Loading...
Please wait, while we are loading the content...
Similar Documents
Flow visualization of discrete-hole film cooling with spanwise injection over a cylinder
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Russell, L. M. |
| Copyright Year | 1979 |
| Description | Insight into the fluid mechanics encountered when film air from a single row of holes is injected over a cylinder in a mainstream at conditions simulating a film cooled, turbulent-vane leading edge was investigated. Smoke was added to the cooling air to visualize its flow path. Film was injected in the spanwise direction at angles of 30 deg and 45 deg to the surface; at angular locations of 15 deg, 30 deg, 45 deg, and 60 deg from the stagnation line; and at various blowing ratios. The observations were related to the measured heat transfer data of others. The results indicate that, in addition to the expected growth in film thickness and the greater penetration of the boundary layer with increasing blowing ration, there was an absence of spanwise spreading and only a small spanwise deflection of the injected film. |
| File Size | 648725 |
| Page Count | 15 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790018971 |
| Archival Resource Key | ark:/13960/t4vj0bq2p |
| Language | English |
| Publisher Date | 1979-07-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Fluid Mechanics Turbine Blades Inlet Flow Smoke Liquid Injection Film Thickness Heat Flux Air Cooling Vanes Flow Visualization Film Cooling Spanwise Blowing Leading Edges Heat Transfer Boundary Layers 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 |
