Abstract
A gas turbine combustor facility (GTCF) has been built and operated for measuring temperature and major species concentrations using dual-pump CARS in combusting flows at above atmospheric pressures. The facility includes a stainless steel window assembly that allows optical access from three sides with a pair of thin and thick windows on each side. It is water-cooled and provides air film-cooling passages; thin windows are designed for thermal load while thick windows are designed for pressure loading. High-speed imaging of combusting flows is performed using the center injector of a 9-point lean direct injection (LDI) device developed at NASA Glenn Research Center. The combustor has been operated using Jet A fuel at inlet air temperatures up to 725 K and combustor pressures up to 10 atm. Dual-pump CARS temperature and major species concentration measurements have been performed in the GTCF at inlet air temperatures up to 725 K and combustor pressures up to 7 atm. Spatial maps of temperature and major species concentrations have been obtained by translating the CARS probe volume in axial and radial directions inside the combustor rig. These measurements will be used for validation of CFD codes under development at NASA Glenn Research Center.
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