| Popis: |
The design and implementation of a rotating probe system for use in supersonic combustion experiments is described. This system contains several components including a remotely-activated servo motor drive, a turntable bearing, a machined probe housing, a cable chain subsystem, three water-cooled exit probe assemblies, and an inclinometer that provides angular position feedback. Optical windows are also integrated into the probe housing allowing access to the exhaust stream for visual monitoring and the application of laser-based diagnostic techniques. Together, these components are installed at the exit of an axisymmetric supersonic combustor. Initially, the probe assemblies are configured to measure Pitot pressure at 17 locations within the combustor exhaust stream. The Pitot pressure measurements provide assessments of flow uniformity at the combustor exit plane. In addition, these measurements, along with assumed values for Mach number and specific heat ratio, can be used in a one-dimensional analysis yielding combustor exit stream thrust. These results can be compared directly with load cell measurements. The probes may also be used to extract gas samples from within the exhaust stream. These gas samples will be analyzed using an on-line system that can determine concentrations of carbon dioxide, carbon monoxide, oxygen, and unburned hydrocarbons. Initial data analyses from tare and combustion tests reveal excellent agreement between the load cell measurements. |
