Numerical Investigation On Effect Of Applying Nonaxisymmetric Endwall On Compressor Cascade Performance

Aviation Industry is a significant state-prospering strategy with a high sence ofmission, which contributes to elevation of comprehensive national strength,consolidation of national security, improvement of international status, enhencing civilliving standard, and the rise-up of Chinese nation. As an important component ofaeroengine, stability and high efficiency of compressor has become a reasonable studysubject for a wide range of researchers. Thus, the effect of applying nonsymmetricendwall on compressor cascade performance was investigated in this passage, in theperspective of aerodynamics.A method of nonsymmetric endwall production was for the first step introduced,followed by the establishment of an endwall controlling function based on controlpoints. After the determination of control points, amplitude and compensation phaseangle became the only two variables of the controlling function.2%,5%,8%spanamplitude and four compesation phase angles associated with four convexificationpositions, including pressure side position, near pressure side position, near flow pathcentre position and flow path centre position, were selected to produce12types ofnonsymmetirc endwalls in a way of the two variable’s combination. A steady numericalsimulation of the12cases under0attack angle and other4undesigned attack anglesincluding-5,-2,+2,+5, was carried out with commercial software ANSYS CFX,and65cases were accomplished together with the original compressor cascade.As the results show, an appropriate selection of amplitude and convexificationpositon assists in controlling secondary flow, as well as decreasing secondary flow loss,consequently elevating compressor cascade efficiency. Among the4convexificationpositions, pressure side position is optimal, of which the nonsymmetric endwallsreduces outlet total pressure loss up to4.33%under0attack angle, and cut down7.17%outlet total pressure loss at the utmost under undesigned attack angle, in comparison tothe original compressor cascade. Assuming a reasonable convexification position ischosen, non-symmetric endwalls of different amplitude lead to the shrink of thesecondary loss area on different extend, meanwhile causing the movement of loss areato mid-span region.