Steady and Unsteady Flow Field in a Multistage Low-Speed Axial Compressor: A Test Case

Abstract

This paper introduces a new test case for compressor aerodynamics. The dataset is provided for the Dresden four-stage Low-Speed Research Compressor (LSRC), which was put into operation in 1995. The compressor consists of four identical stages, which are preceded by an inlet guide vane. The data set will be provided for the reference blading of the compressor with cantilevered stator vanes. This blading was developed on the basis of the profiles of a middle stage of a high-pressure compressor of a jet engine. This paper makes available the blading geometry as well as a variety of flow field measurement results. This includes the compressor map, selected pressure distributions and other results of flow field measurements with conventional techniques (e.g. Pitot probes, 5-hole probes). Furthermore different aspects of blade row interactions were addressed in this compressor within recent years. The periodical unsteady flow field within a selected rotor blade row was investigated using Laser-Doppler-Anemometry. Further results on the unsteady profile pressures and profile boundary layers will be provided. Supplementary, numerical results will be compared to the experiments. Results are available for several stages of the compressor and different operating points. With this test case a unique database for the aerodynamics in a multistage axial compressor will be provided that can be used for the validation of numerical codes.

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

“…The cross section of the compressor is shown in Figure 1 and reference build parameters can be found in Table 1. Boos et al [18] and Künzelmann et al [19] presented detailed information about the compressor installation and measurement results for the reference build. For the investigation at hand the compressor has been installed in a singlestage configuration.…”

Recent German Research on Periodical Unsteady Flow in Turbomachinery

“…The results concerning the periodical unsteady flow conditions in the Dresden compressor, investigated in this research program, became part of a testcase provided recently (more details in ref. [46]). Further on in the present paper the link between the periodical unsteady flow and the heat transfer is discussed, which is an important issue for turbine blades and vanes.…”

Vortex development induced by part gap geometry and endwall configurations for variable stator vanes in a compressor cascade

“…For more details on the profile contour one can refer to Künzelmann et al. 18 In order to reflect the typical operating range of variable guide vanes, the former five-hole probe investigations were performed at two relevant Reynolds numbers (Re=3.4×105 and 5.8×105 ). To reduce time consumption, the actual PIV measurements were carried out at a middle Re=4.6×105 since the pressure measurements did not detect qualitative differences of the resulting secondary flow pattern between the investigated lower and higher inlet velocities.…”