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Experimental flow coefficients of a full-coverage film-cooled-vane chamber
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Hippensteele, S. A. Meitner, P. L. |
| Copyright Year | 1977 |
| Description | Ambient- and elevated-temperature flow tests were performed on a four-times-actual-size model of an impingement- and film-cooled segment of a core engine turbine vane. Tests were conducted with the impingement and film cooling plates combined to form a chamber and also with each of the individual separated plates. For the combined tests, the proximity of the film cooling plate affected the flow of coolant through the impingement plate, but not conversely. Impingement flow is presented in terms of a discharge coefficient, and the film cooling flow discharging into still air with no main stream gas flow is presented in terms of a total pressure-loss coefficient. The effects of main stream gas flow on discharge from the film cooling holes are evaluated as a function of coolant to main-stream gas momentum flux ratio. A smoothing technique is developed that identifies and helps reduce flow measurement data scatter. |
| File Size | 1301560 |
| Page Count | 33 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19770025209 |
| Archival Resource Key | ark:/13960/t3cz8117z |
| Language | English |
| Publisher Date | 1977-09-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Flow Coefficients Turbine Blades Perforated Plates Discharge Coefficient Gas Flow Flow Chambers Film Cooling Turbine Engines 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 |
