Multidisciplinary propulsion simulation using NPSS

Claus, Russell W.; Evans, Austin L.; Follen, Gregory J.

doi:10.2514/6.1992-4709

Cited by 40 publications

(11 citation statements)

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“…The inputs are throttle setting, Mach number, and altitude, and the outputs are thrust and thrust-specific fuel consumption. The data is generated from the Numerical Propulsion System Simulation (NPSS) software [31] for a Boeing 777-sized engine. Thrust is linear in throttle setting, so the throttle is computed in 'throttle comp' by evaluating the maximum thrust for the Mach number and altitude of interest and normalizing the current thrust by the maximum thrust.…”

Section: Coupled Solutionmentioning

confidence: 99%

Design and Trajectory Optimization of a Morphing Wing Aircraft

Jasa

Hwang

Martins

2018

2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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Adding morphing wing technology to aircraft could drastically reduce the fuel burn required to complete a certain mission. This gain comes from the wing being able to adapt to become optimal for the desired flight condition. For maximal benefit, we must design the wing, morphing inputs, and mission trajectory simultaneously. In this work, we perform gradient-based aerostructural optimization for a morphing Common Research Model wing while optimizing its nominal design, morphing twist across its mission, and its altitude profile. Using a morphing optimization approach that simultaneously optimizes the mission and design, we find a 0.2 to 0.7% fuel burn decrease compared to a non-morphing design optimization, where the benefit increases with range. We also compare the fully coupled optimization approach with a surrogate-based approach to determine if we can simplify the optimization problem while still arriving at the optimal result. We find that the surrogate-based approach finds an optimum within 1.5% of the optimum obtained from the fully coupled approach and that the difference is smaller for smaller ranges.

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Section: Coupled Solutionmentioning

confidence: 99%

Design and Trajectory Optimization of a Morphing Wing Aircraft

Jasa

Hwang

Martins

2018

2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…The aircraft weight buildup relationships within FLOPS are based on regressions of historical data, and therefore apply to conventional subsystem architectures. The engine performance data tables (engine decks) used by FLOPS are generated using the industry-standard Numerical Propulsion System Simulation (NPSS) [10] tool. NPSS is not directly integrated with RATE, but is instead used off-line to generate engine deck files which can be imported into RATE and used in the FLOPS sizing and mission performance analyses.…”

Section: Conventional Aircraft Sizing and Mission Performance Evaluationmentioning

confidence: 99%

Parametric Approach to Assessing Performance of High-Lift Device Active Flow Control Architectures

et al. 2017

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Active Flow Control is at present an area of considerable research, with multiple potential aircraft applications. While the majority of research has focused on the performance of the actuators themselves, a system-level perspective is necessary to assess the viability of proposed solutions. This paper demonstrates such an approach, in which major system components are sized based on system flow and redundancy considerations, with the impacts linked directly to the mission performance of the aircraft. Considering the case of a large twin-aisle aircraft, four distinct active flow control architectures that facilitate the simplification of the high-lift mechanism are investigated using the demonstrated approach. The analysis indicates a very strong influence of system total mass flow requirement on architecture performance, both for a typical mission and also over the entire payload-range envelope of the aircraft.

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“…The term fidelity is used in this context to represent the accuracy of the geometry representation in the simulation and level of detail contained in the modeling approach. Simulations involving 0-D or 1-D geometry analyzed at steady-state are considered low fidelity, while 3-D steady-state or transient simulations are considered higher fidelity [5,6]. Robustness of the optimal design in terms of emission performance is also studied by explorin g limited part-power operation.…”

Section: Introductionmentioning

confidence: 99%

Parametric Modeling Investigation of a Radially-Staged Low-Emission Aviation Combustor

Heath

2016

54th AIAA Aerospace Sciences Meeting

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Aviation gas-turbine combustion demands high efficiency, wide operability and minimal trace gas emissions. Performance critical design parameters include injector geometry, combustor layout, fuel-air mixing and engine cycle conditions. The present investigation explores these factors and their impact on a radially staged low-emission aviation combustor sized for a next-generation 24,000-lbf-thrust engine. By coupling multi-fidelity computational tools, a design exploration was performed using a parameterized annular combustor sector at projected 100% takeoff power conditions. Design objectives included nitrogen oxide emission indices and overall combustor pressure loss. From the design space, an optimal configuration was selected and simulated at 7.1, 30 and 85% part-power operation, corresponding to landing-takeoff cycle idle, approach and climb segments. All results were obtained by solution of the steady-state Reynolds-averaged Navier-Stokes equations. Species concentrations were solved directly using a reduced 19-step reaction mechanism for Jet-A. Turbulence closure was obtained using a nonlinear κ-ε model. This research demonstrates revolutionary combustor design exploration enabled by multi-fidelity physics-based simulation. Nomenclature A 3 = inlet combustor cross sectional area, m 2

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Multidisciplinary propulsion simulation using NPSS

Cited by 40 publications

References 0 publications

Design and Trajectory Optimization of a Morphing Wing Aircraft

Design and Trajectory Optimization of a Morphing Wing Aircraft

Parametric Approach to Assessing Performance of High-Lift Device Active Flow Control Architectures

Parametric Modeling Investigation of a Radially-Staged Low-Emission Aviation Combustor

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