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Effect of wall suction on performance of a short annular diffuser at inlet mach numbers up to 0.5. [gas turbine engines
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Juhasz, A. J. |
| Copyright Year | 1975 |
| Description | A short annular diffuser equipped with wall bleed (suction)capability was evaluated at inlet Mach numbers of 0.186 to 0.5. The diffuser had an area ratio of 4.0 and a length-to-inlet height ratio of 1.6. Test results show that the exit velocity profiles, typical of annular jet flow without suction, could be considerably flattened by application of wall suction. This improved performance was also reflected in diffuser effectiveness (static-pressure recovery) and total-pressure loss results. At the inlet Mach number of 0.5 diffuser static-pressure recovery is equal to or better than at lower inlet Mach numbers for comparable suction rates. |
| File Size | 1956796 |
| Page Count | 25 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19750024928 |
| Archival Resource Key | ark:/13960/t6353f20h |
| Language | English |
| Publisher Date | 1975-10-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Suction Air Flow Performance Tests Wall Pressure Jet Flow Gas Turbine Engines Compressors Inlet Flow Diffusers Velocity Distribution Boundary Layer Control Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
