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 18:11] – ikrambeghdadi | public:modeles:rotor_04:accueil [2023/03/28 09:31] – [CAD model] solenekojtych | ||
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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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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. | 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: | + | * Original technical report [(cite: |
author | author | ||
date = {1972}, | date = {1972}, | ||
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+ | |||
<callout type=" | <callout type=" | ||
* [[https:// | * [[https:// | ||
- | * PDF of the NASA report : {{ : | + | * {{ : |
- | * CSV file of the blade geometry : {{ : | + | * {{ : |
</ | </ | ||
+ | |||
===== Reference blade ===== | ===== Reference blade ===== | ||
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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' | ||
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</ | </ | ||
<col md=" | <col md=" | ||
- | {{: | + | {{ : |
- | < | + | < |
</ | </ | ||
<col md=" | <col md=" | ||
- | {{: | + | {{ : |
- | < | + | < |
</ | </ | ||
<col md=" | <col md=" | ||
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===== Initial blade ===== | ===== Initial blade ===== | ||
- | The **initial blade** is defined with in-house LAVA parameters[(cite: | + | The **initial blade** is defined with in-house LAVA parameters[(cite: |
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Ensuite, une autre série d' | Ensuite, une autre série d' | ||
- | * Rapport technique original [(cite: | + | * Rapport technique original[(cite: |
@TechReport{janetzke1972design, | @TechReport{janetzke1972design, | ||
author | author | ||
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- | ===== Géométrie | + | ==== Géométrie ==== |
La géométrie du rotor 4 est décrite dans le [[https:// | La géométrie du rotor 4 est décrite dans le [[https:// | ||
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{{ : | {{ : | ||
- | ===== Caractéristiques aérodynamiques | + | ==== Caractéristiques aérodynamiques |
^ ^ unités | ^ ^ unités | ||
^ taux de compression | ^ taux de compression | ||
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- | ===== 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: | ||
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</ | </ | ||
<col md=" | <col md=" | ||
- | {{: | + | {{ : |
< | < | ||
</ | </ | ||
<col md=" | <col md=" | ||
- | {{: | + | {{ : |
< | < | ||
</ | </ | ||
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^ Mode ^ Type ^ Pulsation propre (rad/ | ^ Mode ^ Type ^ Pulsation propre (rad/ | ||
- | | 1 | + | | 1 |
- | | 2 | + | | 2 |
| 3 | 1T | 8874, | | 3 | 1T | 8874, | ||
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^ Mode ^ Type ^ Pulsation propre (rad/ | ^ Mode ^ Type ^ Pulsation propre (rad/ | ||
- | | 1 | + | | 1 |
- | | 2 | + | | 2 |
| 3 | 1T | 8895, | | 3 | 1T | 8895, | ||
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^ Mode ^ Type ^ Pulsation propre (rad/ | ^ Mode ^ Type ^ Pulsation propre (rad/ | ||
- | | 1 | + | | 1 |
- | | 2 | + | | 2 |
| 3 | 1T | 8897, | | 3 | 1T | 8897, | ||
- | </ | ||
</ | </ | ||
+ | </ | ||
- public/modeles/rotor_04/accueil.txt
- Dernière modification : 2023/04/17 20:36
- de solenekojtych