Abstract
In order to reduce the shock related losses of highly-loaded transonic turbines, a novel turbine blade profile is presented in this paper. The blade profile features that it establishes a convergent blade passage and has a negative curvature uncovered suction side. Numerical simulation shows that a reduction of 29.7% in the total pressure loss coEfficient can be obtained after such a blade profiled is applied to a traditional turbine cascade. The blade profile geometrical characteristics and properties of shocks, expansion and compression waves are analyzed, which helps to reveal the ow physics of the loss reduction. In addition to reducing the aerodynamic losses the blade profile can improve the uniformity of its exit ow, and the downstream blade rows would then suffer less unsteady effects from it.
| Original language | English |
|---|---|
| Pages (from-to) | 1884-1888 |
| Number of pages | 5 |
| Journal | Kung Cheng Je Wu Li Hsueh Pao/Journal of Engineering Thermophysics |
| Volume | 36 |
| Issue number | 9 |
| Publication status | Published - 1 Sep 2015 |
| Externally published | Yes |
Keywords
- Expansion wave
- Negative curvature
- Shock
- Transonic turbine