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Single-stage experimental evaluation of tandem-airfoil rotor and stator blading for compressors. part 7: data and performance for stage e
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Cheatham, J. G. |
| Copyright Year | 1974 |
| Description | An axial flow compressor stage, having tandem airfoil blading, was designed for zero rotor prewhirl, constant rotor work across the span, and axial discharge flow. The stage was designed to produce a pressure ratio of 1.265 at a rotor tip velocity of 757 ft/sec. The rotor has an inlet hub/tip ratio of 0.8. The design procedure accounted for the rotor inlet boundary layer and included the effects of axial velocity ratio and secondary flow on blade row performance. The objectives of this experimental program were (1) to obtain performance with uniform and distorted inlet flow for comparison with the performance of a stage consisting of single-airfoil blading designed for the same vector diagrams and (2) to evaluate the effectiveness of accounting for the inlet boundary layer, axial velocity ratio, and secondary flows in the stage design. |
| File Size | 18422842 |
| Page Count | 276 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740008372 |
| Archival Resource Key | ark:/13960/t4cp1w70g |
| Language | English |
| Publisher Date | 1974-01-28 |
| Access Restriction | Open |
| Subject Keyword | Propulsion Systems Tables Data Turbocompressors Performance Tests Compressor Blades Stator Blades Inlet Flow Secondary Flow Graphs Charts 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 |
