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Vortex-generating coolant-flow-passage design for increased film-cooling effectiveness and surface coverage
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Papell, S. S. |
| Copyright Year | 1984 |
| Description | The thermal film-cooling footprints observed by infrared imagery for three coolant-passage configurations embedded in adiabatic-test plates are discussed. The configurations included a standard round-hole cross section and two orientations of a vortex-generating flow passage. Both orientations showed up to factors of four increases in both film-cooling effectiveness and surface coverage over that obtained with the round coolant passage. The crossflow data covered a range of tunnel velocities from 15.5 to 45 m/sec with blowing rates from 0.20 to 2.05. A photographic streakline flow visualization technique supported the concept of the counterrotating apability of the flow passage design and gave visual credence to its role in inhibiting flow separation. |
| File Size | 3797657 |
| Page Count | 28 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19850004006 |
| Archival Resource Key | ark:/13960/t24b7x79b |
| Language | English |
| Publisher Date | 1984-11-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Engine Coolants Fluid Jets Passageways Ducts Vortices Flow Visualization Flow Characteristics Film Cooling Aircraft Engines Infrared Imagery Cross Flow 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 |
