Add to ORKGThe 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
The design principle of injecting liquid fuel at more than one axial station in an annual turbojet c...
Combustion efficiencies obtained with gaseous methane were compared with reported data obtained with...
Effect of fuel injector and liner design on performance of turbojet combustor with vapor fue
The combustion performance and particularly the phenomenon of altitude operational limits was studie...
Methods of introducing and distributing air and fuel in turbojet-engine combustors were evaluated wi...
The combustion performance, and particularly the phenomenon of altitude operational limits, was stud...
An investigation was conducted with a single combustor from a J47 turbojet engine using weathered av...
Some of the systematic research conducted by the NACA on aircraft gas-turbine combustors is reviewed...
A 19XB-1 combustor was operated under conditions simulating zero-ram operation of the 19XB-1 turboje...
"An investigation has been conducted on a one-sixth segment of an annular turbojet combustor to dete...
NACA research on the single problem of combustion efficiency of turbojet engines at high altitudes i...
An investigation of a single-annulus turbojet combustor with slot-type air admission was conducted t...
Acceleration and steady-state performance of a tubular combustor was evaluated at two simulated alti...
Combustion must be maintained in the turbojet-engine combustor over a wide range of operating condit...
An annular prevaporizing turbojet combustor having pressure losses lower than those obtained in curr...
The design principle of injecting liquid fuel at more than one axial station in an annual turbojet c...
Combustion efficiencies obtained with gaseous methane were compared with reported data obtained with...
Effect of fuel injector and liner design on performance of turbojet combustor with vapor fue
The combustion performance and particularly the phenomenon of altitude operational limits was studie...
Methods of introducing and distributing air and fuel in turbojet-engine combustors were evaluated wi...
The combustion performance, and particularly the phenomenon of altitude operational limits, was stud...
An investigation was conducted with a single combustor from a J47 turbojet engine using weathered av...
Some of the systematic research conducted by the NACA on aircraft gas-turbine combustors is reviewed...
A 19XB-1 combustor was operated under conditions simulating zero-ram operation of the 19XB-1 turboje...
"An investigation has been conducted on a one-sixth segment of an annular turbojet combustor to dete...
NACA research on the single problem of combustion efficiency of turbojet engines at high altitudes i...
An investigation of a single-annulus turbojet combustor with slot-type air admission was conducted t...
Acceleration and steady-state performance of a tubular combustor was evaluated at two simulated alti...
Combustion must be maintained in the turbojet-engine combustor over a wide range of operating condit...
An annular prevaporizing turbojet combustor having pressure losses lower than those obtained in curr...
The design principle of injecting liquid fuel at more than one axial station in an annual turbojet c...
Combustion efficiencies obtained with gaseous methane were compared with reported data obtained with...
Effect of fuel injector and liner design on performance of turbojet combustor with vapor fue