Abstract
This paper presents a modular, flexible, extendable and fast-computational framework that implements a multidisciplinary, varying fidelity, multi-system approach for the conceptual and preliminary design of novel aero-engines. In its current status, the framework includes modules for multi-point steady-state engine design, aerodynamic design, engine geometry and weight, aircraft mission analysis, Nitrogen Oxide (NOx) emissions, control system design and integrated controller-engine transient-performance analysis. All the modules have been developed in the same software environment, ensuring consistent and transparent modeling while facilitating code maintainability, extendibility and integration at modeling and simulation levels. Any simulation workflow can be defined by appropriately combining the relevant modules. Different types of analysis can be specified such as sensitivity, design of experiment and optimization. Any combination of engine parameters can be selected as design variables, and multi-disciplinary requirements and constraints at different operating points in the flight envelope can be specified. The framework implementation is exemplified through the optimization of an ultra-high bypass ratio geared turbofan engine with a variable area fan nozzle, for which specific aircraft requirements and technology limits apply. Although the optimum design resulted in double-digit fuel-burn benefits compared to current technology engines, it did not meet engine-response requirements, highlighting the need to include transient-performance assessments as early as possible in the preliminary engine design phase.
Highlights
When answering a request for proposal, engine manufacturers use various modeling tools to predict if an engine design will meet the aircraft’s top-level requirements
The optimum value of Fan pressure ratio (FPR) was found to be 1.3, requiring the variable-area fan nozzle (VAN) to open by almost 13% at rolling take-off (RTO) compared to the ToC area, in order to keep the fan operating on its unique line
To quickly and accurately evaluate alternative aero-engine designs, appropriate preliminary design tools are necessary that are capable of capturing the effects of new technologies on engine performance and assess their feasibility in a multi-disciplinary and multi-point operational context
Summary
When answering a request for proposal, engine manufacturers use various modeling tools to predict if an engine design will meet the aircraft’s top-level requirements. The design should be fuel-efficient, have stable operation over the entire flight envelope, comply with environmental regulations, have acceptable production and maintenance costs and integrate seamlessly with the aircraft Fulfilling these objectives requires a multiobjective optimization procedure in which reliable and robust predictive models of many engineering disciplines are coupled in an iterative calculation. This entails the existence of the relevant models and the corresponding integration framework with appropriate simulation functionalities. Tools with such modeling and simulation capabilities are available in the industry; for example, MTU’s MOPEDS (MOdular Performance and Engine Design System) [1] and Pratt & Whitney’s PMDO (Preliminary Multi-Disciplinary Design Optimization) [2]. Some tools are too complex for this phase of engine design at the modeling (higher fidelity codes) and/or calculation (nested iterations between disciplines) level, which hinders speed of execution without necessarily improving calculation accuracy
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