Performance Analysis of the Integrated V2527-Engine Fan at Ground Operation

Abstract

The paper focuses on the holistic assessment of the integrated fan stage of DLRs Advanced Technology Research Aircraft ATRA, an Airbus A320 equipped with two IAE-V2527 engines. For the entire engine and all its components, a cycle model was established in order to derive realistic operating conditions for all components. The model was validated against experimental data taken by the Electronic Engine Control (EEC) at the aircrafts last shop visit at Lufthansa Technik. Furthermore the engines nacelle and major fan components including its disk, casing, Outlet Guide Vanes (OGV) and Booster-Inlet Guide Vanes (IGV) etc. were optically scanned and transferred to surfaced based CAD models in a reverse engineering approach to obtain the geometry in a most accurate manner. This allowed for dedicated CFD studies of the fan itself and by including the nacelle its interaction with ground induced inlet distortions at realistic engine operating conditions as being derived from the cycle analysis. A mechanical model of the hollow, honeycomb structured fan blade was set up based on the information from computer tomography (CT) scans of one blade and corresponding experimental determination of the blades Eigen-Frequencies. This model allowed for the cold-to-hot transformation of the fan blade geometry under running conditions. The updated CFD results in terms of stage performance with the realistic deformed geometry will then be used to update the cycle model in an iterative manner. Furthermore, a parametric study characterizing the fan inlet flow at the nacelle entry at varying boundary conditions (e.g. cross flows, different fan mass flow rates etc.) was carried out, allowing to quantify the nacelle induced inlet distortions potentially influencing the fan performance.