Mixing effectiveness test of an exhaust gas mixer in a high bypass turbofan at altitudeThermal mixing effectiveness characteristics of an eighteen lobe, scalloped and unscalloped, partial, forced mixer were measured in a high-bypass turbofan engine. Data were also obtained without the mixer installed, i.e. free mixing. Tests were conducted at four combinations of simulated flight conditions from 0.3 to 0.8 Mach number and from 6,096 meters (20,000 ft) to 13,715 m (45,000 ft) altitude. Mixing chamber lengths of L/D = 0.52 and 0.65 were tested. For this range of test conditions and mixer configurations the forced mixing effectiveness varied from 59 to 68 percent. Values of mixing effectiveness and total pressure loss were calculated from temperature and pressure data obtained at the mixer inlet and exhaust nozzle exit.
Document ID
19810059821
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cullom, R. R. (NASA Lewis Research Center Cleveland, OH, United States)
Burkardt, L. A. (NASA Lewis Research Center Cleveland, OH, United States)
Bobula, G. A. (U.S. Army, Propulsion Laboratory, Cleveland OH, United States)