Flow and modification characteristics of sector intermediate turbine duct
To analyze the aerodynamic performance of a sector intermediate turbine duct,numerical and experimen-tal research focusing on complementary and mutual verification was conducted for a sector intermediate turbine duct.The loss areas and their causes in the sector transition section were analyzed.Additionally,the profile of the transition section was modified using an empirical formula and designed through both experiments and numerical simulations.A periodic numerical simulation was performed to study the prototype sector turbine intermediate tur-bine duct and to identify the main sources of loss in the sector intermediate turbine duct.Our results indicated that the loss in the transition section of the fan-shaped turbine occurred mainly on both sides of the casing at 0.07Ma and 0.14Ma.At other Mach numbers,the loss area was close to the center of the support plate and the left and right end walls due to the combined effects of end wall friction and flow reverse pressure difference.In periodic sim-ulation,the loss area of the outlet surface was located in the central area behind the support plate.Different profile models exhibited different flow processes.The diffusion flow mode,characterized by rapid diffusion followed by slow diffusion of an isobaric gradient profile,effectively reduced the loss in the transition section.Both the loss area and its numerical value were considerably reduced compared with the prototype.
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维普
