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An adverse effect of film cooling on the suction surface of a turbine vane (Document No: 19740012480)
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Gauntner, J. W. Gladden, H. J. |
| Copyright Year | 1974 |
| Description | Film-cooling-air ejection from the suction surface of a turbine vane was investigated. This investigation was conducted in a four-vane cascade on a J75 size turbine vane which had a row of holes near the leading edge. The experimental data are presented. It was found that a small amount of film-cooling air has a detrimental effect on the downstream vane wall cooling effectiveness. It was also shown that the presence of the film-cooling holes, without blowing, also cause an increase in vane wall temperatures. These results came from an increase in the gas-side heat transfer coefficient that was apparently caused by a laminar or transitional boundary layer becoming transitional or turbulent. |
| File Size | 756105 |
| Page Count | 26 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740012480 |
| Archival Resource Key | ark:/13960/t41s1k96g |
| Language | English |
| Publisher Date | 1974-04-01 |
| Access Restriction | Open |
| Subject Keyword | Thermodynamics And Combustion Wall Temperature Laminar Boundary Layer Turbine Blades Turbulent Boundary Layer Film Cooling Leading Edges Heat Transfer 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 |
