Cold Flow and Combustion Experiments With a New Burner Air Distribution Concept

[+] Author and Article Information
B. V. Johnson

Heat Transfer Technology, United Technologies Research Center, E. Hartford, CT 06108

S. J. Markowski

Combustion Fuels and Emissions, Pratt & Whitney Aircraft Group, E. Hartford, CT 06108

H. M. Craig

Combustion Technology, Pratt & Whitney Aircraft Group, E. Hartford, CT 06108

J. Eng. Gas Turbines Power 108(2), 370-375 (Apr 01, 1986) (6 pages) doi:10.1115/1.3239913 History: Received December 18, 1984; Online October 15, 2009


Experiments were conducted with a JT8D-engine sized can combustor modified such that all the combustion and dilution air entered through the burner front face from a single plenum through counter-rotating annular swirlers. Cold flow experiments were conducted to visualize and to develop a mixing and recirculation flow pattern within the combustor which contained annular and central recirculation cells and featured rapid mixing in the downstream section of the combustor. Laser velocimeter measurements, downstream of the air inlet configuration used in the combustion experiments, showed the largest velocity gradients in the radial direction were in the tangential velocity profile. Low-pressure combustion experiments were conducted with three flat spray fuel nozzle orientations and three air inlet geometries to determine the general air inlet and fuel injection characteristics required to produce acceptable combustion characteristics with the selected swirler configuration. The combustion experiments included emission, total pressure and total temperature measurements at the burner exit plane. Low emission levels and temperature pattern factors with relatively low burner pressure losses were demonstrated.

Copyright © 1986 by ASME
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