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Optimizing a Boundary-Layer-Ingestion Offset Inlet by Discrete Adjoint Approach

Cited 11 time in Web of Science Cited 25 time in Scopus
Authors
Lee, Byung Joon; Liou, Mena-Sing; Kim, Chongam
Issue Date
2010-09
Publisher
American Institute of Aeronautics and Astronautics
Citation
AIAA JOURNAL Vol.48 No.9, pp. 2008-2016
Keywords
복합학
Abstract
A large amount of low-momentum boundary-layer flow ingesting into a flush-mounted inlet can cause significant total pressure loss and distortion to the extent beyond operability of a fan/compressor. To improve the quality of incoming flow into the engine, shape optimization of the surface geometry at the inlet entrance has been carried out using the discrete adjoint method; the inlet-floor shape is parameterized by the use of control points on B-spline surface patches. To resolve the complicated geometry flexibly and wall-bounded turbulent flow accurately, an overset mesh system is well-suited for integrating the flow analysis code, sensitivity analysis code, and grid modification tools. To enhance the convergence characteristics of the sensitivity analysis code, additional numerical dissipation for the discrete adjoint formulation is introduced. After using this optimization procedure, the new inlet yields a significant improvement in performance: a more than 50% reduction in flow distortion kind a 3% increase in total pressure recovery. High performance at off-design conditions is also realized with only slight degradation, confirming the capability of the adjoin( method for a practical design problem. Finally, the physical meaning and implication of the performance improvement are elaborated upon in relation to the flow characteristics resulting from the new design.
ISSN
0001-1452
Language
English
URI
http://hdl.handle.net/10371/82302
DOI
https://doi.org/10.2514/1.J050222
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College of Engineering/Engineering Practice School (공과대학/대학원)Dept. of Mechanical Aerospace Engineering (기계항공공학부)Journal Papers (저널논문_기계항공공학부)
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