Nonuniform Energy Transfer in Axial Flow Compressors.
Abstract
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1980
- Accession Number
- ADA100443
Entities
People
- G. Holbrook
Organizations
- von Kármán Institute for Fluid Dynamics