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  • 1.
    Lejon, Marcus
    et al.
    Chalmers University of Technology, Sweden.
    Gronstedt, Tomas
    Chalmers University of Technology, Sweden.
    Glodic, Nenad
    KTH Royal Institute of Technology, Sweden.
    Petrie-Repar, Paul
    KTH Royal Institute of Technology, Sweden.
    Genrup, Magnus
    Lund University, Sweden.
    Mann, Alexander
    RISE - Research Institutes of Sweden, Swerea, Swerea IVF.
    Multidisciplinary design of a three stage high speed booster2017In: Proceedings of the ASME Turbo Expo, Vol. 2B-2017Article in journal (Refereed)
    Abstract [en]

    The paper describes a multidisciplinary conceptual design of an axial compressor, targeting a three stage, high speed, high efficiency booster with a design pressure ratio of 2.8. The paper is outlined in a step wise manner starting from basic aircraft and engine thrust requirements, establishing the definition of the high speed booster interface points and its location in the engine. Thereafter, the aerodynamic 1D/2D design is carried out using the commercial throughflow tool SC90C. A number of design aspects are described, and the steps necessary to arrive at the final design are outlined. The SC90C based design is then carried over to a CFD based conceptual design tool AxCent, in which a first profiling is carried out based on a multiple circular arc blade definition. The design obtained at this point is referred to as the VINK compressor. The first stage of the compressor is then optimized using an in-house optimization tool, where the objective functions are evaluated from detailed CFD calculations. The design is improved in terms of efficiency and in terms of meeting the design criteria put on the stage in the earlier design phases. Finally, some aeromechanical design aspects of the first stage are considered. The geometry and inlet boundary conditions of the compressor are shared with the turbomachinery community on a public server. This is intended to be used as a test case for further optimization and analysis. 

  • 2.
    Olsson, Robin
    et al.
    RISE - Research Institutes of Sweden, Materials and Production, SICOMP.
    Block, Tim
    University of Bremen, Germany.
    Criteria for skin rupture and core shear cracking during impact on sandwich panels2013In: Proc. 19th Int. Conf. on Composite Materials (ICCM-19). Montreal, Canada., 2013, p. 3638-3645Conference paper (Refereed)
    Abstract [en]

    Core shear cracking induced by impact on sandwich panels is a detrimental failure mode causing severe loss of structural performance. This paper derives analytical expressions for initiation of skin rupture and core shear cracking during impact on sandwich panels with foam cores. The criteria are successfully validated by comparison with experimental results for a range of thicknesses of skins and cores in panels with carbon/epoxy NCF skins and a Rohacell foam core.

  • 3.
    Olsson, Robin
    et al.
    RISE, Swerea, SICOMP.
    Juntikka, Rickard
    RISE, Swerea, SICOMP.
    Validation of analytical model for hail impact on composite laminates2010In: Proc. 14th European Conf. on Composite Materials (ECCM 14)., European Society for Composite Materials , 2010, article id Paper 137Conference paper (Refereed)
    Abstract [en]

    This paper examines analytical models for hail impact on composite laminates and compares the predictions with finite element simulations and experiments. The crushing of the ice results in a distributed load and a much higher delamination threshold load than for impact by hard objects. Furthermore, prediction of the impact load by merely considering the mass flow of ice particles results in too low loads and a response in disagreement with experiments. The pressure acting on the impacted plate is fairly uniform within the contact area, but initial through-thickness waves during the first moments of the impact cause much higher stresses than the quasi-static values assumed in the analytical models. Hence the finite element models predict a different load history, with a much steeper initial increase in the contact load.

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