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Rotor 35

Downloadable files

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 report from NASA.

  • Original technical report [1]: 
    @TechReport{reid1978design,
author      = {Reid, L. and Moore, R. D.},
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},
institution = {NASA Lewis Research Center Cleveland, OH, United States},
note        = {NASA-TP-1338, url~: \url{https://ntrs.nasa.gov/citations/19790001889}, 1978}}
  • Picture :

Fig1. https://catalog.archives.gov/id/17466807 
@Misc{brown1977records,
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},
note     = {\href{https://catalog.archives.gov/id/17466807}{https://catalog.archives.gov/id/17466807}, 1975 }, % for Fig. 1}

Useful documents

Geometry

The geometry of rotor 35 is described in the original NASA report by the following tables. The length are in centimeters and the angles in degrees.

Aerodynamic design

unit values
pressure ratio [-] 1.82
mass flow [kg/s] 20.2
tip speed [m/s] 455
tip solidity [-] 1.3
aspect ratio [-] 1.19
number of blades [-] 36
rotative speed [rad/s] 1800

Material properties

Rotor 35 is made of a 200-grade maraging steel

unité valeurs
alloy [-] 18-Ni-200-maraging
Young's modulus [GPa] 180
density [kg/m3] 8000
Poisson's ratio [-] 0.3
yield stress [GPa] 1.38

First three natural frequencies (with clamped root) for the mesh:

  1. (1B): 5009.3 rad/s / 797.2 Hz
  2. (1T): 14852.9 rad/s / 2363.9 Hz
  3. (2B): 18888.7 rad/s / 3006.2 Hz

CAD

Fichiers téléchargeables

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 rapport de la NASA.

  • Rapport technique original [1]: 
    @TechReport{reid1978design,
author      = {Reid, L. and Moore, R. D.},
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},
institution = {NASA Lewis Research Center Cleveland, OH, United States},
note        = {NASA-TP-1338, url~: \url{https://ntrs.nasa.gov/citations/19790001889}, 1978}}
  • Photographie :

Fig1. https://catalog.archives.gov/id/17466807 
@Misc{brown1977records,
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},
note     = {\href{https://catalog.archives.gov/id/17466807}{https://catalog.archives.gov/id/17466807}, 1975 }, % for Fig. 1}

Documents utiles

Géométrie

La géométrie du rotor 35 est décrite dans le rapport d'origine de la NASA par les tableaux suivants. Les grandeurs sont en centimètres et en degrés.

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 [-] 1,19
nombre d'aubes [-] 36
vitesse de rotation [rad/s] 1800

Propriétés matériau

Le matériau du rotor 35 est un alliage à base de nickel : un acier maraging de grade 200

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

Fréquences des trois premiers modes (noeuds de la base encastrés) pour le maillage :

  1. (1B): 5009,3 rad/s / 797,2 Hz
  2. (1T): 14852,9 rad/s / 2363,9 Hz
  3. (2B): 18888,7 rad/s / 3006,2 Hz

CAO

1. a, b 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. pdf
  • public/modeles/rotor_35/accueil.1663337479.txt.gz
  • Dernière modification : 2023/04/05 08:59
  • (modification externe)