A Case Study of High Fidelity Engine System Simulation

Claus, Russell W.; Townsend, Scott; Lavelle, Tom; Naiman, Cynthia; Turner, Mark G.

doi:10.2514/6.2006-4971

Cited by 9 publications

(7 citation statements)

References 3 publications

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“…Such a variable fidelity approach allows certain sensitive regions to be analyzed more thoroughly, while still making the overall problem computationally tractable. There are significant challenges in the interfaces between components when employing such an approach 32,33 . In addition, rigorous validation and verification is key to ensuring accuracy.…”

Section: E Propulsionmentioning

confidence: 99%

The Need for Advanced Simulations for Advanced Air Vehicle Concepts

Dryer¹,

Rogers

2016

46th AIAA Fluid Dynamics Conference

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A NASA program perspective is provided on the overall impact of advanced computational simulations on a portfolio of advanced air vehicles research. The current portfolio is built upon a rich history in both developing and employing advanced computational capabilities that enhance aerospace applications. These tools range from high-fidelity computational fluid dynamics simulations to comprehensive multidisciplinary design analysis and optimization codes. These analysis and design tools impact every area of vehicle-related research. Since this scope is so large, just a few representative examples from various aircraft and propulsion applications are provided. Brief assessments of potential future areas needing further development are also provided. In addition to using these tools to advance specific vehicle technologies, there are ongoing efforts to improve computational simulation capabilities in general by taking a long-term view of what key developments are needed in some key areas. Finally, a brief assessment is provided on how computational tools can be used more effectively in conjunction with ground and flight experimentation.

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Section: E Propulsionmentioning

confidence: 99%

The Need for Advanced Simulations for Advanced Air Vehicle Concepts

Dryer¹,

Rogers

2016

46th AIAA Fluid Dynamics Conference

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“…The multidisciplinary framework of NPSS is illustrated in Figure 3-2, where three primary characteristics of the simulation environment: discipline coupling, component integration and zooming are shown. This framework allows an engineer to "plug and play" or "substitute at will" the components of an engine with any combination of 0, 1, 2, 3 dimensional component codes [24]. Traditionally, the interaction between different disciplines is handled in a sequential fashion, with the use of translators to transfer and translate information from one discipline to the next.…”

Section: Npss Simulation Environmentmentioning

confidence: 99%

“…This is however lengthy, tedious and often inaccurate [20]. from one another [24]. This architecture is illustrated in Figure 3 NPSS utilizes a C++ type object-oriented programming language [25], with the following attributes: 1) maximum code reusability, 2) clear data connectivity, and 3) code modularity [20].…”

Section: Npss Simulation Environmentmentioning

confidence: 99%

“…The problem can be divided into objects that consist of useful data and methods (functions) [26]. The basic objects used for a 0 and 1-dimensional analysis are: 1) elements, 2) subelements, 3) flow stations, 4) ports and 5) tables [24]. This object structure allows NPSS to have a wide range of applications amongst air breathing, rocket, fuel cell and ground based power propulsion and more by creating new functional objects for each particular application [24].…”

Section: Npss Simulation Environmentmentioning

confidence: 99%

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Quasi-one-dimensional Scramjet Combustor Flow Solver Using the Numerical Propulsion System Simulation

Wilson

2018

2018 Joint Propulsion Conference

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The flow field inside a scramjet engine combustor involves complex phenomena such as fuel-air mixing, combustion chemistry, and flow separation. In order to determine the properties of the flow along the length of the combustor, mass, momentum and energy balance equations are solved simultaneously using a numerical method. While a full three dimensional computational simulation gives detailed results with high order of accuracy, it demands a great amount of time and computational resource. A low order analysis produces a fast overall picture of the combustor operation which in turn provides valuable information suitable for the preliminary design process. This research work aims to describe the analysis process of the scramjet combustor in which a quasi-onedimensional, multi-species, reacting real gas model of the flow is developed to address the limitations in previous researches. The Numerical Propulsion System Simulation (NPSS), into which the NASA Chemical Equilibrium with Applications (CEA) code is integrated, is utilized as the platform to perform the analysis. The analytical model is validated by comparison with experimental data from previous researches. The results obtained by this method are expected to shed some light on the advantages of using detailed chemistry with lower order analysis to calculate scramjet engine performance. v Table of Contents Acknowledgements .

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“…Some of the component simulations such as the high pressure compressor were also found to be difficult to converge, and the interface matching remains a weak point of this approach. Some of these issues are currently being addressed in NASA sponsored efforts as mentioned in Claus et al 38 The Stanford effort has addressed improved modeling capability with unsteady RANS techniques and an LES approach in the combustor. However, compressor and turbine blade counts have been modified to limit the problem to a 20-degree sector of the annulus.…”

Section: Current Status In 2007mentioning

confidence: 99%

Petaflops Opportunities for the NASA Fundamental Aeronautics Program (Invited)

Mavriplis

Darmofal

Keyes

et al. 2007

18th AIAA Computational Fluid Dynamics Conference

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The premise of this paper is the observation that the engineering community in general, and the NASA aeronautics program in particular, have not been active participants in the renewed interest in high performance computing at the national level. Advocacy for high performance computing has increasingly been taken up by the science community with the argument that computational methods are becoming a third pillar of scientific discovery alongside theory and experiment. Computational engineering, on the other hand, has continually been relegated to a set of mature software tools which run on commodity hardware, with the notion that engineering problems are not complex enough to warrant the deployment of state-of-the-art hardware on such a vast scale. We argue that engineering practices can benefit equally from an aggressive program in high performance computational methods, and that these problems are at least as important as science problems, particularly with regards to any national competitiveness agenda. Because NASA aeronautics has historically been a principal driver of computational engineering research and development, the current situation represents an opportunity for the NASA aeronautics program to resume its role as a leading advocate for high performance computational engineering at the national level. We outline a sample set of Grand Challenge problems which are used to illustrate the potential benefits a reinvigorated program could produce, and use these examples to identify critical barriers to progress and required areas of investment. We conclude by noting that other communities have spent significant efforts in formulating the case for increased investment in high performance computing activities, and that a similar roadmap will be required for the engineering community.

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A Case Study of High Fidelity Engine System Simulation

Cited by 9 publications

References 3 publications

The Need for Advanced Simulations for Advanced Air Vehicle Concepts

The Need for Advanced Simulations for Advanced Air Vehicle Concepts

Quasi-one-dimensional Scramjet Combustor Flow Solver Using the Numerical Propulsion System Simulation

Petaflops Opportunities for the NASA Fundamental Aeronautics Program (Invited)

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