Add to ORKGEffect of fuel injector and liner design on performance of turbojet combustor with vapor fue
Two short turbojet combustors designed for use with vaporized hydrocarbon fuels were tested in a one...
Performance investigations were conducted on a combustor utilizing several cost-reducing innovations...
Combustion efficiencies obtained with gaseous methane were compared with reported data obtained with...
The design principle of injecting liquid fuel at more than one axial station in an annual turbojet c...
Performance characteristics at simulated high altitudes of prevaporizing annular turbojet combustor ...
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...
A direct-connect duct investigation was conducted w i t h a one-quarter segment of a 2e-inch-diamete...
Tests of various fuel nozzles were conducted with natural gas fuel in a full-annulus combustor. The ...
A reverse flow combustor suitable for a small gas turbine (2 to 3 kg/s mass flow) was used to evalut...
An annular prevaporizing turbojet combustor having pressure losses lower than those obtained in curr...
The combustion performance and particularly the phenomenon of altitude operational limits was studie...
The combustion process in a reverse-flow combustor suitable for a small gas turbine engine was inves...
As part of a continuing effort at the Lewis Research Center to improve performance, emissions, and r...
Vaporization data that could be useful in designing premixed-prevaporized fuel preparation systems f...
Two short turbojet combustors designed for use with vaporized hydrocarbon fuels were tested in a one...
Performance investigations were conducted on a combustor utilizing several cost-reducing innovations...
Combustion efficiencies obtained with gaseous methane were compared with reported data obtained with...
The design principle of injecting liquid fuel at more than one axial station in an annual turbojet c...
Performance characteristics at simulated high altitudes of prevaporizing annular turbojet combustor ...
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...
A direct-connect duct investigation was conducted w i t h a one-quarter segment of a 2e-inch-diamete...
Tests of various fuel nozzles were conducted with natural gas fuel in a full-annulus combustor. The ...
A reverse flow combustor suitable for a small gas turbine (2 to 3 kg/s mass flow) was used to evalut...
An annular prevaporizing turbojet combustor having pressure losses lower than those obtained in curr...
The combustion performance and particularly the phenomenon of altitude operational limits was studie...
The combustion process in a reverse-flow combustor suitable for a small gas turbine engine was inves...
As part of a continuing effort at the Lewis Research Center to improve performance, emissions, and r...
Vaporization data that could be useful in designing premixed-prevaporized fuel preparation systems f...
Two short turbojet combustors designed for use with vaporized hydrocarbon fuels were tested in a one...
Performance investigations were conducted on a combustor utilizing several cost-reducing innovations...
Combustion efficiencies obtained with gaseous methane were compared with reported data obtained with...