DTIC ADA1004437: Nonuniform Energy Transfer in Axial pdf

DTIC ADA1004437: Nonuniform Energy Transfer in Axial

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Current through flow calculation schemes provide the compressor designer with a 2D inviscid flow analysis of a blade row. Due to blade curvature and viscous effects the flow field is quite 3D. A numerical scheme has been developed to calculate the radial migration of secondary flows in a rotating blade row and the influence of these flows on the energy transfer of the rotor. A simple set of equations for the radial equilibrium and resulting trajectory of these fluid particles is derived. A boundary layer calculation was added to correctly model rotor boundary layer fluid. The calculation scheme was then applied to 2D flow field obtained from an existing through flow analysis of a transonic rotor. The results showed the twisting of the free stream streamsheet due to the blade-to-blade velocity gradient, the magnitude of the boundary layer migration and the influence of the radial shift on the enthalpy rise of these particles.

The resulting values of radial velocity and temperature rise are similar to experimentally measured values. Thus, this calculation scheme can provide the compressor designer with a quick first approximation of the influence of 3D and viscous effects on the flow field of a rotating blade row. (Author

• Creator/s: Defense Technical Information Center
• Date: 6/1/1980
• Year: 1980
• Book Topics/Themes: DTIC Archive, Holbrook, G, VON KARMAN INST FOR FLUID DYNAMICS RHODE-SAINT-GENESE (BELGIUM), *ENERGY TRANSFER, *FLOW FIELDS, *NONUNIFORM FLOW, *AXIAL FLOW COMPRESSORS, TWO DIMENSIONAL, BOUNDARY LAYER, THREE DIMENSIONAL, TURBINE BLADES, CURVATURE, PARTICLES, APPROXIMATION(MATHEMATICS), VISCOSITY, SECONDARY FLOW, RADIAL VELOCITY

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