Abstract
This paper explains concepts of aircraft engine afterburner, and describes history of afterburner study, and describe the result of major research items. An afterburner is located down stream of a fan, compressor, burner, and turbine in a jet engine. Its basic principle is that fuel is injected into turbine exhaust and fan air flows from an fuel injector, ignited by a spark plug using oxygen remaining in the exhaust gas flow, burned and flame-held by a flame stabilizer. The combustion gas of high temperature (1,700 to 1,800 {degree}c) thus generated is jetted out from an exhaust nozzle to increase the thrust. The prototype afterburner is featured by adoption of a mixed type fuel injection system that provides wide stable combustion range, and flame stabilizer with a scoop aimed at improving the ignition performance and combustion efficiency. A confirmation test verified smooth ignition and wide air to fuel ratio for stabilized combustion. 4 refs., 16 figs.
Kashiwagi, T
[1]
- Ishikawajima-Harima Heavy Industries, Co. Ltd., Tokyo (Japan)
Citation Formats
Kashiwagi, T.
Study on afterburner of aircraft engine. Koku engine yo afterburner no kenkyu.
Japan: N. p.,
1991.
Web.
Kashiwagi, T.
Study on afterburner of aircraft engine. Koku engine yo afterburner no kenkyu.
Japan.
Kashiwagi, T.
1991.
"Study on afterburner of aircraft engine. Koku engine yo afterburner no kenkyu."
Japan.
@misc{etde_5280664,
title = {Study on afterburner of aircraft engine. Koku engine yo afterburner no kenkyu}
author = {Kashiwagi, T}
abstractNote = {This paper explains concepts of aircraft engine afterburner, and describes history of afterburner study, and describe the result of major research items. An afterburner is located down stream of a fan, compressor, burner, and turbine in a jet engine. Its basic principle is that fuel is injected into turbine exhaust and fan air flows from an fuel injector, ignited by a spark plug using oxygen remaining in the exhaust gas flow, burned and flame-held by a flame stabilizer. The combustion gas of high temperature (1,700 to 1,800 {degree}c) thus generated is jetted out from an exhaust nozzle to increase the thrust. The prototype afterburner is featured by adoption of a mixed type fuel injection system that provides wide stable combustion range, and flame stabilizer with a scoop aimed at improving the ignition performance and combustion efficiency. A confirmation test verified smooth ignition and wide air to fuel ratio for stabilized combustion. 4 refs., 16 figs.}
journal = []
volume = {31:2}
journal type = {AC}
place = {Japan}
year = {1991}
month = {Mar}
}
title = {Study on afterburner of aircraft engine. Koku engine yo afterburner no kenkyu}
author = {Kashiwagi, T}
abstractNote = {This paper explains concepts of aircraft engine afterburner, and describes history of afterburner study, and describe the result of major research items. An afterburner is located down stream of a fan, compressor, burner, and turbine in a jet engine. Its basic principle is that fuel is injected into turbine exhaust and fan air flows from an fuel injector, ignited by a spark plug using oxygen remaining in the exhaust gas flow, burned and flame-held by a flame stabilizer. The combustion gas of high temperature (1,700 to 1,800 {degree}c) thus generated is jetted out from an exhaust nozzle to increase the thrust. The prototype afterburner is featured by adoption of a mixed type fuel injection system that provides wide stable combustion range, and flame stabilizer with a scoop aimed at improving the ignition performance and combustion efficiency. A confirmation test verified smooth ignition and wide air to fuel ratio for stabilized combustion. 4 refs., 16 figs.}
journal = []
volume = {31:2}
journal type = {AC}
place = {Japan}
year = {1991}
month = {Mar}
}