Previous simulations of a turbojet disc cavity with full Navier-Stokes CFD and simplified geometry and boundary conditions have been improved to reduce the level of approximation. A new grid was built using a multi-block approach. The case was computed with a commercial Navier-Stokes solver, STAR-CD (CD-Adapco Group), on the latest parallel computing system available at the CSIR. The results are compared to those computed with an in-house developed 1-D flow solver coupled with a 3D conduction code, and thermal paint validation data. The aim of the paper is to review the approach to disc cavity analysis followed by the CSIR
Reference:
Snedden, GC, Roos, TH and Naidoo, K. 2003. Detailed disc assembly temperature prediction: comparison between CFD and simplified engineering methods. 17th International Symposium for Air-breathing Engines, Germany, Munich, 5-9 September, 2005, pp 11
Snedden, G. C., Roos, T., & Naidoo, K. (2003). Detailed disc assembly temperature prediction: comparison between CFD and simplified engineering methods. http://hdl.handle.net/10204/1063
Snedden, Glen C, TH Roos, and Kavendra Naidoo. "Detailed disc assembly temperature prediction: comparison between CFD and simplified engineering methods." (2003): http://hdl.handle.net/10204/1063
Snedden GC, Roos T, Naidoo K, Detailed disc assembly temperature prediction: comparison between CFD and simplified engineering methods; 2003. http://hdl.handle.net/10204/1063 .
ResearchSpace
