Vortex-generating coolant-flow-passage design for increased film-cooling effectiveness and surface coverage
Abstract
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.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- November 1984
- Bibcode:
- 1984STIN...8512314P
- Keywords:
-
- Ducts;
- Engine Coolants;
- Film Cooling;
- Flow Characteristics;
- Passageways;
- Vortices;
- Aircraft Engines;
- Cross Flow;
- Flow Visualization;
- Fluid Jets;
- Infrared Imagery;
- Fluid Mechanics and Heat Transfer