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Potential of surrogate modelling in compressor casing design focussing on rapid tip clearance assessments

Published online by Cambridge University Press:  13 September 2021

T. Schmidt Open the ORCID record for T. Schmidt [Opens in a new window] ,
V. Gümmer  and
M. Konle
T. Schmidt*
Affiliation:
Technische Universität München Institute for Turbomachinery and Flight Propulsion 85748 Garching Germany
V. Gümmer
Affiliation:
Technische Universität München Institute for Turbomachinery and Flight Propulsion 85748 Garching Germany
M. Konle
Affiliation:
MTU Aero Engines AG 80995 München Germany
*
[email protected]
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Abstract

Losses induced by tip clearance limit decisive improvements in the system efficiency and aerodynamic operational stability of aero-engine axial compressors. The tendency towards even lower blade heights to compensate for higher fluid densities aggravates their influence. Generally, it is emphasised that the tip clearance should be minimised but remain large enough to prevent collisions between the blade tip and the casing throughout the entire mission. The present work concentrates on the development of a preliminary aero-engine axial compressor casing design methodology involving meta-modelling techniques. Previous research work at the Institute for Turbomachinery and Flight Propulsion resulted in a Two-Dimensional (2D) axisymmetric finite element model for a generic multi-stage high-pressure axial compressor casing. Subsequent sensitivity studies led to the identification of significant parameters that are important for fine-tuning the tip clearance via specific flange design. This work is devoted to an exploration of the potential of surrogate modelling in preliminary compressor casing design with respect to rapid tip clearance assessments and its corresponding precision in comparison with finite element results. Reputed as data-driven mathematical approximation models and conceived for inexpensive numerical simulation result reproduction, surrogate models show even greater capacity when linked with extensive design space exploration and optimisation algorithms.

Compared with high-fidelity finite element simulations, the reductions obtained in computational time when using surrogate models amount to 99.9%. Validated via statistical methods and dependent on the size of the training database, the precision of surrogate models can reach down to the range of manufacturing tolerances. Subsequent inclusion of such surrogate models in a parametric optimisation process for tip clearance minimisation rapidly returned adaptions of the geometric design variables.

Keywords

Surrogate modellingCompressor casing designFinite element method
Type
Research Article
Information
The Aeronautical Journal , Volume 125 , Issue 1291: The 25th ISABE Conference Special Issue – Part I , September 2021 , pp. 1587 - 1610
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Copyright
© The Author(s), 2021. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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