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Reasons for low aerodynamic performance of 13.5-centimeter-tip-diameter aircraft engine starter turbine
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Hermann, P. Haas, J. E. Roelke, R. J. |
| Copyright Year | 1981 |
| Description | The reasons for the low aerodynamic performance of a 13.5 cm tip diameter aircraft engine starter turbine were investigated. Both the stator and the stage were evaluated. Approximately 10 percent improvement in turbine efficiency was obtained when the honeycomb shroud over the rotor blade tips was filled to obtain a solid shroud surface. Efficiency improvements were obtained for three rotor configurations when the shroud was filled. It is suggested that the large loss associated with the open honeycomb shroud is due primarily to energy loss associated with gas transportation as a result of the blade to blade pressure differential at the tip section. |
| File Size | 1058321 |
| Page Count | 20 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19810011548 |
| Archival Resource Key | ark:/13960/t6256ff1r |
| Language | English |
| Publisher Date | 1981-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Blade Tips Turbine Blades Shrouds Ducted Bodies Power Efficiency Aircraft Engines Honeycomb Structures Aerodynamic Characteristics Turbine Engines Engine Starters Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
