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Two-dimensional cold-air cascade study of a film-cooled turbine stator blade. 4: comparison of experimental and analytical aerodynamic results for blade with 12 rows of 0.076-centimeter-(0.030-inch-) diameter holes having streamwise ejection angles
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Prust Jr., H. W. |
| Copyright Year | 1978 |
| Description | Previously published experimental aerodynamic efficiency results for a film cooled turbine stator blade are compared with analytical results computed from two published analytical methods. One method was used as published; the other was modified for certain cases of coolant discharge from the blade suction surface. For coolant ejection from blade surface regions where the surface static pressures are higher than the blade exit pressure, both methods predict the experimental results quite well. However, for ejection from regions with surface static pressures lower than the blade exit pressure, both methods predict too small a change in efficiency. The modified method gives the better prediction. |
| File Size | 2729503 |
| Page Count | 31 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19780012187 |
| Archival Resource Key | ark:/13960/t82k17h1z |
| Language | English |
| Publisher Date | 1978-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Turbomachine Blades Cascade Flow Turbine Blades Stator Blades Turbomachinery Film Cooling Two Dimensional Flow Aerodynamic Characteristics 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 |
