Abstract
On the basis of an aero-engine performance emulation model, a turbine cooling algorithm was employed to calculate the cooling flow and the resulting decrease in turbine efficiency. The influence of turbine cooling technology on aero-engine performance was analyzed with regards to different cooling means and different levels of cooling technology. The results show that among all cooling means considered, the convection film cooling offers the best general performance with favorable specific thrust, thermal efficiency and specific fuel consumption. And as for the convection film cooling, when the required cooling flow and incidental turbine efficiency loss are reduced by 20%, the specific fuel consumption drops by 0.9% and the specific thrust boosts by 3%.
| Original language | English |
|---|---|
| Pages (from-to) | 793-798 |
| Number of pages | 6 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 35 |
| Issue number | 6 |
| DOIs | |
| State | Published - Jun 2014 |
Keywords
- Aero-engine
- Cooling means
- Levels of cooling technology
- Turbine cooling algorithm
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