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Study of blade aspect ratio on a compressor front stage aerodynamic and mechanical design report
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Burger, G. D. Snow, D. W. Lee, D. |
| Copyright Year | 1979 |
| Description | A single stage compressor was designed with the intent of demonstrating that, for a tip speed and hub-tip ratio typical of an advanced core compressor front stage, the use of low aspect ratio can permit high levels of blade loading to be achieved at an acceptable level of efficiency. The design pressure ratio is 1.8 at an adiabatic efficiency of 88.5 percent. Both rotor and stator have multiple-circular-arc airfoil sections. Variable IGV and stator vanes permit low speed matching adjustments. The design incorporates an inlet duct representative of an engine transition duct between fan and high pressure compressor. |
| File Size | 2690269 |
| Page Count | 71 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790014914 |
| Archival Resource Key | ark:/13960/t7fr4pk36 |
| Language | English |
| Publisher Date | 1979-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Core Flow Low Aspect Ratio Aerodynamic Configurations Airfoil Profiles Rotor Blades Turbomachinery Mechanical Properties Stator Blades Compressors Inlet Flow Velocity Distribution High Pressure Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
