Différences

Ci-dessous, les différences entre deux révisions de la page.

--- public:modeles:rotor_01:accueil [2023/01/16 15:06] – [Modifier - Pane] solenekojtych
+++ public:modeles:rotor_01:accueil [2023/04/05 09:04] (Version actuelle) – modification externe 127.0.0.1
@@ Ligne 6: / Ligne 6: @@
 <pane id="tab-en">
-<btn type="warning" size="md" modal="modal_en">Downloadable files</btn>
+<btn type="warning" size="md" modal="modal_en">Downloadable models</btn>
 <modal id="modal_en" title="Open access">
-**[[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/rotor1|Git project]]**
+**[[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor01|Git project]]**
 </modal>
-===== Original model =====
+===== About =====
 Rotor 1 is part of a research program to study aspect ratio because the use of high aspect ratio blading can lead to a decrease in the axial length of compressors and therefore a reduction of their size and weight. To investigate the effects of aspect ratio on compressor range and efficiency, two transonic rotors (rotor 1 and 2) were designed and tested. The variation in aspect ratio was based on a change in aerodynamic chord, and the solidity was kept the same by varying the number of blades.
-  * Original technical report [(cite:hager1974design>Hager. «Effect of damper on overall and blade-element performance of a compressor rotor having a tip speed of 1151 feet per second and an aspect ratio of 3.6 » 1974.  {{ https://ntrs.nasa.gov/citations/19740018135|pdf}})]: <code>@TechReport{hager1974design,
+  * Original NASA technical report [(cite:hager1974design>Hager. «Effect of damper on overall and blade-element performance of a compressor rotor having a tip speed of 1151 feet per second and an aspect ratio of 3.6 » 1974.  {{ https://ntrs.nasa.gov/citations/19740018135|pdf}})]:  <code>@TechReport{hager1974design,
-author      = {Hager, Roy D. and Lewis, George W.},
+  author           = {Hager, Roy D. and Lewis, George W.},
-title       = {Effect of damper on overall and blade-element performance of a compressor rotor having a tip speed of 1151 feet per second and an aspect ratio of 3.6},
+  institution      = {NASA Lewis Research Center Cleveland, OH, United States},
-institution = {NASA Lewis Research Center Cleveland, OH, United States},
+  title            = {Effect of damper on overall and blade-element performance of a compressor rotor having a tip speed of 1151 feet per second and an aspect ratio of 3.6},
-note        = {NASA-TM X-3041, url~: \url{https://ntrs.nasa.gov/citations/19740018135}, 1974}}
+  year             = {1974},
+  number           = {NASA-TM X-3041},
+  url              = {https://ntrs.nasa.gov/citations/19740018135},
+}
 </code>
   * Pictures : <grid>
@@ Ligne 34: / Ligne 37: @@
 </grid>
-===== Useful documents  =====
+<callout type="info" icon="true" title="Useful documents">
+  * [[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor01|downloadable models]] (Git project)
+  * {{ :public:modeles:rotor_1:rotor1.pdf | NASA technical report}} (.pdf)
+  * {{ :public:modeles:rotor_1:rotor1_original.csv | geometrical parameters file}} (.csv), usable as input of OpenMCAD[(cite:Kojtych_2022_gene_aubes>Kojtych S., Batailly A. «OpenMCAD, an open blade generator: from Multiple-Circular-Arc profiles to Computer-Aided Design model» 2022. {{ https://hal.science/hal-03923093|code en libre accès}})] to generate reference blade models.
+</callout>
+===== Reference blade =====
+The **reference blade** is defined with multiple-circular arc profiles[(cite:Crouse_1969_computer)] given in the original NASA report[(cite:hager1974design)]. Corresponding models are computed with the open-source code OpenMCAD[(cite:Kojtych_2022_gene_aubes)].
-  * PDF of the NASA report : {{ :public:modeles:rotor_1:rotor1.pdf |}}
-  * CSV file of the blade geometry : {{ :public:modeles:rotor_1:rotor1_original.csv |}}
-===== Geometry =====
+==== Geometry ====
-The geometry of rotor 1 is described in the [[https://ntrs.nasa.gov/citations/19740018135|original NASA report]]  by the following tables. The length are in inches and the angles in degrees.
+The geometry of rotor 1 is described in the [[https://ntrs.nasa.gov/citations/19740018135|original NASA report]] by the following table. The lenghts are in inches and the angles in degrees.
 {{ :public:modeles:rotor_1:gene_aubes_nasa_geom_rotor1.png?400 |}}
-===== Aerodynamic design  =====
+==== Aerodynamic design  ====
-^                      ^  unit  ^ values  ^
+^                      ^  unit  ^ value  ^
 ^ pressure ratio  |  [-]     | 1.53     |
 ^ mass flow       |  [kg/s]  | 33.5     |
@@ Ligne 54: / Ligne 63: @@
 ^ rotative speed  |  [rad/s]  | 1381.25  |
-===== Material properties  =====
+==== Material properties  ====
-Rotor 1 is made of a 200-grade maraging steel
+The material of rotor 1 is not defined in the original NASA report. A 200-grade maraging steel is considered:
-^                         ^  unité    ^ valeurs             ^
+^                         ^  unit    ^ value             ^
 ^ alloy                |  [-]      | 18-Ni-200-maraging  |
 ^ Young's modulus          |  [GPa]    | 180                 |
@@ Ligne 65: / Ligne 74: @@
 ^ yield stress        |  [GPa]    | 1.38                |
-First three natural frequencies (with clamped root) for the mesh:
+==== CAD model ====
-     - <fc #c0c0c0>(1F)</fc> : 940.8 rad/s  / 149.7 Hz
-     - <fc #c0c0c0>(1T)</fc> : 3479.2 rad/s / 553.7 Hz
+The CAD model is computed with the open source code OpenMCAD[(cite:Kojtych_2022_gene_aubes)].
-     - <fc #c0c0c0>(2F)</fc> : 5530.2 rad/s / 880.2 Hz
+<grid>
+<col md="2">
+</col>
+<col md="4">
+{{ :public:modeles:rotor_01:1_intra.png?200 |}}
+ <caption>pressure side</caption>
+</col>
+<col md="4">
+{{ :public:modeles:rotor_01:1_extra.png?200 |}}
+<caption>suction side</caption>
+</col>
+<col md="2">
+</col>
+</grid>
+==== Natural frequencies ====
+First three natural frequencies (with clamped root) for the mesh computed with OpenMCAD[(cite:Kojtych_2022_gene_aubes)]:
+^ Mode  ^ Type  ^ Natural angular frequency (rad/sec)  ^ Natural frequency (Hz)  ^
+| 1     | 1B    | 1018.5                       | 162.1                  |
+| 2     | 1T    | 3542.5                      | 563.8                  |
+| 3     | 2B    | 6094.7                      | 970.0                  |
+===== Initial blade =====
+The **initial blade** is defined with in-house LAVA parameters[(cite:Kojtych_2022_Methodology)] computed from the reference blade CAD model. The initial blade is usually used as starting point for an optimization process. Its geometry is similar to the one of the reference blade.
+==== Natural frequencies ====
+First three natural frequencies (with clamped root)
+  * from the whole mesh:
+^ Mode  ^ Type  ^ Natural angular frequency (rad/sec)  ^ Natural frequency (Hz)  ^
+| 1     | 1B    | 1019.1                       | 162.2                  |
+| 2     | 1T    | 3539.3                       | 563.3                  |
+| 3     | 2B    | 6074.0                       | 966.7                  |
+  * from the reduced order model:
-===== CAD =====
+^ Mode  ^ Type  ^ Natural angular frequency (rad/sec)  ^ Natural frequency (Hz)  ^
+| 1     | 1B    | 1019.1                      | 162.2                  |
+| 2     | 1T    | 3540.8                      | 563.5                  |
+| 3     | 2B    | 6075.8                      | 967.0                  |
-{{ :public:modeles:rotor_1:gene_aubes_nasa_rotor1_cao.png?300 |}}
 </pane>
 <pane id="tab-fr">
@@ Ligne 82: / Ligne 143: @@
 <modal id="modal_fr" title="Libre accès">
-**[[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/rotor01|lien vers le projet Git]]**
+**[[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor01|lien vers le projet Git]]**
 </modal>
 ===== À propos =====
@@ Ligne 89: / Ligne 152: @@
 Le rotor 1 fait partie d'un programme de recherche visant à étudier l’allongement des aubes, car l'utilisation d’un fort allongement peut conduire à une diminution de la longueur axiale des compresseurs et donc à une réduction de leur taille et poids. Pour étudier les effets de cet allongement sur les rendements des compresseurs, deux rotors transsoniques (rotor 1 et 2) ont été conçus et testés. La variation d’allongement entre ces deux rotors a été effectuée grâce à une modification de la corde aérodynamique et la solidité a été maintenue identique en faisant varier le nombre d'aubes.
-  * Rapport technique original [(cite:hager1974design>Hager. «Effect of damper on overall and blade-element performance of a compressor rotor having a tip speed of 1151 feet per second and an aspect ratio of 3.6 » 1974. NASA-TM X-3041. {{ https://ntrs.nasa.gov/citations/19740018135|pdf}})]: <code>@TechReport{hager1974design,
+  * Rapport technique original [(cite:hager1974design>)]: <code>@TechReport{hager1974design,
   author           = {Hager, Roy D. and Lewis, George W.},
   institution      = {NASA Lewis Research Center Cleveland, OH, United States},
@@ Ligne 110: / Ligne 173: @@
 <callout type="info" icon="true" title="Documents utiles">
-  * [[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/rotor01|modèles téléchargeables]] (lien vers projet Git)
+  * [[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor01|modèles téléchargeables]] (lien vers projet Git)
   * {{ :public:modeles:rotor_1:rotor1.pdf | rapport technique original}} de la NASA (.pdf)
   * {{ :public:modeles:rotor_1:rotor1_original.csv | fichier de paramètres géométriques}} (.csv), utilisable en entrée de OpenMCAD[(cite:Kojtych_2022_gene_aubes>Kojtych S., Batailly A. «OpenMCAD, an open blade generator: from Multiple-Circular-Arc profiles to Computer-Aided Design model» 2022. {{ https://hal.science/hal-03923093|code en libre accès}})] pour générer l'aube de référence
@@ Ligne 128: / Ligne 191: @@
 ==== Caractéristiques aérodynamiques  ====
-^                      ^  unités   ^ valeurs                          ^
+^                      ^  unité    ^ valeurs  ^
 ^ taux de compression  |  [-]      | 1,53     |
 ^ débit massique       |  [kg/s]   | 33,5     |
@@ Ligne 155: / Ligne 218: @@
 </col>
 <col md="4">
-{{ :public:modeles:rotor_1:1_intra.png?200 |}}
+{{ :public:modeles:rotor_01:1_intra.png?200 |}}
  <caption>intrados</caption>
 </col>
 <col md="4">
-{{ :public:modeles:rotor_1:1_extra.png?200 |}}
+{{ :public:modeles:rotor_01:1_extra.png?200 |}}
 <caption>extrados</caption>
 </col>
@@ Ligne 199: / Ligne 262: @@
 | 3     | 2F    | 6075,8                      | 967,0                  |
-</tabs>
 </pane>
+</tabs>