Différences

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

--- ressources:logiciels:gene_aubes_nasa:geneaubeslisteaubes:rotor_4:accueil [2022/05/16 17:10] – antoinelemery
+++ ressources:logiciels:gene_aubes_nasa:geneaubeslisteaubes:rotor_4:accueil [2022/05/17 14:16] – antoinelemery
@@ Ligne 8: / Ligne 8: @@
 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.
-Then, another series of tests is being conducted with the blade tip solidities of 1.3 (rotor 14), 1.5, and 1.7 (rotor 12) 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 would be the same.
+Then, another series of tests is being conducted with the blade tip solidities of 1.3 (rotor 14), 1.5 (rotor 8), and 1.7 (rotor 12) 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 would be the same.