Collaborative Aircraft Engine Preliminary Design using a Virtual Engine Platform, Part A: Architecture and Methodology

Reitenbach, Stanislaus; Vieweg, Maximilian; Becker, Richard-Gregor; Hollmann, Carsten; Wolters, Florian; Schmeink, Jens; Otten, Tom; Siggel, Martin

doi:10.2514/6.2020-0867

Cited by 30 publications

(14 citation statements)

References 22 publications

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“…The virtual engine platform Gas Turbine Laboratory (GTlab) [25,26], which is developed at the Institute of Propulsion Technology of the German Aerospace Center (DLR), is used to design the engines. The DLR Performance Program (DLRp2) [27] is linked to the performance interface of GTlab and is used for the thermodynamic cycle evaluation.…”

Section: Turbofan Engine Performancementioning

confidence: 99%

Climate Impact Reduction Potentials of Synthetic Kerosene and Green Hydrogen Powered Mid-Range Aircraft Concepts

et al. 2022

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One of aviation’s major challenges for the upcoming decades is the reduction in its climate impact. As synthetic kerosene and green hydrogen are two promising candidates, their potentials in decreasing the climate impact is investigated for the mid-range segment. Evolutionary advancements for 2040 are applied, first with an conventional and second with an advanced low-NOx and low-soot combustion chamber. Experts and methods from all relevant disciplines are involved, starting from combustion, turbofan engine, overall aircraft design, fleet level, and climate impact assessment, allowing a sophisticated and holistic evaluation. The main takeaway is that both energy carriers have the potential to strongly reduce the fleet level climate impact by more than 75% compared with the reference. Applying a flight-level constraint of 290 and a cruise Mach number of 0.75, causing 5% higher average Direct Operating Costs (DOC), the reduction is even more than 85%. The main levers to achieve this are the advanced combustion chamber, an efficient contrail avoidance strategy, in this case a pure flight-level constraint, and the use of CO2 neutral energy carrier, in a descending priority order. Although vehicle efficiency gains only lead to rather low impact reduction, they are very important to compensate the increased costs of synthetic fuels or green hydrogen.

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Section: Turbofan Engine Performancementioning

confidence: 99%

Climate Impact Reduction Potentials of Synthetic Kerosene and Green Hydrogen Powered Mid-Range Aircraft Concepts

et al. 2022

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“…DLR experts have delivered performance and geometrical data for the SST engines under consideration for direct implementation into the process. The DLR tool GTlab (Gas Turbine Laboratory) was applied to design the SST engine model and to calculate required data [18]. The tool is an interactive, cross-platform simulation and preliminary design environment for aero engines and gas turbines.…”

Section: Aircraft and Engine Designmentioning

confidence: 99%

Simulation of Landing and Take-Off Noise for Supersonic Transport Aircraft at a Conceptual Design Fidelity Level

Nöding

Schuermann²,

Bertsch

et al. 2021

Aerospace

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The German Aerospace Center has launched an internal project to assess the noise impact associated with supersonic transport aircraft during approach and departure. A dedicated simulation process is established to cover all relevant disciplines, i.e., aircraft and engine design, engine installation effects, flight simulation, and system noise prediction. The core of the simulation process is comprised of methods at the complexity and fidelity level of conceptual aircraft design, i.e., typical overall aircraft design methods and a semi-empirical approach for the noise modeling. Dedicated interfaces allow to process data from high fidelity simulation that will support or even replace initial low fidelity results in the long run. All of the results shown and discussed in this study are limited to the fidelity level of conceptual design. The application of the simulation process to the NASA 55t Supersonic Technology Concept Aeroplane, i.e., based on non-proprietary data for this vehicle, yields similar noise level predictions when compared to the published NASA results. This is used as an initial feasibility check of the new process and confirms the underlying methods and models. Such an initial verification of the process is understood as an essential step due to the lack of available noise data for supersonic transport aircraft in general. The advantageous effect of engine noise shielding on the resulting system noise is demonstrated based on predicted level time histories and certification noise levels. After this initial verification, the process is applied to evaluate a conceptual supersonic transport design based on a PhD thesis with two engines mounted under the wing, which is referred to as aircraft TWO. Full access to this vehicle’s design and performance data allows to investigate the influence of flight procedures on the resulting noise impact along approach and departure. These noise results are then assembled according to proposed Federal Aviation Agency regulations in their Notice of Proposed Rulemaking, e.g., speed limitations, for Supersonic transport noise certification and the regulations from Noise Chapters of the Annex 16 from the International Civil Aviation Organization in order to evaluate the resulting levels as a function of the flight procedure.

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“…The entire architecture of the developed collaborative process and the applied software tools are summarized in Refs. [3,28]. The final 3-D geometry of the turbofan engine, which was generated entirely from the information of the central data model, is shown in Fig.…”

Section: Generic Two-shaft Mixed Flow Turbofan Enginementioning

confidence: 99%

Parametric Datamodel for Collaborative Preliminary Aircraft Engine Design

Reitenbach

Hollmann

Schmeink

et al. 2021

AIAA Scitech 2021 Forum

Self Cite

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An essential aspect of the collaborative multidisciplinary preliminary design process of aircraft engines is the involvement of a large number of experts from different disciplines and the usage of numerous tools and workflows. This is a major challenge, especially in the area of data management, as large amounts of data are generated that have to be exchanged and traced via a multitude of interfaces. The purpose of the paper is to present an approach of a central data model as a vehicle for data management in collaborative aircraft engine preliminary design. The first part describes the general structure and abstract definition of the developed data model utilizing modeling languages. Subsequently, a detailed description of the geometric parameterization concerning important engine components and additional data structures follows. Besides the methodology, the software implementation to support this approach is presented in detail, including data serialization and data identification, as well as automated capturing and storage of provenance data throughout the design process. The functionality of the approach is demonstrated by means of examples derived from the preliminary engine design.

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Collaborative Aircraft Engine Preliminary Design using a Virtual Engine Platform, Part A: Architecture and Methodology

Cited by 30 publications

References 22 publications

Climate Impact Reduction Potentials of Synthetic Kerosene and Green Hydrogen Powered Mid-Range Aircraft Concepts

Climate Impact Reduction Potentials of Synthetic Kerosene and Green Hydrogen Powered Mid-Range Aircraft Concepts

Simulation of Landing and Take-Off Noise for Supersonic Transport Aircraft at a Conceptual Design Fidelity Level

Parametric Datamodel for Collaborative Preliminary Aircraft Engine Design

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