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Test Facility
In the past years, a high-speed, three-stage axial compressor with IGV was built up at the Institute of Jet Propulsion and Turbomachinery at RWTH Aachen University (Hoynacki, 1999). Retaining the front stage, the rig is based on a compressor built up by Schulte (1994). All blade rows of the three-stage axial compressor were inversely designed by a two-dimensional method on five rotational symmetric stream surfaces (Grein and Schmidt, 1994). In Fig. 1, the cross-sectional view of the compressor is shown. The IGV and the stator blades are mounted in inner shroud rings with negligible small radial clearances both at the hub and the casing. The rotor tip clearances are less than 0.3 mm during operation yielding a relative clearance of 0.35% for the first rotor row, and 0.49%, and 0.64%, for the subsequent rotor rows. Fundamental parameters of
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Figure 1. Cross section of the three-stage axial compressor
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Table 1. Characteristic parameters of the three-stage axial compressor
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the compressor are summarized in Table 1. The compressor has a nominal total pressure ratio of 2.03, and a mass fbw of 13.4kg/s at a rotational speed of 17000 RPM. With a circumferential tip speed of 345 m/s, the maximum relative Mach number is 0.89 at the tip of the first rotor. Although the compressor was up to now investigated in much detail for five different operating points on three different speedlines, this paper will focus on two operating points on the 100% speedline. As can be seen, operating point OP1 is close to design conditions. OP3 is the last stable operating point close to surge.
