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 - Mhadbi, Beya A1 - Mischke, Marcel A1 - Höschler, Klaus A1 - Huppertz, André T1 - Semi-automatische Erstellung parametrisch-assoziativer 3D CAD-Modelle am Beispiel eines Flug-Kerntriebwerks T1 - Semi-automated creation of parametric associative 3D CAD models exemplified by a core aero engine T2 - Digitalisierung und Produktentwicklung - vernetzte Entwicklungsumgebungen, 16. Gemeinsames Kolloquium Konstruktionstechnik 2018, Bayreuth, Tagungsband N2 - Zukünftige Produktentwicklungen werden auf multidisziplinäre Optimierungen eines virtuellen Modells basieren, da nur sie die Interaktionen zwischen den beteiligten Disziplinen berücksichtigen. Beabsichtigt man beispielsweise ein Produkt hinsichtlich seiner aerodynamischen, thermodynami-schen und statisch-dynamischen Eigenschaften zu optimieren, ist es erforderlich, die Generierung der virtuellen Produktgeometrie zu automatisieren und die interessierenden Dimensionen, welche für die o.g. Disziplinen relevant sind, zu parametrisieren, d.h. flexibel zu gestalten und eine potenzielle Veränderung der Morphologie bzw. der Abmessungen vorzusehen. Wie eine flexible, für die Optimierung angemessene Geometrie zu erstellen ist, ist Gegenstand des vorliegenden Artikels. Dabei wird gezeigt, wie ein 3D CAD-Modell ausgehend von einer einfachen 2D Referenzgeometrie, welche aus Grundgeometrien besteht, und von generisch, parametrisch-assoziativen Benutzerformelementen (User-Defined Features, UDFs) zu generieren ist. Der methodische Ansatz wird am Beispiel eines Kerntriebwerks konkretisiert. Der vorgestellte Prozess ist ein Schritt in Richtung einer flexiblen Geometrieerstellung, die die Durchführung multidisziplinärer Optimierung ermöglicht. N2 - Future product developments require multidisciplinary optimization of a virtual model, as only multi-disciplinary optimization takes the interactions between several applications into account. For example, if one intends to optimize a product in terms of its aerodynamic, thermodynamic and static-dynamic properties, one will have to automate the product geometry and to parametrize the dimensions, which are relevant to the above mentioned disciplines, i.e. to design flexible geometries and to allow for potential changes in morphology and geometrical dimensions. The present paper deals with how to create a flexible geometry that is appropriate for the optimization. It demonstrates how to generate a 3D CAD model based on the one hand upon a simple 2D reference geometry consisting of geometric primitives, and on the other hand upon generic, parametric-associative user-defined features (UDFs). This design process is then automated and the methodological approach is illustrated with the example of a core aero engine. The presented approach is a step towards the generation of a flexible geometry enabling the implementation of multidisciplinary optimization. KW - Automatisierung KW - Automation KW - Vorauslegungsphase KW - Assoziativität KW - Siemens NX KW - 3D CAD-Modell KW - Parametrisierung KW - UDFs KW - Generisch KW - Preliminary Design Phase KW - Associativity KW - Siemens NX KW - 3D CAD Model KW - Parametrization KW - UDFs KW - Generic Y1 - 2018 UR - https://eref.uni-bayreuth.de/id/eprint/45929 SN - 978-3-00-059609-4 SP - 236 EP - 243 PB - Universität Bayreuth, Lehrstuhl für Konstruktionslehre und CAD CY - Bayreuth ER - TY - GEN A1 - König, Paul A1 - Mischke, Marcel A1 - Pohl, Michael A1 - Kazula, Stefan A1 - Höschler, Klaus T1 - Concept Development and Evaluation for a Broadband Noise Absorbing Acoustic Liner Concept for Aviation T2 - 24th International Society For Air Breathing Engines (ISABE-2019-24261), 22.-27. September 2019 N2 - This paper presents design adaptations during the further development of innovative broadband acoustic liner concepts (Foil Helmholtz Resonator Liner; FHR-Liners) which utilise flexible foils within a honeycomb structure to attenuate engine and aircraft noise. The requirements for acoustic liners in aviation are described and utilised to derive evaluation criteria. Modifications of the FHR-Liner concept are introduced. A suitable concept evaluation method based on VDI 2225 is applied to evaluate the modified liner concepts concerning the main evaluation criteria. Y1 - 2019 UR - https://2019.isabe.org/content/uploads/ISABE2019_Technical_Program.pdf ER - TY - GEN A1 - Kazula, Stefan A1 - Mischke, Marcel A1 - König, Paul A1 - Höschler, Klaus T1 - Evaluation of Variable Pitot Inlet Concepts 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 describes the selection of the ideal variable inlet concept group by utilising results of aerodynamic investigations, system safety analyses and integration studies. Aerodynamic and functional inlet requirements are explained and variable inlet concept groups are introduced. The concept evaluation by means of a weighted point rating is presented. The respective concept groups are analysed and evaluated regarding economic, functional and safety requirements. By means of this evaluation, the concept group that adjusts the inlet geometry by rigid segment repositioning is identified as most suitable concept group. The early selection of the most suitable concept group enables more detailed subsequent concept investigations, potentially enabling the technology of variable inlets for future commercial aircraft. Y1 - 2019 U6 - https://doi.org/10.1051/matecconf/201930402016 SN - 2261-236X VL - 304 ER - TY - CHAP A1 - Mischke, Marcel A1 - Kazula, Stefan A1 - Höschler, Klaus T1 - A Comparative Concept Study and Evaluation for New Broadband Noise Absorbing Acoustic Liner Concepts for Civil Aviation T2 - Proceedings of Global Power and Propulsion Society, Technical Conference 2019, Zurich N2 - This paper presents an approach to product rating and evaluation of different product solutions for broadband attenuation acoustic liner concepts for aerospace application. In the process, corresponding requirements have been defined for the considered system and evaluation criteria have been derived. Three “Main Evaluation Categories” (Acoustics, System Safety and Integration, Structure and Material) have been introduced to not falsify the assessment results by subject-specific exclusion criteria. A ranked space method has been selected for weighting the evaluation criteria to ensure an objective and knowledge-based rating. The rating has been carried out by a weighted point rating. Concise operational requirements and previously not considered system functions have been identified and linked to the rating and evaluation process. Building on this, further steps for the optimisation and development of the acoustic liner concepts have been presented and explained. KW - Concept Evaluation KW - Concept Rating KW - Acoustic Liner KW - Broadband Attenuation Y1 - 2019 UR - https://gpps.global/proceedings/gpps-zurich19-proceedings/108-zu19-ducts-nozzels/268-gpps-z-2019-46.html SP - 1 EP - 9 ER - TY - GEN A1 - Mischke, Marcel A1 - Pohl, Michael A1 - Höschler, Klaus A1 - Huppertz, André T1 - GAS PATH DESIGNER – zeiteffiziente Vorauslegung von Triebwerks-Ringräumen und zusätzlichen Strukturen T1 - GAS PATH DESIGNER – Time Efficient Pre-Design of Aero Engine Annulus Contours and Additional Structures T2 - Conference Paper des Deutscher Luft- und Raumfahrtkongress 2020 N2 - Der Beginn einer jeden Triebwerksentwicklung startet mit der Auslegung des Ringraumes des Primärgasstromes. Hier müssen einige vorläufige aber auch grundlegende Entscheidungen zu Entwurfsparametern wie Eintrittsquerschnitte, Subsystemlängen, axiale Stufenanzahl in Verdichter und Turbine, usw. definiert werden. Für die Vorauslegung sollte die Palette an anfänglichen Entwurfsparametern so gering wie möglich gehalten werden, um die Menge an möglichen Ringraumentwürfen nicht frühzeitig einzuschränken. Dieses Paper präsentiert das Vorauslegungswerkzeug „Gas Path Designer“ (GPD), welches in der Lage ist Ringraumentwürfe für Turbotriebwerke über zeiteffiziente Berechnungsmethoden in kürzester Zeit bereitzustellen. Das Interface bietet eine Auswahl an Einstellungen, um die genannten Variationsmöglichkeiten zu unterstützen. Der Aufbau ist übersichtlich, um im Rahmen grundlegender konzeptorientierter Gespräche mit dem Kunden eine schnelle und beidseitig nachvollziehbare Variation und Visualisierung des Konzeptentwurfes zu ermöglichen. Des Weiteren können die erhaltenen Ringraumstrukturen der Triebwerksentwürfe als Leitstruktur für CAD-Programme sowie weiterführende Optimierungsstrategien genutzt werden. N2 - The beginning of each aircraft engine development starts with the design of the annulus contour of the primary gas path. In this case, preliminary but also fundamental decisions on design parameters such as inlet cross sections, subsystem lengths, number of stages in compressor and turbine and many more details have to be defined. For the preliminary design, the amount of initial design parameters should be kept as small as possible. Hence, the amount of possible annulus contours and future aero engine designs will not be limited at an early design stage. This paper presents the design tool "Gas Path Designer" (GPD) which is able to provide annulus designs for aero engines via time efficient calculation methods. The user interface offers a suitable range of settings to support the afore mentioned design variation possibilities. Hence, in the context of basic concept-oriented discussions with customers, the GPD allows a quick and mutually comprehensible variation and visualisation of conceptual designs. Furthermore, the resulting annulus contour of the aircraft engine designs can be used as a reference curves for CAD programs and advanced optimization strategies. KW - Gas Path Designer; Annulus Contour; Generic Preliminary Design; Aircraft Engine Y1 - 2020 U6 - http://nbn-resolving.de/urn/resolver.pl?urn:nbn:de:101:1-2020121112494640076557 UR - https://publikationen.dglr.de/?tx_dglrpublications_pi1%5bdocument_id%5d=530098 VL - Deutscher Luft- und Raumfahrtkongress 2020 PB - Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V. CY - Bonn ER - TY - CHAP A1 - Sain, Chetan Kumar A1 - Höschler, Klaus A1 - Mischke, Marcel T1 - Concept study of variable area fan nozzle for UHBPR turbofan engine T2 - 22nd International Symposium on Air Breathing Engines (ISABE-2015-20213), 25.-30. Oktober 2015, Phoenix (AZ, USA) Y1 - 2015 UR - http://hdl.handle.net/2374.UC/745788 PB - ISABE ER - TY - GEN A1 - Mischke, Marcel A1 - Pohl, Michael A1 - Höschler, Klaus A1 - Huppertz, André T1 - A Holistic Approach for the Generic Preliminary Design of Axial Compressor and Turbine Annulus Contours T2 - Conference Paper of the DLRK 2020 N2 - An essential aspect in the whole engine modelling of modern aircraft engines is the preliminary design of the meridional gas path definition. Especially the annulus dimensioning and topological characterisation of engine core subsystems are usually time-consuming. This paper presents a holistic and parametric approach to predesign the geometric 2D annulus contours of compressor and turbine subsystems without complex thermodynamic calculations. It is based on distribution functions of the axial and radial dimensions, as well as the variations of compressor and turbine stages and realises a time-efficient re-dimensioning and topological variation of the complex annulus geometry. Parametric methods for an optimised arrangement of the blade stages in a turbomachinery subsystem configuration are shown and integrated into a mathematical model. KW - Gas Path; Annulus Contour; Generic Preliminary Design; Turbine; Compressor Y1 - 2020 U6 - http://nbn-resolving.de/urn/resolver.pl?urn:nbn:de:101:1-2020121112463561159960 UR - https://publikationen.dglr.de/?tx_dglrpublications_pi1%5bdocument_id%5d=530097 VL - Deutscher Luft- und Raumfahrtkongress 2020 PB - Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V. CY - Bonn ER - TY - GEN A1 - Mischke, Marcel A1 - Kazula, Stefan A1 - Höschler, Klaus T1 - Preliminary Safety Assessment on System Design Level for Broadband Acoustic Liner Concepts for Aviation T2 - Proceedings of the 9th EASN International Conference on Innovation in Aviation & Space N2 - Selected methods of the aviation safety assessment process according to ARP 4761 are introduced and conducted within the scope of a concept study for future broadband acoustic liners. While having similar primary functions and basic design, the acoustic liner concepts diverge concerning subfunctions and potential malfunctions. With the ARP 4761 safety assessment methods, significant differences in sub functions and possible malfunctions of the concepts can be identified. The results of the safety assessment are discussed, and the concepts are evaluated in terms of feasibility and safety. Y1 - 2019 UR - https://www.matec-conferences.org/articles/matecconf/abs/2019/53/matecconf_easn2019_04010/matecconf_easn2019_04010.html U6 - https://doi.org/10.1051/matecconf/201930404010 CY - Athen ER -