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Augmentation of stagnation region heat transfer due to turbulence from a dln can combustor
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | VanFossen Sr., G. James Bunker, Ronald S. |
| Copyright Year | 2000 |
| Description | Heat transfer measurements have been made in the stagnation region of a flat plate with a circular leading edge. Electrically heated aluminum strips placed symmetrically about the leading edge stagnation region were used to measure spanwise averaged heat transfer coefficients. The maximum Reynolds number obtained, based on leading edge diameter, was about 100,000. The model was immersed in the flow field downstream of an approximately half scale model of a can-type combustor from a low NO(x), ground based power-generating turbine. The tests were conducted with room temperature air; no fuel was added. Room air flowed into the combustor through six vane type fuel/air swirlers. The combustor can contained no dilution holes. The fuel/air swirlers all swirled the incoming airflow in a counter clockwise direction (facing downstream). A 5-hole probe flow field survey in the plane of the model stagnation point showed the flow was one big vortex with flow angles up to 36' at the outer edges of the rectangular test section. Hot wire measurements showed test section flow had very high levels of turbulence, around 28.5 percent, and had a relatively large axial-length scale-to-leading edge diameter ratio of 0.5. X-wire measurements showed the turbulence to be nearly isotropic. Stagnation heat transfer augmentation over laminar levels was around 77 percent and was about 14 percent higher than predicted by a previously developed correlation for isotropic grid generated turbulence. |
| File Size | 816435 |
| File Format | |
| Language | English |
| Publisher Date | 2000-07-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Turbulent Flow Wind Tunnels Flat Plates Scale Models Data Acquisition Hot-wire Flowmeters Stagnation Point Turbulence Meters Augmentation Gas Turbines Stagnation Flow Test Chambers Flow Distribution Isotropic Turbulence Combustion Chambers Heat Transfer Coefficients Heat Transfer Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
