Traditionally the electric power-net is supplied with energy by one generator connected via a gearbox with the turbine high-pressure-shaft (HP-shaft). Due to increasing electric power requirements, especially in More-Electric-Aircraft (MEA) applications, topologies with two generators per turbine engine are under research. One possibility, which will be further observed in this paper, is the addition of a second generator to the low-pressure-shaft (LP-shaft) of the engine. By replacing the generator on the HP-shaft by a starter-generator it is furthermore possible to start the engine electrically. These two generators are feeding a single 270 VDC power-net, which requires new control strategies of the generators to ensure a stable voltage in the power-net. The new degree of freedom by dividing the power generation can be used to optimize the engine's efficiency.In this paper it is demonstrated that a stable voltage in a two-generator-power-net can be achieved. Therefore five different control strategies are developed and implemented, by first deriving the transfer functions of the generator and starter-generator and then designing the controller. For verification purposes the power net is modelled in MatLab / Simulink and load steps are simulated. The next step is the validation of the results on a hardware-in-the-loop test bench, which is being built up at the laboratory of the Institute for Electrical Drives and Actuators at the Universität der Bundeswehr Munich. After that the validation of the two-generator-power-net further energy sources will be added to the power-net like a fuel-cell APU. Control strategies will be developed for these power-nets and verified via simulation and finally validated on a HIL-test-bench.
Control of a two-generator-power-net in more electric aircraft engine
2013
10 Seiten, 10 Bilder, 13 Quellen
Conference paper
Storage medium
English
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