Boundary Layer Ingestion (BLI) has the potential to offer significantly reduced fuel burn, but the fan stage must be designed to run efficiently with severe inlet distortion. In addition, it must also be able to withstand unsteady aerodynamic loads resulting from a non-uniform flowfield. In a multidisciplinary turbomachinery design cycle involving such a complicated flowfield, a large number of flow solutions are sought to interact iteratively or concurrently with various objectives and constraints from other disciplines. This necessitates the rapid high fidelity numerical solutions that accurately predict aerodynamic performance and aeromechanic response of a fan stage. Two Unsteady Reynolds Averaged Navier-Stokes (URANS) methods for accurate analysis of a Tail Cone Thruster (TCT) transonic fan stage subjected to inlet distortion have been used. They are the frequency domain based Non-Linear Harmonic (NLH) and full-annulus complete time domain based time-marching methods. It is shown that the relevant parameters required in effectively computing aerodynamic performance of a fan stage in distorted conditions can be accurately modelled with a few harmonics using the NLH method in a fraction of time compared to the time-marching method. However, the complete aerodynamics of distortion transfer across different blade rows of a fan stage can only be analyzed using a time marching solution. A study of fan response to different inlet distortion profiles is also presented including their effects on fan performance. These analyses aid in accurate and quick design solutions for further BLI fan investigations.


Unsteady Methods to Investigate Inlet Distortion in a Transonic Tail Cone Thruster Fan Stage With Boundary Layer Ingestion

Division / Sponsor:
International Gas Turbine Institute (IGTI)

Paper Proceedings: https://asmedigitalcollection.asme.org/GT/GT2020/volume/84058

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