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- W2185829541 abstract "The goal of this project is to report on some computationalinvestigationsabout the return flow passages. The return flow channel provides theconnection and carries the flow between two stages of a multistagecentrifugal compressor. Of course, deswirl vanes are indispensable betweenthe inlet and outlet section, because usually the inlet flow angle, whichcomes from the impeller, is 70° -75° measured from radius andthe downstream flow angle should be axial, for the next stage. Generally, theshape of this unconventional blade is unique; it is not possible to chooseit from any catalogues.During the design procedures, a couple of new blade design techniques havebeen developed; among them one is based on a zero circulation over thecontrol surface, between two blades with the meaning of CBL (constant bladeloading) [14]. The purpose of this investigation is to construct a 3Dbladefor the return passage. In addition, a system of programsfor UNIX was developed to help us to communicate between the differentsoftware. The nextstep is to use the inviscid inverse design program to make the most relevantblade; provided by the CBL design, as perfect as possible and introducenegative and positive lean to improve the design specifications. Finally, weshould analyse the configuration with a 3D Navier-Stokes solver to have someconclusions about the new blade geometry.Of course, in the design process, the loss coefficient and pressure recoveryfactor are the two main parameters, which are always taken intoconsideration to check the correctness of the design." @default.
- W2185829541 created "2016-06-24" @default.
- W2185829541 creator A5075312958 @default.
- W2185829541 date "2003-04-09" @default.
- W2185829541 modified "2023-09-26" @default.
- W2185829541 title "COMPUTATIONAL INVESTIGATION ON DESWIRL VANES FOR MULTISTAGE CENTRIFUGAL COMPRESSORS" @default.
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