Investigation of Performance and Rotor Tip Flow Field in a Low Speed Research Compressor with Circumferential Groove Casing Treatment at Varying Tip Clearance

Abstract EN

Experimental investigations in a single-stage low speed axial research compressor are presented.

The influence of four different rotor tip clearances on the overall compressor performance and on the rotor tip flow field is investigated in configurations with and without circumferential groove casing treatments.

Piezo-resistive pressure transducers are used to capture the unsteady flow field in the rotor tip region.

The investigated casing groove is effectively working at the three largest investigated tip clearance sizes.

The largest achieved operating range increase by the groove is 6.9%.

The groove can delay the upstream movement of the flow interface between leakage flow and main flow and thus increase the stable operating range.

Rotating instabilities are shown to exist at large tip clearance sizes in throttled operating conditions.

Their amplitudes can be damped by the casing groove.

No modal activities could be detected in the current single-stage compressor build.