A Method for Calculating Turbulent Boundary Layers and Losses in the Flow Channels of Turbomachines.
Abstract
An interactive inviscid core flow boundary layer method is presented for the calculation of turbomachine channel flows. For this method, a one-dimensional inviscid core flow is assumed. The end wall and blade surface boundary layers are calculated using an integral entrainment method. The boundary layers are assumed to be collateral and thus are two-dimensional. The boundary layer equations are written in a streamline coordinate system. The streamwise velocity profiles are approximated by power law profiles. Compressibility is accounted for in the streamwise direction but not in the normal direction. Equations are derived for the special cases of conical and two dimensional rectangular diffusers. For these cases, the assumptions of a one dimensional core flow and collateral boundary layers are valid. Results using the method are compared with experiment and good quantitative agreement is obtained. Keywords: Turbomachine flow; Conical diffuser; Rectangular diffuser; Turbulent boundary layer; Entrainment method; Compressible flow.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1987
- Accession Number
- ADA178164
Entities
People
- Lawrence F. Schumann
Organizations
- National Aeronautics and Space Administration