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Les deux révisions précédentes Révision précédente Prochaine révision | Révision précédente | ||
public:modeles:rotor_68:accueil [2023/04/05 09:04] – modification externe 127.0.0.1 | public:modeles:rotor_68:accueil [2023/04/14 12:36] (Version actuelle) – [Fréquences propres] solenekojtych | ||
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To reduce fan noise, an advanced, two-stage, high-pressure-ratio fan having widely spaced blade rows was build and tested. Rotor 68 is the rotor of the second 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 68 is the rotor of the second 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 | ||
- | | + | |
institution | institution | ||
title = {Performance of two-stage fan having low-aspect-ratio first-stage rotor blading}, | title = {Performance of two-stage fan having low-aspect-ratio first-stage rotor blading}, | ||
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* Picture : | * Picture : | ||
{{ : | {{ : | ||
- | < | + | < |
<callout type=" | <callout type=" | ||
* [[https:// | * [[https:// | ||
* {{ : | * {{ : | ||
- | * {{ : | + | * {{ : |
</ | </ | ||
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==== Aerodynamic design | ==== Aerodynamic design | ||
- | ^ ^ | + | ^ ^ |
^ pressure ratio | [-] | 1.54 | | ^ pressure ratio | [-] | 1.54 | | ||
^ mass flow | ^ mass flow | ||
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==== Material properties | ==== Material properties | ||
- | The original material of the rotor 68 is not defined in the NASA report. | + | The original material of the rotor 68 is not defined in the NASA report. |
- | Considered properties: Ti-6Al-4V, generic titanium : | + | ^ |
- | + | ||
- | ^ | + | |
^ alloy | [-] | Ti-6Al-4V | ^ alloy | [-] | Ti-6Al-4V | ||
^ Young' | ^ Young' | ||
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^ Mode ^ Type ^ Natural angular frequency (rad/ | ^ Mode ^ Type ^ Natural angular frequency (rad/ | ||
- | | 1 | 1B | 2492.51 | + | | 1 | 1B | 2492.51 |
- | | 2 | 2B | 7697.97 | + | | 2 | 2B | 7697.97 |
- | | 3 | 1T | 10374.29 | + | | 3 | 1T | 10374.29 |
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* Rapport technique original [(cite: | * Rapport technique original [(cite: | ||
author | author | ||
- | | + | |
institution | institution | ||
title = {Performance of two-stage fan having low-aspect-ratio first-stage rotor blading}, | title = {Performance of two-stage fan having low-aspect-ratio first-stage rotor blading}, | ||
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* Photographie : | * Photographie : | ||
{{ : | {{ : | ||
- | < | + | < |
<callout type=" | <callout type=" | ||
* [[https:// | * [[https:// | ||
* {{ : | * {{ : | ||
- | * {{ : | + | * {{ : |
</ | </ | ||
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==== Propriétés matériau | ==== Propriétés matériau | ||
- | Le matériau original du rotor 68 n'est pas défini dans le rapport de la NASA. | + | Le matériau original du rotor 68 n'est pas défini dans le rapport de la NASA. Un alliage de titane Ti-6Al-4v est considéré : |
- | Propriétés considérées : alliage de titane Ti-6Al-4v : | ||
- | ^ | + | ^ |
^ alliage | ^ alliage | ||
^ module d' | ^ module d' | ||
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^ Mode ^ Type ^ Pulsation propre (rad/ | ^ Mode ^ Type ^ Pulsation propre (rad/ | ||
- | | 1 | + | | 1 |
- | | 2 | + | | 2 |
- | | 3 | 1T | 10374, | + | | 3 | 1T | 10374, |
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^ Mode ^ Type ^ Pulsation propre (rad/ | ^ Mode ^ Type ^ Pulsation propre (rad/ | ||
- | | 1 | + | | 1 |
- | | 2 | + | | 2 |
| 3 | 1T | 10308, | | 3 | 1T | 10308, | ||
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^ Mode ^ Type ^ Pulsation propre (rad/ | ^ Mode ^ Type ^ Pulsation propre (rad/ | ||
- | | 1 | + | | 1 |
- | | 2 | + | | 2 |
| 3 | 1T | 10314, | | 3 | 1T | 10314, | ||
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- Dernière modification : 2023/04/05 09:04
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