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Experimental verification of film-cooling concepts on a turbine vane
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Gauntner, J. W. Gladden, H. J. |
| Copyright Year | 1975 |
| Description | Film cooling concepts applied to gas turbine vanes were investigated. The filming cooling air was ejected from a single row of holes on the convex surface and a double row of holes of the concave surface. Tests were conducted at a gas temperature of 1260 K, a gas pressure of 3 atmospheres, and a coolant temperature of 280 K. Mass velocity ratios were varied between 0 and 2.0. Data were taken without film cooling holes, with film cooling holes but without blowing, and with blowing. A small amount of blowing into a nonturbulent boundary layer caused an increase in vane temperatures. Film cooling when combined with convection cooling was verified to be more effective than either film or convection cooling alone. |
| File Size | 1424294 |
| Page Count | 18 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19750021034 |
| Archival Resource Key | ark:/13960/t6741jk8g |
| Language | English |
| Publisher Date | 1975-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Surface Cooling Convective Heat Transfer Gas Turbines Turbine Blades Turbulence Effects Film Cooling Boundary Layers Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |