The combustion performance, and particularly the phenomenon of altitude operational limits, was studied by operating the annular combustor of a turbojet engine over a range of conditions of air flow, inlet pressure, inlet temperature, and fuel flow. Information was obtained on the combustion efficiencies, the effect on combustion of inlet variables, the altitude operational limits with two different fuels, the pressure losses in the combustor, the temperature and velocity profiles at the combustor outlet, the extent of afterburning, the fuel-injection characteristics, and the condition of the combustor basket.
Effect of combustor-inlet conditions on performance of an annular turbojet combustor
1947-01-01
Miscellaneous
No indication
English
Effect of combustor-inlet conditions on performance of Annular Turbojet Combustor
Engineering Index Backfile | 1947
|Effect of combustor-inlet conditions on performance of annular turbojet combustor
Engineering Index Backfile | 1947
|