Embedded heat flux sensors fabricated using direct-write technology have been developed and tested within a direct-connect gaseous hydrocarbon-fueled scramjet combustor under Mach 5 flight conditions. The sensors employed a multilayer thermopile architecture fabricated via the additive direct-write thermal spray process, which enables their integration directly onto the components to be tested. The sensors were embedded within a 0.50-mm-thick (0.020-in.-thick) thermal barrier coating on test plugs that were inserted into the tunnel for testing. Fuel equivalence ratios and dynamic pressures were varied from to 1.0 and and 48 kPa (500 and 1000 psf), respectively, with increases in the global heat flux found to depend on the tunnel location. Heat flux values ranging from 30 to (26 to ) were measured downstream of the cavity flame holder, 20 to (18 to ) in the cavity flame holder, and 20 to (18 to ) upstream of the flame holder. Direct-write sensors reported heat flux trends that were consistent with separate area-averaged calorimetric measurements, and the local nature of the direct-write sensors enabled the detection of subtle transient phenomena not captured by calorimetry.
Heat Flux Measurements in a Scramjet Combustor Using Embedded Direct-Write Sensors
Journal of Propulsion and Power ; 31 , 4 ; 1003-1013
2015-03-24
11 pages
Article (Journal)
Electronic Resource
English
Heat Flux Measurements in a Scramjet Combustor Using Direct Write Technology
British Library Conference Proceedings | 2011
|AIAA | 2009
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