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Stagnation region gas film cooling: spanwise angled injection from multiple rows of holes. [gas turbine engines
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Lecuyer, M. R. Luckey, D. W. |
| Copyright Year | 1981 |
| Description | The stagnation region of a cylinder in a cross flow was used in experiments conducted with both a single row and multiple rows of spanwise angled (25 deg) coolant holes for a range of the coolant blowing ratio with a freestream to wall temperature ratio approximately equal to 1.7 and R(eD) = 90,000. Data from local heat flux measurements are presented for injection from a single row located at 5 deg, 22.9 deg, 40.8 deg, 58.7 deg from stagnation using a hole spacing ratio of S/d(o) = 5 and 10. Three multiple row configurations were also investigated. Data are presented for a uniform blowing distribution and for a nonuniform blowing distribution simulating a plenum supply. The data for local Stanton Number reduction demonstrated a lack of lateral spreading by the coolant jets. Heat flux levels larger than those without film cooling were observed directly behind the coolant holes as the blowing ratio exceeded a particular value. The data were spanwise averaged to illustrate the influence of injection location, blowing ratio and hole spacing. The large values of blowing ratio for the blowing distribution simulating a plenum supply resulted in heat flux levels behind the holes in excess of the values without film cooling. An increase in freestream turbulence intensity from 4.4 to 9.5 percent had a negligible effect on the film cooling performance. |
| File Size | 18090854 |
| Page Count | 382 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19810016797 |
| Archival Resource Key | ark:/13960/t3mw7835w |
| Language | English |
| Publisher Date | 1981-04-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Forced Convection Turbine Blades Hole Distribution Mechanics Gas Turbine Engines Stagnation Point Blowing Holes Mechanics Stanton Number Film Cooling Free Flow Fluid Injection Leading Edges Graphs Charts 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 |
