Abstract
The design of the inter-stage seal in an axial compressor is an important topic because the leakage flow across the stator well would lead to aerodynamic mixing losses with the main flow, which will consequently impact the efficiency of the compressor. In this region, the leakage flow is normally controlled by a labyrinth seal with upstream and downstream rotating cavities. In addition, the long rotating wall results in substantial temperature rise and swirl flow development. In particular, the swirl flow in the compressor stator well has a great influence on the leakage behavior of the labyrinth seal. Therefore, it is essential to understand the leakage characteristic, windage heating characteristic and swirl flow characteristic of the stator well.A test rig capable of running at rotational speed 8100 rpm and pressure ratio 1.3 was built according to the simplified model of the labyrinth seal in a compressor stator well (one stage). Labyrinth rings with different rotor tip radii were manufactured to investigate the effect of tip clearance. Leakage flow rate, windage heating and swirl ratios in the outlet cavity were measured at different rotating speeds and different labyrinth rings. As the working tip clearance was very important for the analysis of the leakage behavior, the set up tip clearance was measured with plug gauges, while the radial displacements of rotating disc and stator casing were measured separately with two laser distance sensors. Since the tip clearance was varying with rotating speed and airflow temperature, the data interpolation method was used to find the pure influences of rotation and tip clearance.Numerical simulations were performed to analyze the flow characteristic, variation of total temperature and development of swirl flow in the stator well. Besides, CFD results could provide more detailed insight into the flow mechanisms that are responsible for the influences of rotation and tip clearance.
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