|October 23, 2001, 01:22||
[HELP]mixing plane convergence strategy??
Hi all users. I have some serious and urgent problem.
The model, i solve now, is below (1) supersonic turbin system consist of 8 converging-diverging nozzle, 80 blade. Over expanded flow in nozzle hits turbine blade.
(2) So, I modeled 1 nozzle and 1 blade with periodic BC's and mixing plane.
(3) BC's are 6.8 Mpa pressure inlet at nozzle inlet, 0.5 Mpa pressure outlet. Rotor speed is 50,000 rpm
(4) I started with 1,000 rpm, mixing plane relaxation factor 0.5, and update interval 1.
(5) But, Reversed flow were not disappeared at mixing plane and Residual showed oscilation after 4000 iteration (about). Before 4000 iter, the Residual shows good convergence.
Is there anyone who had solved turbine problem with fluent like this?, or who has any related articles? reply or mail me plz.
Any comment about solution strategy will help me..
|Thread||Thread Starter||Forum||Replies||Last Post|
|Convergence||Centurion2011||FLUENT||33||November 8, 2016 16:08|
|Problem with Gmsh||nishant_hull||Open Source Meshers: Gmsh, Netgen, CGNS, ...||23||August 5, 2015 02:09|
|Force can not converge||colopolo||CFX||13||October 4, 2011 22:03|
|boundaries with gmshToFoam||ouafa||Open Source Meshers: Gmsh, Netgen, CGNS, ...||7||May 21, 2010 12:43|
|Convergence of CFX field in FSI analysis||nasdak||CFX||2||June 29, 2009 01:17|