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Was you successful to validate the near peak efficiency case with your grid?? I was using the previous CGNS file. I didn't have any problem with defining periodic boundaries. but for my case the position of M=1 is incorrect. Could you please send me your grid to check my solution process? my email is : mm.abdollahzadeh@yahoo.com Best Mahdi |
nasa67
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Dear friend The incorrect position of m=1 is due to two reasons first of all the incorrect outlet static pressure ... secondly to coarse mesh Anyway I will send you my mesh file : https://rapidshare.com/files/344103514/nasa67.rar |
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In my previous case , I was just defining a guess value for static pressure at outlet and then by targetting massflow rate I was trying to solve the problem. for the inlet also i was usuing fixed total pressure and temperature. at the outlet also i am using radial equliburim. I am not using the experimental profile for velocity angle and pressure and temperature distribuation. I am also runnning my case in Fluent. the case is resulting to correct pressure ratio. could you please tell me that this boundary condition is correct? if I need to use experimental datas , I dont know how to get the profiles and input them :(. I am not familer enough with turbomachinary modelling. could you please tell me that if I extend the geomtry at inlet and outlet. the part that is adding to hub should be stainary or moving. many thanks for your help. Kind Regards. Mahdi |
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Dear abdollahzadeh Actually , you must extend the outlet.... I modeled a stage so i couldn't extend the space between rotor and stator .... but in your case you should extend , otherwise you will have convergence problem the need for extension of inlet if you didn't find any considerable eddy at inlet is not important in this case considering this fact that hub is attached to blades so they should be moving... but about shroud, if you consider the gap between blade tip and casing it is better you set the casing fixed otherwise you can set it moving too without major difference between results I didn't have the profile .... so there is some error ... anyway by try and error I found the best boundary condition for fan is inlet total pressure and outlet average static pressure.... then I increased outlet pressure from 0 to 40 kpa to find characteristic curve Near stall convergence is much more difficult if you simulate nasa67 for steady state condition. here is some part of my results : https://rapidshare.com/files/3209642269/NASA67.pdf |
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Thanks for your help. am i righit? you use the simple nonreflecting boundary condition which gives you the ability to define avarge pressure at outlet. and do the trail and error procedure by your own expect of using that targrting mass flow. and in this case you are changing the pressure between 0 to 40kpa. so did you used a reffrence pressure 1atm? and define 0 for total pressure at inlet? ( I know that my questions looks stupid). Best Mahdi |
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You are on the right track Mehdi Break a leg |
Hi Rafiee,
I am also trying to simulate the NASA 67 Stage, I was wondering whether you have a .cgns model of the downstream stator. I would great appreciate it! Thanks, Priyanka |
surface pressure of Nasa rotor 67
Hi dear all. i,m searching for surface static pressure of Nasa rotor 67 at mid span for validation of my code. Is there any experimental results or any other result for validating my code?
If you have it or you know any paper which has it, please tell me. thanks |
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I have the geometry for both. Get me your email id so that I could send you. Regards, Jwala. |
request of validation for nasa rotor 67
Hi everybody.
I had a problem for validating of my case. In fact, I simulate nasa rotor67 profile at mid-span in 2D. I find out that my simulation, grid and boundary condition is true but my result is different from experimental results. 1. Is it because of my 2D simulation? or I must calculate it in 3D for comparing to experimental results? 2. If you have any result of mid-span surface pressure ratio, please send me. 3. Also, If you have any other results of 2D calculation, or you know papers which could give these information, please send it to me. Note: I run my case for near peak efficiency condition. Thanks very much. |
Could someone please upload the analysis files again, I am not using them, but it might be of great help to go through.
Thanks |
hi
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eslam
You have contacted me but I forgot to send you required info. I have huge data base (almost all turbulence models, three Y+, three meshes) and meshes for rotor 37 |
geometry of rotor 67 and 37
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maj_eslam@yahoo.com thanks |
[QUOTE=Far;427039]eslam
You have contacted me but I forgot to send you required info. I have huge data base (almost all turbulence models, three Y+, three meshes) and meshes for rotor 37[/QUOTE dear far just please send me the geometry of rotor 67 and rotor 37 in igs file on my email id maj_eslam@yahoo.com thanks |
transonic rotor
dear far
just please send me the geometry of rotor 67 and rotor 37 in igs file on my email id bondamani123@gmail.com |
need guid
hi rafiee
i just started my project related to transonic blade parametrization and optimization of compressor stage i need co ordinates of rotor 67,what r the difficulties u faced during geometry creation ,mesh generation in turbo grid,please share with me thank you mail id : flyrajesh4@gmail.com |
Have you used this mesh?
When i import it in pointwise or ICEM and then into fluent it gives me an error. if you look at the leading/trailing edge of the mesh you can see weird overlapping regions. |
NASArotor37
Hi all,
I need geometry rotor 37 to complete my project as a student..can you share with me a softcopy of the geometry to my email black16_geng@yahoo.com.. TQ |
NASA rotor 37(67)
Hi all,
does anybody have the geometry data of rotor 37 and 67? I need rotor blades, stator blades, hub, shroud, inlet and outlet coordinates. Please, send me any information you have. My teacher gave me a task and didn't give any information. My email: marina4erk@gmail.com Regards, Marina. |
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