Flame Radiation in a Gas Turbine Combustor Gas Turbine Combustion Laboratory, Thermal Sciences and Propulsion Center, School of Mechanical Engineering, Purdue Univ. West Lafayette, IN

Format:

Conference/Event

Author/Creator:

Cummings, W. G., author.

Conference Name:

1985 SAE International Fall Fuels and Lubricants Meeting and Exhibition (1985-10-21 : Tulsa, Oklahoma, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1985

Summary:

Flame radiation measurements are presented for a gas turbine combustor analog. The test rig consists of a 15-cm diameter air-cooled liner, multipoint airblast atomizer and a high-temperature, high pressure air supply. Combustor pressures spanned the range 5-10 atm, and combustor inlet temperature was fixed at 560K. A unique feature of the test rig is its multipoint airblast atomizer. The atomizer consists of an evenly distributed array of 68 "microscopic" air-blast nozzles and produces sprays with SMD between 15 and 45 m. An important characteristic of the atomizer is its ability to vary the spray SMD independent of main combustor air flow conditions. This allows separation of physical effects, due to spray formation, from the chemical effects, due to changing fuel type. Separation of physical and chemical effects has not been accomplished by previous researchers. Flame radiation was measured as a continuous function of axial position. This was accomplished by translation of the atomizer-stabilizer-flame front relative to the system optical axis. The modified Schmidt technique was used for all radiation measurements. The effects of inlet pressure, temperature, air velocity, and equivalence ratio are presented for a single fuel, Diesel Fuel #2

Notes:

Vendor supplied data

Publisher Number:

852084

Access Restriction:

Restricted for use by site license