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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2015, Vol. 36 ›› Issue (10): 3249-3262.doi: 10.7527/S1000-6893.2015.0134

• Fluid Mechanics and Flight Mechanics • Previous Articles     Next Articles

Energy loss in a low-speed compressor cascade with dissipation function

TIAN Simeng1,2, WU Yun1,2, ZHANG Haideng3, LI Yinghong1, LI Jun1   

  1. 1. College of Aeronautics and Astronautics Engineering, Air Force Engineering University, Xi'an 710038, China;
    2. College of Aeronautics and Astronautics, Xi'an Jiaotong University, Xi'an 710091, China;
    3. College of Energy and Power Engineering, Beihang University, Beijing 100191, China
  • Received:2014-11-05 Revised:2015-05-14 Online:2015-10-15 Published:2015-06-30
  • Supported by:

    National Natural Science Foundation of China (51207169, 51276797)

Abstract:

A viscous incompressible flow model in compressor cascade is set up without chemical reaction and heat input. Each of these components is resolved from the energy dissipation function with the derivation of the formula and simplified according to the simulation result in compressor cascade. These main factors are summarized as streamwise-vorticity item, axial resistance and shear force. Then, the axial characteristic of each component of the energy dissipation function is discussed in leading-edge loss, profile loss and passage loss with total pressure loss efficient. The streamwise-vorticity item, as the primary factor in passage loss to reflect the vortex structure in cascade, is concentrated near the passage vortex and separation surface. The axial resistance is concentrated on the boundary layer in the front of cascade passage, which is the key factor in leading-edge loss and profile loss to reflect the flow loss in diffusion and turning of boundary layer. The shear force item is concentrated on the separation surface and the boundary layer near the suction surface and endwall, which is the key factor in passage loss and profile loss to reflect the inhomogeneity of velocity. The relation between vortex structure and the energy dissipation is investigated with the distribution characteristic. One large dissipation zone is also found between main flow and corner separation region, which is influenced by υ(∂Vx/∂y)2 and the streamwise-vorticity item. Another is developed because of boundary layer near blades, which is influenced by flow resistance at the front part and υ(∂Vx/∂y)2 in the rear part. Governing factors on each axial plane are found while the key factor to energy dissipation is the shear item. The passage loss is significantly increased with high angle of attack, while the induction of streamwise-vorticity item is earlier in positive incidence and the shear force in boundary layer is higher in negative incidence.

Key words: low-speed compressor cascade, energy dissipation rate, total pressure loss, vortex structure, angle of attack characteristic

CLC Number: