Page:Performance of a high-speed compression-ignition engine using multiple orifice fuel injection nozzles.djvu/2



This report presents test results obtained at the Langley Memorial Aeronautical Laboratory of the National Advisory Committee for Aeronautics during an investigation to determine the relative performance of a single-cylinder, high-speed, compression-ignition engine when using fuel injection valve nozzles with different numbers, sizes, and directions of round orifices. A spring-loaded, automatic injection valve was used, centrally located at the top of a vertical disk-type combustion chamber formed between horizontally opposed inlet and exhaust valves of a 5-inch by 7-inch engine.

A series of fuel injection valve nozzles with different arrangements of round orifices were tested, starting with orifices so small that impingement on the combustion chamber walls was impossible and increasing beyond the start of impingement. From these data two main jets of 0.018-inch diameter were decided upon and the other jets varied in number, size, and direction, A nozzle was tested with the area of the orifices proportional to the volume of air to be served by the jets using the