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Automated Aerodynamic Optimization of an Aggressive S-Shaped Intermediate Compressor Duct
German Aerospace Center DLR, Cologne, Germany.
German Aerospace Center DLR, Cologne, Germany.
German Aerospace Center DLR, Cologne, Germany.
MTU Aero Engines AG, Munich, Germany.
Vise andre og tillknytning
2018 (engelsk)Inngår i: ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition: Volume 2D: Turbomachinery, ASME International , 2018, s. GT2018-75184, V0-2DT46A002Konferansepaper, Publicerat paper (Fagfellevurdert)
Abstract [en]

As bypass-ratio in modern aero engines is continuously increasing over the last decades, the radial offset between low pressure compressor (LPC) and high pressure compressor (HPC), which needs to be overcome by the connecting s-shaped intermediate compressor duct (ICD), is getting higher. Due to performance and weight saving aspects the design of shorter and therefore more aggressive ducts has become an important research topic. In this paper an already aggressive design (with respect to current aero engines) of an ICD with integrated outlet guide vane (OGV) is used as a baseline for an aerodynamic optimization. The aim is to shorten the duct even further while maintaining it separation free. The optimization is broken down into two steps. In the first optimization-step the baseline design is shortened to a feasible extent while keeping weak aerodynamic restrictions. The resulting highly aggressive duct (intermediate design), which is shortened by 19 % in axial length with respect to the baseline, shows separation tendencies of low momentum fluid in the strut/hub region. For the second step, the length of the optimized duct design is frozen. By implementing new design features in the process of the optimizer, this optimization-step aims to eliminate separation and to reduce separation tendencies caused by the aggressive shortening. In particular, these features are: a nonaxisymmetric endwall contouring and parametrization of the strut and the OGV to allow for changes in lift and turning in both blade designs. By comparison of the three designs: Baseline, intermediate (separating flow) and final design, it can be shown, that it is possible to decrease length of the already aggressive baseline design even further, when adding a nonaxisymmetric endwall contouring and changes in blade shape of the strut and OGV. Flow separation can be eliminated while losses are kept low. With a more aggressive and therefore shorter duct the engine length and weight can be reduced. This in turn leads to lighter aircrafts, less fuel consumption and lower CO2 and NOx emissions.

sted, utgiver, år, opplag, sider
ASME International , 2018. s. GT2018-75184, V0-2DT46A002
HSV kategori
Identifikatorer
URN: urn:nbn:se:kth:diva-306901DOI: 10.1115/GT2018-75184OAI: oai:DiVA.org:kth-306901DiVA, id: diva2:1624298
Konferanse
ASME Turbo Expo 2018, June 11–15, 2018 Oslo, Norway
Merknad

QC 20220125

Part of proceedings: ISBN 978-0-7918-5102-9

Tilgjengelig fra: 2022-01-03 Laget: 2022-01-03 Sist oppdatert: 2022-06-25bibliografisk kontrollert

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Totalt: 136 treff
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