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Numerical Analysis of Unsteady Compressor Performance Under Boundary Conditions Caused by Pulsed Detonation Combustion
Citation key 2022_neumann_n_springerafcc
Author Neumann, N. and Rähse, T. and Stathopoulos, P. and Peitsch, D.
Title of Book Active Flow and Combustion Control 2021
Pages 272–287
Year 2022
ISBN 978-3-030-90727-3
ISSN 1612-2909
DOI 10.1007/978-3-030-90727-3_17
Location Switzerland
Address Cham
Volume 152
Note Paper Contributed to the Conference “Active Flow and Combustion Control 2021”, September 28–29, 2021, Berlin, Germany

Technische Universität Berlin:
N. Neumann, T. Rähse, P. Stathopoulos, D. Peitsch
Editor King, Rudibert and Peitsch, Dieter
Publisher Springer International Publishing
Series Notes on Numerical Fluid Mechanics and Multidisciplinary Design
Abstract Pressure gain combustion is a revolutionary concept to increase gas turbine efficiency and thus potentially reduces the environmental footprint of power generation and aviation. Pressure gain combustion can be realized through pulsed detonation combustion. However, this unsteady combustion process has detrimental effects on adjacent turbomachines. This paper identifies realistic time-variant compressor outlet conditions, which could potentially stem from pulsed detonation combustion. Furthermore, a low fidelity approach based on the 1D-Euler method is applied to investigate the performance of a compressor exposed to these outlet boundary conditions. The simulation results indicate that the efficiency penalty due to unsteady compressor operation remains below 1% point. Furthermore, between 80% and 95% of the fluctuations' amplitudes are damped till the inlet of the 4-stage compressor.
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