Abstract
As one of the most important factors influencing the combustor life -span, the temperature gradient of the effusion wall, as well as the cooling efficiency were investigated experimentally under the guidance of similarity theory. The effects of the temperature ratio of the main flow to the cooling air, the speed ratio of the cooling air to the main flow and the speed of the main flow were analyzed and discussed. IR thermograph was used to perform local measurements of the surface temperature field. The results reveal that these parameters which are investigated in this paper have strong influence on the temperature gradient and the cooling efficiency.
| Original language | English |
|---|---|
| Pages (from-to) | 647-650 |
| Number of pages | 4 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 23 |
| Issue number | 4 |
| State | Published - Apr 2008 |
Keywords
- Aerospace propulsion system
- Combustor
- Cooling
- Cooling efficiency
- Effusion wall
- Gas turbine engine
- Liner
- Temperature gradient
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