Comparison of Coupling Analysis of Fluid-Structure Interaction with Engineering Empirical Formula on Typical Stages of a Compressor

摘要

In order to achieve comparison study of blades, numerical simulation and engineering empirical formula checking are conducted for typical stages of a compressor in a heavy-duty gas turbine by the method of fluid-structure interaction, which are specially calculated to obtain the flow characteristic, deformation and stress distribution of blades under the aerodynamic loads and centrifugal force. The results show that rotor of the 1st stage of the compressor is working under the supersonic condition and the shock of the rotor of the 2nd stage is obviously weaker than that of the 1st stage. The development of vortex system in separation region may lead to cyclic stress and make the blades fatigue failure. The aerodynamic load of typical stages blades is concentrated on the root region, while, the stator load of the 2nd stage is higher than that of the 1st stage. Rotor of the 1st stage is more dangerous to be failure than other blades and the location of the maximum equivalent stress is on the place of mid-lower section of pressure side and trailing edge of rotor hub in the strength check. The maximum rotary deformation of blade tip is about 3.1% of blade height. The computational results of the two methods are basically coincident , especially for the sections of the rotor hub to the middle region of the blade, but there is a little bit of computational error in the blade tip.