Abstract
Numerical simulation was conducted to investigate heat transfer in a rectangular channel with both 60-degree rib-roughened wall and film hole suctions with Reynolds number of 9 × 104 and suction ratio of 0.22. A finite volume method with unstructured meshes was used to solve the three dimensional compressible Navier-Stokes equations. The realizable k-ε model was used carefully and the enhanced wall function was utilized for near wall treatment. The numerical results agree well with the experimental data of the surface with both ribs and film holes. Based on this, investigation was focused on the heat transfer of three other surfaces. The numerical result shows that the flow of the passage is very complex. Heat transfer is enhanced because of the ribs. Maximum Heat transfer coefficient is found on the smooth right surface but not the surfaces with ribs.
Original language | English |
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Pages (from-to) | 995-1000 |
Number of pages | 6 |
Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
Volume | 21 |
Issue number | 6 |
State | Published - Dec 2006 |
Keywords
- Aerospace propulsion system
- Aircraft engines
- Film holes
- Heat transfer
- Internal cooling passage
- Numerical simulation
- Ribs