TY - CHAP

T1 - Experimental Validation of an Optimized Design Process for Transonic Mixed-Flow Compressors

AU - Maroldt, Niklas

AU - Kauth, Felix

AU - Seume, Joerg R.

N1 - Funding Information: Acknowledgements The authors would like to thank the German Research Foundation (DFG) for supporting this fundamental research in active high-lift systems for future aircraft as part of the Collaborative Research Centre 880 (Sonderforschungsbereich SFB 880). Moreover, the authors thank Malte Nyhuis for his outstanding commitment when supporting the post-test calculations.

PY - 2021

Y1 - 2021

N2 - A novel active high-lift system for future commercial aircraft uses electrically driven compressors to provide the required jet momentum for steady blowing over a Coanda flap. This application necessitates high total pressure ratios and high flow rates. A newly developed aeromechanical optimization approach was applied to fulfill these requirements under the given constraints. The optimization resulted in an mixed-flow compressor design featuring a transonic flow regime. A prototype of this compressor stage was designed and manufactured. In this paper, the optimization process is extended to account for the requirements of the electrical components of the compressor system. The compressor performance of the prototype at rotational speeds up to the design speed of 60,000 rpm is measured. A sensitivity study and post-test calculations using Computational Fluid Dynamics are performed. To correct for the influence of leakage flow within the design optimization process, a simple speed-dependent penalty function is implemented. The results confirm the design calculations at points with sufficient surge margin.

AB - A novel active high-lift system for future commercial aircraft uses electrically driven compressors to provide the required jet momentum for steady blowing over a Coanda flap. This application necessitates high total pressure ratios and high flow rates. A newly developed aeromechanical optimization approach was applied to fulfill these requirements under the given constraints. The optimization resulted in an mixed-flow compressor design featuring a transonic flow regime. A prototype of this compressor stage was designed and manufactured. In this paper, the optimization process is extended to account for the requirements of the electrical components of the compressor system. The compressor performance of the prototype at rotational speeds up to the design speed of 60,000 rpm is measured. A sensitivity study and post-test calculations using Computational Fluid Dynamics are performed. To correct for the influence of leakage flow within the design optimization process, a simple speed-dependent penalty function is implemented. The results confirm the design calculations at points with sufficient surge margin.

KW - Active high-lift system

KW - Future aircraft

KW - Multi-disciplinary optimization

KW - Transonic mixed-flow compressor

UR - http://www.scopus.com/inward/record.url?scp=85093854525&partnerID=8YFLogxK

U2 - 10.1007/978-3-030-52429-6_36

DO - 10.1007/978-3-030-52429-6_36

M3 - Contribution to book/anthology

AN - SCOPUS:85093854525

SN - 978-3-030-52428-9

T3 - Notes on Numerical Fluid Mechanics and Multidisciplinary Design

SP - 597

EP - 613

BT - Fundamentals of High Lift for Future Civil Aircraft

PB - Springer Science and Business Media Deutschland GmbH

CY - Cham

ER -