Altitude-wind-tunnel investigation of various can-type burners in Bumblebee 18-inch ram jet

Dupree, D T Nussdorfer, T J Sterbentz, W H
naca-rm-e8l20
March 16, 1949


An investigation on various can-type burners in a Bumblebee 18-inch ram jet under controlled conditions of pressure altitude and ram pressure ratio was conducted in the NACA Lewis altitude wind tunnel with kerosene as fuel. The performance of the following can-type burner configurations was better than that of the other burner configurations investigated: (1) a flame holder having a two-pitch alinement of perforations, 0.07-inch-wide cooling slots, and an arrangement of fuel nozzles located within an annulus having a mean radius of 7.24 inches; and (2) a flame holder having a zero-pitch alinement of perforations, 0.16-inch-wide cooling slots, and an annulus of fuel nozzles having a mean radius of 6.89 inches. The maximum net-thrust coefficient and minimum specific fuel consumption were obtained with the ram-jet configuration that consisted of the burner just described having a flame holder with a two-pitch alinement of perforations and a combustion-chamber outlet restricted by a 14-and-three-quarter-inch-diameter orifice plate. At a ram pressure ratio equivalent to a free-stream Mach number of 1.44 and a pressure altitude of 30,000 feet, the net-thrust coefficient was 0.68 and the reduced specific fuel consumption was 3.0 pounds of fuel per hour per pound of net thrust.

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