| Abstract | Under Laboratory Order 6539-A, the Engine Laboratory began initial development work on an annular combustion chamber for a large aircraft gas turbine. The engine was to be a 10,000 pound thrust, axial flow unit, with a sea level static mass flow of about 200 lb. /sec., and a pressure ratio of 7 to 1.
Work on this project proceeded along two lines, one using a sector comprising one-sixth of the annulus, and using a vaporizing fuel system, the other a study of the primary zone only, and utilizing pneumatio atomization and swirling flow in the annulus. The latter required the use of the complete annulus and, since air supply and pressure were limited, only the primary zone could be studied. Promising results were obtained, however, and it was desired to test a complete annular chamber on an atmospheric rig to study the fuel atomization system further. |
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