A new LPP injector concept for aero engines is presented. The design target was to achieve a fine atomization in order to get a high degree of prevaporization. Inside the injector atomization and mixture homogenization are spatially separated allowing for an individual optimization. The injector was operated in an optical accessible single sector combustor at elevated pressures. The reacting two phase flow was investigated by means of Laser Doppler Anemometry (LDA), Phase Doppler Anemometry (PDA), visualisation of OH* chemiluminescence, kerosene LIF and Mie scattering and OH LIF. The spatially and temporally resolved temperature distribution was calculated from the OH LIF images. The influence of the air preheat temperature on emissions was examined by applying conventional exhaust gas analysis. The results of the optical measurement techniques were used for an analysis of the reacting flow field and for the interpretation of the influence of the preheat temperature.
Experimental Investigation of a New LPP Injector Concept for Aero Engines at Elevated Pressures
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Behrendt, T, Heinze, J, & Hassa, C. "Experimental Investigation of a New LPP Injector Concept for Aero Engines at Elevated Pressures." Proceedings of the ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. Volume 2: Turbo Expo 2003. Atlanta, Georgia, USA. June 16–19, 2003. pp. 377-386. ASME. https://doi.org/10.1115/GT2003-38444
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