Radical clearance analysis on the high pressure compressor

Tip clearance has great influence on the working performance of aeroengines. The statistical data show that if tip clearance increased 1% of the blade length, the efficiency will decrease 1%,sfc will increase 1%, life cycle cost will increase 1.5%, So, research on the active clearance control is important for enlarging working envelop, increasing working reliability and reducing cost. However, to build a stable, accurate clearance analytical method is the previous condition for active clearance control. So for the high pressure compressor of an aeroengine, which is combined wit h an axial and radial compressor, on the comprehensive consideration of aerodynamic loading, centrifugal loading, temperature loading, the paper established the radical clearance computational model for high pressure compressor. Characteristics of flow field and distribution of deformation and stress of blade were got under the 3 typical working states. The computational results of flow field showed under the state of design point, the rotor of the 1st stage was working under transonic condition and the relative mach number of blade leading edge increased along the span, flow separation was observed in the diffuser of the radial compressor. In radical clearance analysis, the distribution regularity along the axial direction was achieved under the 3 typical working states. For axial compressor, the minimum value of radical clearance was under the state of the greatest rotating speed and the maximum value of radical clearance was under the state of the highest temperature. For radial compressor, the computational results showed that under the state of design point and the state of the greatest rotating speed, the blade tip would rub on the casing. The results were coincident with the aero� engines test results which testify the correction of the calculating method and also provide the research idea of building logical and effective analytical method of radical clearance for compressor.