Compared with a straight blade, a unique compressor blade integratedforward-swept and positive-curved stacking line is studied experimentally. Aerodynamic parameters ofthe two cascades are measured by a five-hole prob...Compared with a straight blade, a unique compressor blade integratedforward-swept and positive-curved stacking line is studied experimentally. Aerodynamic parameters ofthe two cascades are measured by a five-hole probe at different positions and ink trace flowvisualization is conducted on blade surfaces. The result shows that the swept-curved cascade haslower endwall loss and higher midspan loss as compared with the straight cascade. However, lowerloss is accompanied with lower diffusion factor. Opposite 'C' shape static pressure distribution isestablished on the suction surface of the swept-curved blade, which is helpful for avoiding theaccumulation of low energy fluid in the endwall corner region. Anyhow the studies support theconclusion that the swept-curved blade conduces to not only the reduction of overall loss but alsothe improvement of stable operation in the endwall corner region.展开更多
Geometric parameters of the turbine blade are classified according to their destined functions, and the mathematical definition of those parameters in the section curve is introduced in detail. Some parts of the secti...Geometric parameters of the turbine blade are classified according to their destined functions, and the mathematical definition of those parameters in the section curve is introduced in detail. Some parts of the section curve shape can be adjusted freely, offering more flexibility to designers.展开更多
Tests and numerical simulations of super-critical adjust stage blade were carried out and the effect of bowed blade on flow characteristics and the secondary flow were analyzed. The simulation and test results show th...Tests and numerical simulations of super-critical adjust stage blade were carried out and the effect of bowed blade on flow characteristics and the secondary flow were analyzed. The simulation and test results show that the adjust stage blade with aft-loading and big front-edge radius has good flow characteristics by meridian shrink. The numerical studies were carried out with software of NUMECA in order to investigate the aerodynamic characteristics of adjust stage blades,which include prototype blade(tested blade) ,positive curved blade (15°) and negative curved blade(-15°) . The simulation results show that the positive curved blade forms a negative static pressure gradient in the lower region of the cascade along the blade height and a positive static pressure gradient in the upper region. This leads to the reduction of the streamwise vortices intensity and the aerodynamic load on both sides of the blade and the endwall. Therefore,the crosswise secondary flow losses of endwall can be decreased considerably.展开更多
The impact of boundary layer suction on the aerodynamic performance of a high-turning compressor cascade was numerically simulated and discussed.The aerodynamic performance of a curved and a straight cascade with and ...The impact of boundary layer suction on the aerodynamic performance of a high-turning compressor cascade was numerically simulated and discussed.The aerodynamic performance of a curved and a straight cascade with and without boundary layer suction were comparatively studied at several suction flow rates.The results showed that boundary layer suction dramatically improved the flow behavior within the flow passage.Moreover,higher loading over the whole blade height,lower total pressure loss,and higher passage throughflow were achieved with a relatively small amount of boundary layer removal.The integration of curved blade and boundary layer suction contributed to better aerodynamic performance than the cascades with only curved blade or boundary layer suction used,and the more favorable effect resulted from the weakening of the three dimensional effects of the boundary layer close to the endwalls.展开更多
文摘Compared with a straight blade, a unique compressor blade integratedforward-swept and positive-curved stacking line is studied experimentally. Aerodynamic parameters ofthe two cascades are measured by a five-hole probe at different positions and ink trace flowvisualization is conducted on blade surfaces. The result shows that the swept-curved cascade haslower endwall loss and higher midspan loss as compared with the straight cascade. However, lowerloss is accompanied with lower diffusion factor. Opposite 'C' shape static pressure distribution isestablished on the suction surface of the swept-curved blade, which is helpful for avoiding theaccumulation of low energy fluid in the endwall corner region. Anyhow the studies support theconclusion that the swept-curved blade conduces to not only the reduction of overall loss but alsothe improvement of stable operation in the endwall corner region.
文摘Geometric parameters of the turbine blade are classified according to their destined functions, and the mathematical definition of those parameters in the section curve is introduced in detail. Some parts of the section curve shape can be adjusted freely, offering more flexibility to designers.
文摘Tests and numerical simulations of super-critical adjust stage blade were carried out and the effect of bowed blade on flow characteristics and the secondary flow were analyzed. The simulation and test results show that the adjust stage blade with aft-loading and big front-edge radius has good flow characteristics by meridian shrink. The numerical studies were carried out with software of NUMECA in order to investigate the aerodynamic characteristics of adjust stage blades,which include prototype blade(tested blade) ,positive curved blade (15°) and negative curved blade(-15°) . The simulation results show that the positive curved blade forms a negative static pressure gradient in the lower region of the cascade along the blade height and a positive static pressure gradient in the upper region. This leads to the reduction of the streamwise vortices intensity and the aerodynamic load on both sides of the blade and the endwall. Therefore,the crosswise secondary flow losses of endwall can be decreased considerably.
基金Sponsored by the National Natural Science Foundation of China(Grant No.50646021).
文摘The impact of boundary layer suction on the aerodynamic performance of a high-turning compressor cascade was numerically simulated and discussed.The aerodynamic performance of a curved and a straight cascade with and without boundary layer suction were comparatively studied at several suction flow rates.The results showed that boundary layer suction dramatically improved the flow behavior within the flow passage.Moreover,higher loading over the whole blade height,lower total pressure loss,and higher passage throughflow were achieved with a relatively small amount of boundary layer removal.The integration of curved blade and boundary layer suction contributed to better aerodynamic performance than the cascades with only curved blade or boundary layer suction used,and the more favorable effect resulted from the weakening of the three dimensional effects of the boundary layer close to the endwalls.
