====== Rotor 36 ====== * [[#tab-fr|Français]] * [[#tab-en|English]] Downloadable files **[[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor36|Git project]]** ===== About ===== Rotor 36 is part of a research program to study a advanced-core compressor design with a high compression ratio (20:1). It is therefore the second 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:reid1982design>Reid L., Moore R. D. «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 » 1982. {{ https://ntrs.nasa.gov/citations/19820011348|pdf}})]: @TechReport{reid1982design, author = {Reid, L. and Moore, R. D.}, date = {1982}, 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 1.63 and 1.78, respectively, and with design pressure ratio of 1.82}, number = {NASA-TP-1974}, url = {https://ntrs.nasa.gov/citations/19820011348}, } * Pictures : {{ :public:modeles:rotor_36:gene_aubes_nasa_image_rotor36a.png?400 |}} Fig. 1 https://catalog.archives.gov/id/17467913 {{ :public:modeles:rotor_36:gene_aubes_nasa_image_rotor36b.png?400 |}} Fig. 2 https://catalog.archives.gov/id/17467884 * @Misc{huebler1977records, author = {Huebler, D.}, title = {Rotor 36 assembly and stator 36 casing half. {R}ecords of the {N}ational {A}eronautics and {S}pace {A}dministration, 1903 - 2006. {P}hotographs relating to agency activities, facilities and personnel, 1973 - 2013}, note = {\href{https://catalog.archives.gov/id/17467913}{https://catalog.archives.gov/id/17467913}, 1977 }, % for Fig. 1} note = {\href{https://catalog.archives.gov/id/17467884}{https://catalog.archives.gov/id/17467884}, 1977 }, % for Fig. 2} * [[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor36|downloadable models]] (Git project) * {{ :public:modeles:rotor_36:rotor36.pdf | NASA technical report}} (.pdf) * {{ :public:modeles:rotor_36:rotor36_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|open source code}})] to generate reference blade models. ===== Reference blade ===== The **reference blade** is defined with multiple-circular arc profiles[(cite:Crouse_1969_computer)] given in the original NASA report[(cite:reid1982design)]. Corresponding models are computed with the open-source code OpenMCAD[(cite:Kojtych_2022_gene_aubes)]. ==== Geometry ==== The geometry of rotor 36 is described in the [[https://ntrs.nasa.gov/citations/19820011348|original NASA report]] by the following tables. The length are in centimeters and the angles in degrees. {{ :public:modeles:rotor_36:gene_aubes_nasa_geom_rotor36.png?400 |}} ==== Aerodynamic design ==== ^ ^ unit ^ value ^ ^ pressure ratio | [-] | 1.82 | ^ mass flow | [kg/s] | 20.2 | ^ tip speed | [m/s] | 455 | ^ tip solidity | [-] | 1.3 | ^ aspect ratio | [-] | 1.63 | ^ number of blades | [-] | 48 | ^ nominal rotation speed $\omega_n$ | [rad/s] | 1800 | ==== Material properties ==== Rotor 36 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. The following properties are considered: ^ ^ unit ^ value ^ ^ alloy | [-] | 18-Ni-200-maraging | ^ Young's modulus | [GPa] | 180 | ^ density | [kg/m3] | 8000 | ^ Poisson's ratio | [-] | 0.3 | ^ yield stress | [GPa] | 1.38 | ==== CAD model ==== The CAD model is computed with the open source code OpenMCAD[(cite:Kojtych_2022_gene_aubes)]. {{ :public:modeles:rotor_36:36_intra.png?200 |}} pressure side {{ :public:modeles:rotor_36:36_extra.png?200 |}} suction side ==== 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 | 3525.61 | 561.12 | | 2 | 1T | 12882.23 | 2050.27 | | 3 | 2B | 14256.42 | 2268.98 | ====Campbell diagram==== Evolution of the natural frequencies of the first 3 vibration modes, as a function of rotation speed, for the mesh computed with OpenMCAD[(cite:Kojtych_2022_gene_aubes)]: {{ :public:modeles:rotor_36:campbell_eng_36_ref.png?500 }} Campbell diagram computed with a linear centrifugal preload, with clamped root (nominal rotation speed ωₙ = 1 800 rad/s) * {{ :public:modeles:rotor_36:campbell_eng_36_ref.pdf |graph (.pdf)}} * {{ :public:modeles:rotor_36:campbell_36_ref.csv |Campbell data (.csv)}} ===== 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 | 3538.38 | 563.15 | | 2 | 1T | 12965.60 | 2063.54 | | 3 | 2B | 14395.72 | 2291.15 | * from the reduced order model: ^ Mode ^ Type ^ Natural angular frequency (rad/sec) ^ Natural frequency (Hz) ^ | 1 | 1B | 3538.56 | 563.18 | | 2 | 1T | 12969.75 | 2064.20 | | 3 | 2B | 14407,60 | 2293.04 | ====Campbell diagram==== Comparison of the evolution of the natural frequencies of the first 3 vibration modes, as a function of rotation speed for the initial and the reference blade: {{ :public:modeles:rotor_36:campbell_eng_36_ini.png?500 }} Campbell diagram computed with a linear centrifugal preload, with clamped root (nominal speed ωₙ = 1 800 rad/s), initial blade (orange), reference blade (gray) * {{ :public:modeles:rotor_36:campbell_eng_36_ini.pdf |graph (.pdf)}} * {{ :public:modeles:rotor_36:campbell_36_ini.csv |Campbell data (.csv)}} Fichiers téléchargeables **[[ https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor36|lien vers le projet Git]]** ===== À propos ===== Le rotor 36 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 deuxième 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:reid1982design>)]: @TechReport{reid1982design, author = {Reid, L. and Moore, R. D.}, date = {1982}, 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 1.63 and 1.78, respectively, and with design pressure ratio of 1.82}, number = {NASA-TP-1974}, url = {https://ntrs.nasa.gov/citations/19820011348}, } * Photographies : {{ :public:modeles:rotor_36:gene_aubes_nasa_image_rotor36a.png?400 |}} Fig. 1 https://catalog.archives.gov/id/17467913 {{ :public:modeles:rotor_36:gene_aubes_nasa_image_rotor36b.png?400 |}} Fig. 2 https://catalog.archives.gov/id/17467884 * @Misc{huebler1977records, author = {Huebler, D.}, title = {Rotor 36 assembly and stator 36 casing half. {R}ecords of the {N}ational {A}eronautics and {S}pace {A}dministration, 1903 - 2006. {P}hotographs relating to agency activities, facilities and personnel, 1973 - 2013}, note = {\href{https://catalog.archives.gov/id/17467913}{https://catalog.archives.gov/id/17467913}, 1977 }, % pour Fig. 1 note = {\href{https://catalog.archives.gov/id/17467884}{https://catalog.archives.gov/id/17467884}, 1977 }, % pour Fig. 2} * [[https://gitlab.lava.polymtl.ca/depots_publics/modeles/catalogue_aubes/-/tree/master/rotor36|modèles téléchargeables]] (lien vers projet Git) * {{ :public:modeles:rotor_36:rotor36.pdf | rapport technique original}} de la NASA (.pdf) * {{ :public:modeles:rotor_36:rotor36_original.csv | fichier de paramètres géométriques}} (.csv), utilisable en entrée de OpenMCAD[(cite:Kojtych_2022_gene_aubes>)] pour générer l'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:reid1982design)]. Les modèles associés sont obtenus avec le code en libre accès OpenMCAD[(cite:Kojtych_2022_gene_aubes)]. ==== Géométrie ==== La géométrie du rotor 36 est décrite dans le [[https://ntrs.nasa.gov/citations/19820011348|rapport d'origine de la NASA]] par les tableaux suivants. Les grandeurs sont en centimètres et en degrés. {{ :public:modeles:rotor_36:gene_aubes_nasa_geom_rotor36.png?400 |}} ==== Caractéristiques aérodynamiques ==== ^ ^ unités ^ valeurs ^ ^ taux de compression | [-] | 1,82 | ^ débit massique | [kg/s] | 20,2 | ^ vitesse en tête | [m/s] | 455 | ^ solidité en tête | [-] | 1,3 | ^ allongement | [-] | 1,63 | ^ nombre d'aubes | [-] | 48 | ^ vitesse de rotation $\omega_n$ | [rad/s] | 1800 | ==== Propriétés matériau ==== Le matériau du rotor 36 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. Les propriétés considérées sont : ^ ^ unité ^ valeurs ^ ^ alliage | [-] | 18-Ni-200-maraging | ^ module d'Young | [GPa] | 180 | ^ masse volumique | [kg/m3] | 8000 | ^ coefficient de Poisson | [-] | 0,3 | ^ limite élastique | [GPa] | 1,38 | ==== Modèle CAO ==== Le modèle CAO est obtenu avec OpenMCAD[(cite:Kojtych_2022_gene_aubes)]. {{ :public:modeles:rotor_36:36_intra.png?200 |}} intrados {{ :public:modeles:rotor_36:36_extra.png?200 |}} extrados ==== Fréquences propres ==== Fréquences des trois premiers modes (noeuds du pied d'aube encastrés) pour le maillage obtenu avec OpenMCAD[(cite:Kojtych_2022_gene_aubes)] : ^ Mode ^ Type ^ Pulsation propre (rad/sec) ^ Fréquence propre (Hz) ^ | 1 | 1F | 3525,61 | 561,12 | | 2 | 1T | 12882,23 | 2050,27 | | 3 | 2F | 14256,42 | 2268,98 | ====Diagramme de Campbell==== Évolution des fréquences propres des 3 premiers modes, en fonction de la vitesse de rotation, pour le maillage obtenu avec OpenMCAD[(cite:Kojtych_2022_gene_aubes)]: {{ :public:modeles:rotor_36:campbell_36_ref.png?500 }} diagramme de Campbell calculé avec une précharge centrifuge linéaire, noeuds du pied d'aube encastrés (vitesse nominale ωₙ = 1 800 rad/s) * {{ :public:modeles:rotor_36:campbell_36_ref.pdf |graphique (.pdf)}} * {{ :public:modeles:rotor_36:campbell_36_ref.csv |données du Campbell (.csv)}} ===== Aube initiale ===== L'**aube initiale** est définie par des paramètres spécifiques au LAVA[(cite:Kojtych_2022_Methodology>Kojtych S. //et al//. «Methodology for the Redesign of Compressor Blades Undergoing Nonlinear Structural Interactions: Application to Blade-Tip/Casing Contacts » 2022. Journal of Engineering for Gas Turbines and Power, Vol. 145, No. 5. {{ https://hal.archives-ouvertes.fr/hal-03795257|pdf}})] obtenus à partir du modèle CAO de l'aube de référence. L'aube initiale est classiquement utilisée comme point de départ dans le cadre de procédures d'optimisation; sa géométrie est similaire à celle de l'aube de référence. ==== Fréquences propres ==== Fréquences des trois premiers modes (noeuds du pied d'aube encastrés), * pour le maillage complet : ^ Mode ^ Type ^ Pulsation propre (rad/sec) ^ Fréquence propre (Hz) ^ | 1 | 1F | 3538,38 | 563,15 | | 2 | 1T | 12965,60 | 2063,54 | | 3 | 2F | 14395,72 | 2291,15 | * pour le modèle réduit : ^ Mode ^ Type ^ Pulsation propre (rad/sec) ^ Fréquence propre (Hz) ^ | 1 | 1F | 3538,56 | 563,18 | | 2 | 1T | 12969,75 | 2064,20 | | 3 | 2F | 14407,60 | 2293,04 | ====Diagramme de Campbell==== Comparaison de l'évolution des fréquences propres des 3 premiers modes, en fonction de la vitesse de rotation, pour l'aube initiale et de référence: {{ :public:modeles:rotor_36:campbell_36_ini.png?500 }} diagramme de Campbell calculé avec une précharge centrifuge linéaire, noeuds du pied d'aube encastrés (vitesse nominale ωₙ = 1 800 rad/s), aube initiale (orange), aube de référence (grise) * {{ :public:modeles:rotor_36:campbell_36_ini.pdf |graphique (.pdf)}} * {{ :public:modeles:rotor_36:campbell_36_ini.csv |données du Campbell (.csv)}}