Design of a 1500 Ft/Sec, Transonic, High-through-Flow, Single-Stage Axial-Flow Compressor with Low Hub/Tip Ratio
Abstract
This report describes the aerodynamic design of a transonic axial- flow compressor inlet stage designed for high flow rate per unit frontal area and relatively high aerodynamic loading. The performance objectives of this stage were derived from a preliminary design study of a multi-stage compressor for an advanced turbojet engine. The design goals chosen included a tip speed of 1500 ft/sec, a flow rate of 39.7 lb/sec per square foot of frontal area, a stage total pressure ratio of 1.91 and a stage isentropic efficiency of 0.83. The techniques used in the preliminary and detail designs are described. The complete aerodynamic flow field pertaining to the design point is defined on twenty-one stream surfaces, and radial and meridional distributions of significant parameters are presented. Finally, the detailed flowpath geometry is defined and airfoil coordinates are included for both stream surfaces and cartesian manufacturing sections.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1976
- Accession Number
- ADB016386
Entities
People
- Arthur J. Wennerstrom
- George R. Frost
Organizations
- Air Force Research Laboratory