Influence of aero-engine casing structure on tip clearance under maneuvering load
To solve the problem of uneven tip clearance variation in aero-engine compressor under maneuvering load,the influence of structural factors on tip radial clearance under maneuvering load was studied.Taking a small bypass ratio turbofan aero engine as an object,a computational model was established.Through finite element numerical simulation,the influence law of aero-engine compressor casing,and intermediate casing on the tip clearance of a high-pressure compressor under maneuvering load was obtained.The results show that the double-layer casing structure can increase the longitudinal stiffness of the compressor,reduce the elliptical deformation and eccentricity of the compressor under normal overload and gyroscopic moment,thus make the tip clearance change more uniform.Increasing the rigidity of the intermediate casing can reduce the asymmetric deformation of the inner compressor casing under normal overload,to improve the working characteristics of the compressor tip clearance.The influence of aero-engine casing structure on compressor tip clearance under maneuvering load is significant.By improving the casing structure,0.41%-0.64% of working clearance reduction benefits can be obtained.
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