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| public:modeles:rotor_35:accueil [2023/02/24 21:54] – ikrambeghdadi | public:modeles:rotor_35:accueil [2023/04/15 13:29] (Version actuelle) – [Material properties] ikrambeghdadi |
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| <btn type="warning" size="md" modal="modal_en">Downloadable files</btn> | <btn type="warning" size="md" modal="modal_en">Downloadable files</btn> |
| <modal id="modal_en" title="Open access"> | <modal id="modal_en" title="Open access"> |
| **[[} | **[[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor36|Git project]]** |
| https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor35|Git project]]** | |
| </modal> | </modal> |
| ===== Original model ===== | ===== Original model ===== |
| |
| Rotor 35 is part of a research program to study a advanced-core compressor design with a high compression ratio (20:1). It is therefore the first stage rotor of this eight stage transonic compressor. Of these eight stages, the first four have been designed and tested : rotors 35, 36, 37 and 38. For more information, here is a link to [[https://ntrs.nasa.gov/citations/19780025165|report from NASA]]. | Rotor 35 is part of a research program to study a advanced-core compressor design with a high compression ratio (20:1). It is therefore the first stage rotor of this eight stage transonic compressor. Of these eight stages, the first four have been designed and tested : rotors 35, 36, 37 and 38. For more information, here is a link to [[https://ntrs.nasa.gov/citations/19780025165|a report from NASA]]. |
| |
| * Original technical report [(cite:reid1978performance>Reid. «Performance of Single-Stage Axial-Flow Transonic Compressor With Rotor and Stator Aspect Ratios of 1.19 and 1.26, Respectively, and With Design Pressure Ratio of 1.82 » 1978. {{ https://ntrs.nasa.gov/citations/19790001889|pdf}})]: | * Original technical report [(cite:reid1978performance>Reid L., Moore R. D. «Performance of Single-Stage Axial-Flow Transonic Compressor With Rotor and Stator Aspect Ratios of 1.19 and 1.26, Respectively, and With Design Pressure Ratio of 1.82 » 1978. {{ https://ntrs.nasa.gov/citations/19790001889|pdf}})]: |
| <code>@TechReport{reid1978performance, | <code>@TechReport{reid1982design, |
| author = {Reid, L. and Moore, R. D.}, | author = {Reid, L. and Moore, R. D.}, |
| date = {1978}, | date = {1982}, |
| institution = {NASA Lewis Research Center Cleveland, OH, United States}, | institution = {NASA Lewis Research Center Cleveland, OH, United States}, |
| title = {Performance of Single-Stage Axial-Flow Transonic Compressor With Rotor and Stator Aspect Ratios of 1.19 and 1.26, Respectively, and With Design Pressure Ratio of 1.82}, | title = {Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.63 and 1.78, respectively, and with design pressure ratio of 1.82}, |
| number = {NASA-TP-1338}, | number = {NASA-TP-1974}, |
| url = {https://ntrs.nasa.gov/citations/19790001889}, | url = {https://ntrs.nasa.gov/citations/19820011348}, |
| } | } |
| </code> | </code> |
| * Picture : | * Picture : |
| |
| {{ :public:modeles:rotor_35:gene_aubes_nasa_image_rotor35.png?300 |}} | {{ :public:modeles:rotor_35:gene_aubes_nasa_image_rotor35.png?300 |}} |
| <caption>Fig1. https://catalog.archives.gov/id/17466807 </caption> | <caption>Fig. 1 https://catalog.archives.gov/id/17466807 </caption> |
| | * <code>@Misc{brown1977records, |
| <code>@Misc{brown1977records, | |
| author = {Brown, M.}, | author = {Brown, M.}, |
| title = {Rotor 35 - Rotor 35 - Stator 35 in casing. {R}ecords of the {N}ational {A}eronautics and {S}pace {A}dministration, 1903 - 2006. {P}hotographs relating to agency activities, facilities and personnel, 1977 - 2013}, | title = {Rotor 35 - Rotor 35 - Stator 35 in casing. {R}ecords of the {N}ational {A}eronautics and {S}pace {A}dministration, 1903 - 2006. {P}hotographs relating to agency activities, facilities and personnel, 1977 - 2013}, |
| note = {\href{https://catalog.archives.gov/id/17466807}{https://catalog.archives.gov/id/17466807}, 1975 }, % for Fig. 1} | url = {https://catalog.archives.gov/id/17466807}} |
| </code> | </code> |
| |
| <callout type="info" icon="true" title="Useful documents"> | <callout type="info" icon="true" title="Useful documents"> |
| * [[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor35|downloadable models]] (Git project) | * [[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor36|downloadable models]] (Git project) |
| * PDF of the NASA report : {{ :public:modeles:rotor_35:rotor35.pdf |}} | * PDF of the NASA report : {{ :public:modeles:rotor_35:rotor35.pdf |}} |
| * CSV file of the blade geometry : {{ :public:modeles:rotor_35:rotor35_original.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. | * CSV file of the blade geometry : {{ :public:modeles:rotor_35:rotor35_original.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|open source code}})] to generate reference blade models. |
| </callout> | </callout> |
| |
| ===== Material properties ===== | ===== Material properties ===== |
| |
| Rotor 35 is made of a 200-grade maraging steel[(cite:reid1978designandoverall>Reid. «Design and overall performance of four highly loaded, high-speed inlet stages for and advanced high-pressure-ratio core compressor» 1978. {{ https://ntrs.nasa.gov/citations/19780025165|pdf}})], but the exact material properties are not provided in the NASA report. | Rotor 35 is made of a 200-grade maraging steel[(cite:reid1978designandoverall>Reid //et all//. «Design and overall performance of four highly loaded, high-speed inlet stages for and advanced high-pressure-ratio core compressor» 1978. {{ https://ntrs.nasa.gov/citations/19780025165|pdf}})], but the exact material properties are not provided in the NASA report. The following properties are considered : |
| | |
| Considered properties: 18-Ni-200-maraging steel : | |
| |
| ^ ^ unité ^ valeurs ^ | ^ ^ unité ^ valeurs ^ |
| ===== Modèle original ===== | ===== Modèle original ===== |
| |
| Le rotor 35 appartient à un programme de recherche visant à étudier une conception de compresseur possédant un grand taux de compression (20:1). Il est donc le rotor du premier étage de ce compresseur transsonique de huit étages. Parmi ces huit étages, les quatre premiers ont été conçus et testés, ils correspondent aux rotors 35, 36, 37 et 38. Pour plus d'information, voici un lien vers [[https://ntrs.nasa.gov/citations/19780025165|rapport de la NASA]]. | Le rotor 35 appartient à un programme de recherche visant à étudier une conception de compresseur possédant un grand taux de compression (20:1). Il est donc le rotor du premier étage de ce compresseur transsonique de huit étages. Parmi ces huit étages, les quatre premiers ont été conçus et testés, ils correspondent aux rotors 35, 36, 37 et 38. Pour plus d'information, voici un lien vers [[https://ntrs.nasa.gov/citations/19780025165|un rapport de la NASA]]. |
| |
| * Rapport technique original [(cite:reid1978performance>Reid. «Performance of Single-Stage Axial-Flow Transonic Compressor With Rotor and Stator Aspect Ratios of 1.19 and 1.26, Respectively, and With Design Pressure Ratio of 1.82 » 1978. {{ https://ntrs.nasa.gov/citations/19790001889|pdf}})]: <code>@TechReport{reid1978performance, | * Rapport technique original [(cite:reid1978design>)]: <code>@TechReport{reid1982design, |
| author = {Reid, L. and Moore, R. D.}, | author = {Reid, L. and Moore, R. D.}, |
| date = {1978}, | date = {1982}, |
| institution = {NASA Lewis Research Center Cleveland, OH, United States}, | institution = {NASA Lewis Research Center Cleveland, OH, United States}, |
| title = {Performance of Single-Stage Axial-Flow Transonic Compressor With Rotor and Stator Aspect Ratios of 1.19 and 1.26, Respectively, and With Design Pressure Ratio of 1.82}, | title = {Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.63 and 1.78, respectively, and with design pressure ratio of 1.82}, |
| number = {NASA-TP-1338}, | number = {NASA-TP-1974}, |
| url = {https://ntrs.nasa.gov/citations/19790001889}, | url = {https://ntrs.nasa.gov/citations/19820011348}, |
| } | } |
| </code> | </code> |
| * Photographie : | * Photographie : |
| |
| {{ :public:modeles:rotor_35:gene_aubes_nasa_image_rotor35.png?300 |}} | {{ :public:modeles:rotor_35:gene_aubes_nasa_image_rotor35.png?300 |}} |
| <caption>Fig1. https://catalog.archives.gov/id/17466807 </caption> | <caption>Fig. 1 https://catalog.archives.gov/id/17466807 </caption> |
| | * <code>@Misc{brown1977records, |
| <code>@Misc{brown1977records, | |
| author = {Brown, M.}, | author = {Brown, M.}, |
| title = {Rotor 35 - Rotor 35 - Stator 35 in casing. {R}ecords of the {N}ational {A}eronautics and {S}pace {A}dministration, 1903 - 2006. {P}hotographs relating to agency activities, facilities and personnel, 1977 - 2013}, | title = {Rotor 35 - Rotor 35 - Stator 35 in casing. {R}ecords of the {N}ational {A}eronautics and {S}pace {A}dministration, 1903 - 2006. {P}hotographs relating to agency activities, facilities and personnel, 1977 - 2013}, |
| note = {\href{https://catalog.archives.gov/id/17466807}{https://catalog.archives.gov/id/17466807}, 1975 }, % for Fig. 1} | url = {https://catalog.archives.gov/id/17466807}} |
| </code> | </code> |
| |
| |
| <callout type="info" icon="true" title="Documents utiles"> | <callout type="info" icon="true" title="Documents utiles"> |
| * [[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor35|modèles téléchargeables]] (lien vers projet Git) | * [[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor36|modèles téléchargeables]] (lien vers projet Git) |
| * PDF du rapport de la NASA : {{ :public:modeles:rotor_35:rotor35.pdf |}} | * PDF du rapport de la NASA : {{ :public:modeles:rotor_35:rotor35.pdf |}} |
| * Fichier CSV de la géométrie : {{ :public:modeles:rotor_35:rotor35_original.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 | * Fichier CSV de la géométrie : {{ :public:modeles:rotor_35:rotor35_original.csv |}}, utilisable en entrée de OpenMCAD[(cite:Kojtych_2022_gene_aubes>)] pour générer l'aube de référence |
| </callout> | </callout> |
| |
| ===== Aube de référence ===== | ===== Aube de référence ===== |
| |
| L'**aube de référence** est définie par des profils de type arcs circulaires multiples[(cite:Crouse_1969_computer>Crouse //et al//. «A computer program for composing compressor blading from simulated circular-arc elements on conical surfaces » 1969. NASA-TN-D-5437. {{ https://ntrs.nasa.gov/citations/19690027504|pdf}})], donnés dans le rapport technique original de la NASA[(cite:reid1978performance)]. Les modèles associés sont obtenus avec le code en libre accès OpenMCAD[(cite:Kojtych_2022_gene_aubes)]. | L'**aube de référence** est définie par des profils de type arcs circulaires multiples[(cite:Crouse_1969_computer>Crouse //et al//. «A computer program for composing compressor blading from simulated circular-arc elements on conical surfaces » 1969. NASA-TN-D-5437. {{ https://ntrs.nasa.gov/citations/19690027504|pdf}})], donnés dans le rapport technique original de la NASA[(cite:reid1978design)]. Les modèles associés sont obtenus avec le code en libre accès OpenMCAD[(cite:Kojtych_2022_gene_aubes)]. |
| |
| ===== Géométrie ===== | ===== Géométrie ===== |
| ===== Propriétés matériau ===== | ===== Propriétés matériau ===== |
| |
| Le matériau du rotor 35 est un alliage à base de nickel : un acier maraging de grade 200[(cite:reid1978designandoverall>Reid. «Design and overall performance of four highly loaded, high-speed inlet stages for and advanced high-pressure-ratio core compressor» 1978. {{ https://ntrs.nasa.gov/citations/19780025165|pdf}})], mais ses caractéristiques ne sont pas fournies dans le raport de la NASA. | Le matériau du rotor 35 est un alliage à base de nickel : un acier maraging de grade 200[(cite:reid1978designandoverall>)], mais ses caractéristiques ne sont pas fournies dans le raport de la NASA. Les propriétés considérées sont : |
| | |
| Propriétés considérées : alliage 18-Ni-200-maraging | |
| |
| ^ ^ unité ^ valeurs ^ | ^ ^ unité ^ valeurs ^ |
| |
| ^ Mode ^ Type ^ Pulsation propre (rad/sec) ^ Fréquence propre (Hz) ^ | ^ Mode ^ Type ^ Pulsation propre (rad/sec) ^ Fréquence propre (Hz) ^ |
| | 1 | 1B | 5000,55 | 795,863 | | | 1 | 1F | 1018,5 | 162,1 | |
| | 2 | 1T | 14833,91 | 2360,89 | | | 2 | 1T | 3542,5 | 563,8 | |
| | 3 | 2B | 18699,83 | 2976,17 | | | 3 | 2F | 6094,7 | 970,0 | |
| |
| |
| |
| ^ Mode ^ Type ^ Pulsation propre (rad/sec) ^ Fréquence propre (Hz) ^ | ^ Mode ^ Type ^ Pulsation propre (rad/sec) ^ Fréquence propre (Hz) ^ |
| | 1 | 1B | 5037,31 | 801,712 | | | 1 | 1F | 1019,1 | 162,2 | |
| | 2 | 1T | 14910,06 | 2373,01 | | | 2 | 1T | 3539,3 | 563,3 | |
| | 3 | 2B | 18900,76 | 3008,15 | | | 3 | 2F | 6074,0 | 966,7 | |
| |
| * pour le modèle réduit : | * pour le modèle réduit : |
| |
| ^ Mode ^ Type ^ Pulsation propre (rad/sec) ^ Fréquence propre (Hz) ^ | ^ Mode ^ Type ^ Pulsation propre (rad/sec) ^ Fréquence propre (Hz) ^ |
| | 1 | 1B | 5037,84 | 801,797 | | | 1 | 1F | 1019,1 | 162,2 | |
| | 2 | 1T | 14917,41 | 2374,18 | | | 2 | 1T | 3540,8 | 563,5 | |
| | 3 | 2B | 18926,96 | 3012,32 | | | 3 | 2F | 6075,8 | 967,0 | |
| |
| |
| </tabs> | |
| </pane> | |
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| | </pane> |
| | </tabs> |
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