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Cold-air annular-cascade investigation of aerodynamic performance of core-engine-cooled turbine vanes. 2: pressure surface trailing edge ejection and split trailing edge ejection
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Goldman, L. J. McLallin, K. L. |
| Copyright Year | 1976 |
| Description | The aerodynamic performance of two trailing edge ejection cooling configurations of a core-engine stator vane were experimentally determined in an ambient inlet-air full-annular cascade where three-dimensional effects could be obtained. The tests were conducted at the design mean-radius ideal aftermixed critical velocity ratio of 0.778. Overall vane aftermixed thermodynamic and primary efficiencies were obtained over a range of coolant flows to about 10 percent of the primary flow at a primary to coolant total temperature ratio of 1.0. The radial variation in efficiency and the circumferential and radial variations in vane-exit total pressure were determined. Comparisons are made with the solid (uncooled) vane. |
| File Size | 5874055 |
| Page Count | 25 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760014113 |
| Archival Resource Key | ark:/13960/t7pp3w54w |
| Language | English |
| Publisher Date | 1976-04-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Cascade Flow Performance Tests Gas Cooling Three Dimensional Flow Aerodynamic Heat Transfer Trailing Edges Vanes Stator Blades Cold Flow Tests Secondary Flow Annular Flow Ejection 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 |
