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Main aspects of kerosene and gaseous fuel ignition in aero-engine

Part of: ISABE 2017

Published online by Cambridge University Press:  06 December 2017

O. Antoshkiv ,
Th. Poojitganont ,
L. Jehring  and
C. Berkholz
O. Antoshkiv*
Affiliation:
BTU Cottbus - Senftenberg, Flight Propulsion, Cottbus, Germany
Th. Poojitganont
Affiliation:
BTU Cottbus - Senftenberg, Flight Propulsion, Cottbus, Germany
L. Jehring
Affiliation:
BTU Cottbus - Senftenberg, Flight Propulsion, Cottbus, Germany
C. Berkholz
Affiliation:
BTU Cottbus - Senftenberg, Flight Propulsion, Cottbus, Germany
*
Oleksiy.Antoshkiv@b-tu.de
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Abstract

Various liquid and gaseous alternative fuels have been proposed to replace the kerosene as aircraft fuel. Furthermore, new combustion technologies were developed to reduce the emissions of aero-engine. A staged fuel injection arrangement for a lean burn combustion system was applied to improve the operability of an aero-engine by achieving high flame stability at reduced combustion emissions. Originally, both circuits (pilot and main) are fuelled by kerosene; moreover, the pilot injector is operating at low power (engine idle and approach) and the pilot flame is anchored in an airflow recirculation zone. In the case of the performed research, the pilot injector was modified to allow the use of gaseous fuels. Thus, the burner model allows a flexible balancing of the mass flows for gaseous and liquid fuel. The present paper describes the investigation of ignitability for the proposed staged combustor model fuelled by gaseous and liquid fuels. A short overview on physical properties of used fuels is given. To investigate atomisation and ignition, different measurements systems were used. The effectiveness of two ignitor types (spark plug and laser ignitor) was analysed. The ignition performance of the combustor operating on various fuels was compared and discussed in detail.

Keywords

Alternative Aviation FuelsIgnitionFuel GasStaged Fuel Injection
Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1246 , December 2017 , pp. 1779 - 1794
Copyright
Copyright © Royal Aeronautical Society 2017 

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Footnotes

A version of this paper was presented at the ISABE 2017 Conference, 3-8 September 2017, Manchester, UK.

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