Abstract
The blade-to-blade variation of relative stagnation pressure losses in the tip region inside the rotor of a single-stage, axial-flow compressor is presented and interpreted in this paper. The losses are measured at two flow coefficients (one at the design point and the other at the near peak pressure rise point) to discern the effect of blade loading on the end-wall losses. The tip clearance losses are foundto increase with an increase in the pressure rise coefficient. The losses away from the tip region and near the hub regions are measured downstream. The losses are integrated and interpreted in this paper.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 22-31 |
| Number of pages | 10 |
| Journal | Journal of Engineering for Gas Turbines and Power |
| Volume | 108 |
| Issue number | 1 |
| DOIs | |
| State | Published - Jan 1986 |
All Science Journal Classification (ASJC) codes
- Nuclear Energy and Engineering
- Fuel Technology
- Aerospace Engineering
- Energy Engineering and Power Technology
- Mechanical Engineering