TY - CHAP A1 - Grasselt, David A1 - Höschler, Klaus A1 - Sain, Chetan Kumar T1 - Fluid-Structure Interaction With a Fully Integrated Multiphysics Environment T2 - Proceedings of the ASME Fluids Engineering Division Summer Meeting - 2017, presented at the ASME 2017 Fluids Engineering Division Summer Meeting, July 30-August 3, 2017, Waikoloa, Hawaii, USA, Volume 1B N2 - The paper is focusing on Fluid-Structure Interaction (FSI) process modelling to look for the aero-elastic equilibrium with commercial software packages. The center of intention is to prove whether Ansys Workbench is capable to handle industrial size FSI applications on the one side and to identify possible excitation regions in the example case on the other. The three steps taken to come to a thermal-enhanced bidirectional fluid-structure approach within a fully integrated (monolithic) multiphysics environment are explained: aerodynamic assessment, thermo-structure mechanical setup and unidirectional coupling, as well as bidirectional coupling. Each subchapter describes the specific challenges, how they are solved and which results can be obtained or expected. The paper is focusing on the setup of a bidirectional process chain and does not set the thematic priority on detailed modelling and its results. Y1 - 2017 SN - 978-0-7918-5805-9 U6 - https://doi.org/10.1115/FEDSM2017-69078 PB - ASME CY - New York, NY ER - TY - GEN A1 - Grasselt, David A1 - Höschler, Klaus A1 - Kazula, Stefan T1 - A Design Approach for a Coupled Actuator System for Variable Nozzles and Thrust Reverser of Aero Engines T2 - Proceedings of ISABE 2017, ISABE-2017-21450, Manchester, September 3.-8., 2017 Y1 - 2017 UR - https://isabe2017.org/ UR - https://drive.google.com/uc?id=0B0DfCIh2pyLOeXVtazZBcUFEcVE&export=download SP - 11 PB - ISABE ER - TY - GEN A1 - Kazula, Stefan A1 - Grasselt, David A1 - Mischke, Marcel A1 - Höschler, Klaus T1 - Preliminary safety assessment of circular variable nacelle inlet concepts for aero engines in civil aviation T2 - Safety and Reliability – Safe Societies in a Changing World N2 - A safe design process and its application are introduced to a concept study for circular variable aero engine inlets. The paper highlights the tasks of inlets, the compromise in designing them and how using variable inlets could solve this compromise and allow for faster and more efficient commercial aircraft. However, high safety and reliability requirements bring up disadvantages. Tackling these disadvantages, a systems engineering approach is complemented by a safety assessment process, according to Aerospace Recommended Practice ARP 4754A. Safety methods that are applicable during early phases of the product development process are presented and applied to develop feasible variable inlet concepts. Hence, safety requirements, potential failure events and resulting failure modes are systematically identified, assessed and mitigated. The mitigation of a failure condition by the means of redundancy within the adjustment control system is presented. KW - Preliminary System Safety Assessment KW - Fault Tree Analysis KW - Variable Aero Engine Intake Y1 - 2018 UR - https://www.taylorfrancis.com/books/e/9781351174657/chapters/10.1201%2F9781351174664-309 SN - 978-0-8153-8682-7 SP - 2459 EP - 2467 PB - Taylor & Francis Group CY - London ER - TY - GEN A1 - Kazula, Stefan A1 - Wöllner, Mark A1 - Grasselt, David A1 - Höschler, Klaus T1 - Parametric Design Study on Aerodynamic Characteristics of Variable Pitot Inlets for Transonic and Supersonic Civil Aviation T2 - MATEC Web of Conferences : Proceedings of the 9th EASN International Conference on Innovation in Aviation & Space N2 - This paper reveals the influence of selected geometric parameters on the aerodynamic performance of circular variable aero engine inlets in transonic and supersonic civil aviation. The trade-off in inlet design and aerodynamic evaluation parameters are presented. The approach to investigate the dependencies between the aerodynamic and geometric parameters at different flight conditions by means of a parametric design study is introduced. The dependencies of inlet drag and efficiency from geometric parameters at flight speeds of Mach 0.95 up to Mach 1.6 are identified. Although entailing additional weight, the inlet length represents the parameter with the highest potential for drag reduction by up to 50% in the selected design space. Ideal geometries for variable pitot inlets are determined. After considering weight, their potential range benefit nearly disappears for subsonic applications, but remains above 20% for supersonic flight at Mach 1.6. Y1 - 2019 U6 - https://doi.org/10.1051/matecconf/201930402017 SN - 2261-236X VL - 304 ER - TY - CHAP A1 - Kazula, Stefan A1 - Grasselt, David A1 - Höschler, Klaus ED - Silva Gomes, J. F. ED - Meguid, Shaker A. T1 - Common cause analysis of circular variable nacelle inlet concepts for aero engines in civil aviation T2 - Proceedings IRF2018: 6th International Conference Integrity-Reliability-Failure, Lisbon/Portugal, 22-26 July 2018 N2 - This paper presents the application of a safe design process within a concept study for variable aero engine inlets. The safety assessment method Common Cause Analysis (CCA), consisting of a Zonal Safety Analysis (ZSA), a Particular Risk Analysis (PRA) and a Common Mode Analysis (CMA), is performed on variable inlet concepts. By the means of the CCA individual failure modes and external events, which can lead to failure conditions, are identified. Potential design adaptations to mitigate these failure conditions are presented. KW - variable aero engine inlets KW - coupled design and safety process KW - safety and reliability KW - safety assessment methods Y1 - 2018 UR - https://paginas.fe.up.pt/~irf/Proceedings_IRF2018/data/papers/7148.pdf SN - 978-989-20-8313-1 SP - 759 EP - 770 PB - INEGI/FEUP CY - Lisbon ER - TY - CHAP A1 - Grasselt, David A1 - Höschler, Klaus T1 - Safety Assessment of Aero Engine Thrust Reverser Actuation Systems : ISABE-2015-20260 T2 - 22nd International Symposium on Air Breathing Engines (ISABE-2015-20260), 25.-30. Oktober 2015, Phoenix (AZ, USA) Y1 - 2015 UR - http://hdl.handle.net/2374.UC/745815 PB - ISABE ER - TY - CHAP A1 - Grasselt, David A1 - Höschler, Klaus T1 - Vergleich von FSI Methoden kommerzieller integrativer Programme gegenüber inkonsistenten Lösungen am Beispiel eines Schubumkehrers im Flug-Triebwerk T2 - Deutscher Luft- und Raumfahrtkongress 2015, 22. -24. September 2015, Rostock KW - FSI Methoden KW - Schubumkehrers Y1 - 2015 U6 - http://nbn-resolving.de/urn/resolver.pl?urn:nbn:de:101:1-201512113094 PB - Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V. CY - Bonn ER - TY - CHAP A1 - Grasselt, David A1 - Höschler, Klaus A1 - Konstantinidis, Aris T1 - Fluid Structure Interaction with Inconsistent Software Platforms T2 - ECCOMAS, Barcelona 2014 N2 - The FSI problem class describes the mutual dependence of the multiphysical interaction between aerodynamic forces and structural mechanic deformation. The FSI effects become more significant and influences partially safety analysis when the dependence between the influence and response becomes stronger, e.g. the fluttering of aero-engine blades or the pumping of blood by the ventricles of the human heart. [1] The modelling of fluid dynamic problems requires solutions different from those, which are relevant for structure mechanical issues. The coupling of modern numerical methods and tools enables the analysis of mutual dependencies. Although software companies develop more and more integrated solutions, inconsistent application of software solutions (SW) play an important role. Furthermore, automation of interface processing, finite-element analysis (FEA) and computational fluid dynamic (CFD) solution processes can lead to significant exploitation potential for example for design-optimisation applications, design evaluation with target solver-, Monte Carlo-, six sigma-, Taguchi- and stochastic design improval methods or is capable to just accelerate the design process. This requires the strict separation of method code and application dependent information. The paper describes a coupling approach, in the case of obligatory use of inconsistent SW for the separate, mutual depending challenges of a FSI problem description, especially for strong displacement applications. The first step of a FSI process chain is the solution of a fluid dynamic problem followed by a coupled FE Analysis. The start of the FE solution process can be divided into three steps: • the pre-processing and generation of a finite-element-model input file, • the manipulation with an external code, including the required time and data management, • the execution of the FEM solver with the manipulated input file. Typical finite-element-codes generate an input file and process this file with a SW specific interface. A self-coded Java programme uses this interface strategy to manipulate the structural solvers’ input before executing the solver. The outcome of the FE solution can be divided into two types of information. The most obvious is numerical output in form of stress or displacement. Additionally FSI process relevant information is required to allow the coupling of FEA to the CFD analysis: boundary conditions, like surface pressure or heat transfer coefficients distributions provoked deformation of the component. A key method to allow importing deformed surfaces to form the 2nd coupling way is the description of surfaces using non-uniform rational B-splines. KW - Fluid Structure Interaction (FSI), Multiphysics Problems, Applications, Computing Methods, inconsistent Software Platforms Y1 - 2014 UR - http://www.wccm-eccm-ecfd2014.org/admin/files/fileabstract/a4345.pdf ER - TY - GEN A1 - Kazula, Stefan A1 - Wöllner, Mark A1 - Grasselt, David A1 - Höschler, Klaus T1 - Ideal Geometries and Potential Benefit of Variable Pitot Inlets for Subsonic and Supersonic Business Aviation T2 - 8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) N2 - The challenge of determining ideal inlet geometries for variable pitot aero engine inlets in transonic and supersonic civil aviation is presented. The trade-off in inlet design and the geometric inlet parameters are introduced. By means of a parametric design study, feasible inlet geometries for variable inlets are identified and the potential aerodynamic benefit of using variable pitot inlets for flight speeds from Mach 0.95, 1.3 up to 1.6 is examined. After considering the additional weight of variable inlets, for instance due to required actuators, a remaining range benefit of over 20% at a flight speed of Mach 1.6 is determined. Y1 - 2019 UR - https://eucass.eu/index.php/component/docindexer/?task=download&id=5871 U6 - https://doi.org/10.13009/EUCASS2019-314 ER - TY - GEN A1 - Kazula, Stefan A1 - Wöllner, Mark A1 - Grasselt, David A1 - Höschler, Klaus T1 - Parametric design and aerodynamic analysis of circular variable aero engine inlets for transonic and supersonic civil aviation T2 - Proceedings of the 24th ISABE Conference : ISABE 2019-24018 N2 - This paper focusses on the challenge of determining the ideal inlet geometries within a concept study for variable pitot aero engine inlets in transonic and supersonic civil aviation. The trade-off in inlet design and the geometric parameters of inlets for different Mach numbers are introduced. The utilised process of the parametric design study and its implementation are presented. The dependencies of inlet drag and occurrence of flow separation from geometric parameters are examined. The ideal inlet geometries are identified to determine the potential aerodynamic benefit of using variable pitot inlets. The comparison of the identified geometries with the reference reveals a significant drag reduction at the investigated flight speeds of Mach 0.95, 1.3 and 1.6. While the drag reduction potentially leads to decreased fuel consumption and increased flight range, the application of variable inlet systems entails additional weight and complexity. By means of a simplified Breguet range equation, the benefit of using variable pitot inlets has been determined. For an additional weight of 500 kg per variable inlet, the range benefit nearly disappears for subsonic applications up to Mach 0.95, while a range benefit of over 20% remains for supersonic applications at Mach 1.6. KW - benefit of supersonic variable axisymmetric pitot inlets KW - parametric design study KW - response surface optimisation KW - pitot inlet drag estimation KW - ideal aircraft intake geometries Y1 - 2019 UR - https://drive.google.com/drive/folders/1PZaMaLOLsybB3KFLmvP8hwM_lwmk3e4B CY - Canberra ER -