Engine Pylon Topology Optimization Framework Based on Performance and Stress Criteria

Abstract : Reducing fuel consumption is a major driver for the design of future aircraft. The engine integration primary structure plays a significant role in the integrated engine thrust-specific fuel consumption. A topology optimization framework was developed to design the primary structure integrating the engine to the aircraft wing considering mass, stress, and engine performance criteria. The proposed approach had to address several challenges associated with the use of nonuniform meshes, the integration of the engine model as a super-element, and the presence of nonconforming mesh interfaces. Analytical adjoint evaluations for all the responses were also derived. The framework was tested on a simplified engine model providing a consistent solution. Nomenclature DOF = degrees of freedom F c = engine retained DOFs condensated load vector K cc = engine retained DOFs condensated stiffness matrix l s = sth-stage blade height N s = sth-stage number of angular position R s = sth-stage tip clearance root mean square TSFC = thrust-specific fuel consumption u b r = rotor blade tip radial displacement u c r = casing radial displacement K = stiffness matrix P = engine recovery matrix fFg = load vector frθg = radial unit vector at the angle θ fUg = displacement vector ΔTSFC% = TSFC approximative variation induced by mechanical load δ 0 = initial tip clearance θ = angular position around the engine stage fδ s g = sth-stage tip clearance variation vector
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Contributor : Simone Coniglio <>
Submitted on : Tuesday, October 1, 2019 - 5:36:47 PM
Last modification on : Tuesday, November 19, 2019 - 2:10:38 AM



Simone Coniglio, Christian Gogu, Rémi Amargier, Joseph Morlier. Engine Pylon Topology Optimization Framework Based on Performance and Stress Criteria. AIAA Journal, American Institute of Aeronautics and Astronautics, 2019, pp.1-13. ⟨10.2514/1.J058117⟩. ⟨hal-02302631⟩



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