The Design of an Axial Compressor Stage for a Total Pressure Ratio of 3 to 1
Abstract
The report describes in detail the aerodynamic design of a supersonic axial compressor stage. The principal design-point characteristics of the stage are a corrected tip speed of 1600 ft/sec, an inlet hub/tip radius ratio of 0.75, a total pressure ratio of 3.0, and an isentropic efficiency of 82%. Four features distinguish this stage from other reported stages. A new type of rotor airfoil is employed. The stator leading edges are swept back from both walls toward mid-passage. Unusually large and variable fillet radii blend blades with platforms. Also, a new and precise technique was used to determine Cartesian manufacturing coordinates for the airfoils, aerodynamically defined on streamsurfaces. The preliminary design employed a technique resulting in equilibrium radial distributions of loss coefficient and flow angle which are fully consistent with relative Mach numbers and diffusion factors for each blade row and on each streamsurface according to a prescribed loss model. The detail design was accomplished using computing stations internal as well as external to both blade rows and attempted to optimize the axial distribution of static pressure.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1971
- Accession Number
- AD0727001
Entities
People
- Arthur J. Wennerstrom
- Richard M. Hearsey
Organizations
- Air Force Research Laboratory