blade rows was build and tested. Rotor 67 is the rotor of the first stage of this fan. But, the overall efficiency of this two-stage fan was approximately 5 percentage points less than its design value. Analysis of the test results indicated that the first-stage stator and the second stage had potential for good performance but were hampered mainly by the dampered first-stage rotor. The dampers were responsible for large radial gradients of total pressure and deviation angle across a large portion of the blade height, resulting in mismatches in later blade rows. To improve performance of the first stage as well as the stage matching, the original two-stage fan was reconfigured with a newly designed first-stage rotor. Lower-aspect-ratio blading was selected for the rotor to eliminate both the need for part span dampers and their associated penalties on aerodynamic performance. | ||
| - | * Original technical report [(cite: | + | * Original technical report [(cite: |
| author | author | ||
| date = {1979}, | date = {1979}, | ||
| Ligne 27: | Ligne 27: | ||
| {{ : | {{ : | ||
| - | < | + | < |
| - | < | + | * < |
| author | author | ||
| title = {Stage 67 rotor and stage 67 casing half stators mounted. {R}ecords of the {N}ational {A}eronautics and {S}pace {A}dministration, | title = {Stage 67 rotor and stage 67 casing half stators mounted. {R}ecords of the {N}ational {A}eronautics and {S}pace {A}dministration, | ||
| - | note = {\href{https:// | + | year = {1980}, |
| + | url = {https:// | ||
| </ | </ | ||
| Ligne 38: | Ligne 39: | ||
| * [[https:// | * [[https:// | ||
| * {{ : | * {{ : | ||
| - | * {{ : | + | * {{ : |
| </ | </ | ||
| Ligne 52: | Ligne 53: | ||
| ==== Aerodynamic design | ==== Aerodynamic design | ||
| - | ^ ^ unit ^ values | + | ^ |
| - | ^ pressure ratio | [-] | + | ^ pressure ratio | [-] | 1.63 | |
| - | ^ mass flow | + | ^ mass flow |
| - | ^ tip speed | + | ^ tip speed |
| - | ^ tip solidity | + | ^ tip solidity |
| - | ^ aspect ratio | [-] | + | ^ aspect ratio | [-] | 1.56 | |
| - | ^ number of blades | + | ^ number of blades |
| - | ^ rotative speed | [rad/ | + | ^ rotative speed | [rad/ |
| ==== Material properties | ==== Material properties | ||
| - | The original material of the rotor 67 is not defined in the NASA report. | + | The original material of the rotor 67 is not defined in the NASA report. |
| - | Considered properties: Ti-6Al-4V, generic titanium : | + | ^ ^ |
| - | + | ^ alloy | [-] | Ti-6Al-4V | |
| - | ^ | + | ^ Young' |
| - | ^ alloy | [-] | Ti-6Al-4V | + | ^ density |
| - | ^ Young' | + | ^ Poisson' |
| - | ^ density | + | ^ yield stress |
| - | ^ Poisson' | + | |
| - | ^ yield stress | + | |
| Ligne 101: | Ligne 100: | ||
| First three natural frequencies (with clamped root) for the mesh computed with OpenMCAD[(cite: | First three natural frequencies (with clamped root) for the mesh computed with OpenMCAD[(cite: | ||
| - | ^ Mode ^ Type ^ Natural angular frequency (rad/ | + | ^ Mode ^ Type ^ Natural angular frequency (rad/ |
| - | | 1 | 1B | | + | | 1 |
| - | | 2 | 2B | | + | | 2 |
| - | | 3 | 1T | | + | | 3 |
| Ligne 120: | Ligne 119: | ||
| * from the whole mesh: | * from the whole mesh: | ||
| - | ^ Mode ^ Type ^ Natural angular frequency (rad/ | + | ^ Mode ^ Type ^ Natural angular frequency (rad/ |
| - | | 1 | 1B | | + | | 1 |
| - | | 2 | 2B | | + | | 2 |
| - | | 3 | 1T | | + | | 3 |
| * from the reduced order model: | * from the reduced order model: | ||
| - | ^ Mode ^ Type ^ Natural angular frequency (rad/ | + | ^ Mode ^ Type ^ Natural angular frequency (rad/ |
| - | | 1 | 1B | | + | | 1 |
| - | | 2 | 2B | | + | | 2 |
| - | | 3 | 1T | | + | | 3 |
| Ligne 148: | Ligne 147: | ||
| Pour réduire le bruit des soufflantes, | Pour réduire le bruit des soufflantes, | ||
| - | * Rapport technique original [(cite: | + | * Rapport technique original [(cite: |
| author | author | ||
| date = {1979}, | date = {1979}, | ||
| Ligne 163: | Ligne 162: | ||
| - | < | + | * < |
| author | author | ||
| title = {Stage 67 rotor and stage 67 casing half stators mounted. {R}ecords of the {N}ational {A}eronautics and {S}pace {A}dministration, | title = {Stage 67 rotor and stage 67 casing half stators mounted. {R}ecords of the {N}ational {A}eronautics and {S}pace {A}dministration, | ||
| - | note = {\href{https:// | + | year = {1980}, |
| + | url = {https:// | ||
| </ | </ | ||
| Ligne 173: | Ligne 173: | ||
| * [[https:// | * [[https:// | ||
| * {{ : | * {{ : | ||
| - | * {{ : | + | * {{ : |
| </ | </ | ||
| Ligne 198: | Ligne 198: | ||
| ==== Propriétés matériau | ==== Propriétés matériau | ||
| - | Le matériau original du rotor 67 n'est pas défini dans le rapport de la NASA. | + | Le matériau original du rotor 67 n'est pas défini dans le rapport de la NASA. Un alliage de titane Ti-6Al-4v |
| - | + | ||
| - | Propriétés considérées : | + | |
| - | ^ | + | ^ |
| ^ alliage | ^ alliage | ||
| ^ module d' | ^ module d' | ||
| Ligne 233: | Ligne 231: | ||
| Fréquences des trois premiers modes (noeuds du pied d'aube encastrés) pour le maillage obtenu avec OpenMCAD[(cite: | Fréquences des trois premiers modes (noeuds du pied d'aube encastrés) pour le maillage obtenu avec OpenMCAD[(cite: | ||
| - | ^ Mode ^ Type ^ Pulsation propre (rad/ | + | ^ Mode ^ Type ^ Pulsation propre (rad/ |
| - | | 1 | + | | 1 |
| - | | 2 | + | | 2 |
| - | | 3 | 1T | | + | | 3 |
| Ligne 250: | Ligne 248: | ||
| * pour le maillage complet : | * pour le maillage complet : | ||
| - | ^ Mode ^ Type ^ Pulsation propre (rad/ | + | ^ Mode ^ Type ^ Pulsation propre (rad/ |
| - | | 1 | + | | 1 |
| - | | 2 | + | | 2 |
| - | | 3 | 1T | | + | | 3 |
| Ligne 259: | Ligne 257: | ||
| * pour le modèle réduit : | * pour le modèle réduit : | ||
| - | ^ Mode ^ Type ^ Pulsation propre (rad/ | + | ^ Mode ^ Type ^ Pulsation propre (rad/ |
| - | | 1 | + | | 1 |
| - | | 2 | + | | 2 |
| - | | 3 | 1T | | + | | 3 |
| </ | </ | ||
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