Towards an Aero-Propulso-Servo-Elasticity Analysis of a Commercial Supersonic Transport

Connolly, Joseph W.; Chwalowski, Pawel; Sanetrik, Mark D.; Carlson, Jan-Reneé; Silva, Walter A.; McNamara, Jack J.; Kopasakis, George

doi:10.2514/6.2016-1320

Cited by 8 publications

(6 citation statements)

References 29 publications

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“…This work compared the installed performance and sonic boom for two discrete inlet designs, and the limited number of configurations made manual coupling a reasonable approach. Connolly et al [27] developed a transient coupled model using an Euler aerodynamic model with 1D gas-dynamics propulsion model for aero-propulso-servo-elasticity applications. They iterate by passing boundary condition values at the interfaces between the two models at every time step to compute state derivatives for the time integration.…”

Section: Fully Coupled Modelmentioning

confidence: 99%

Approach to Modeling Boundary Layer Ingestion using a Fully Coupled Propulsion-RANS Model

Gray

Mader

Kenway

et al. 2017

58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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Airframe-propulsion integration concepts that use boundary layer ingestion have the potential to reduce aircraft fuel burn. One concept that has been recently explored is NASA's Starc-ABL aircraft configuration, which offers the potential for 12% mission fuel burn reduction by using a turbo-electric propulsion system with an aft-mounted electrically driven boundary layer ingestion propulsor. This large potential for improved performance motivates a more detailed study of the boundary layer ingestion propulsor design, but to date, analyses of boundary layer ingestion have used uncoupled methods. These methods account for only aerodynamic effects on the propulsion system or propulsion system effects on the aerodynamics, but not both simultaneously. This work presents a new approach for building fully coupled propulsive-aerodynamic models of boundary layer ingestion propulsion systems. A 1D thermodynamic cycle analysis is coupled to a RANS simulation to model the Starc-ABL aft propulsor at a cruise condition and the effects variation in propulsor design on performance are examined. The results indicates that both propulsion and aerodynamic effects contribute equally toward the overall performance and that the fully coupled model yields substantially different results compared to uncoupled. The most significant finding is that boundary layer ingestion, while offering substantial fuel burn savings, introduces throttle dependent aerodynamics effects that need to be accounted for. This work represents a first step toward the multidisciplinary design optimization of boundary layer ingestion propulsion systems.

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Section: Fully Coupled Modelmentioning

confidence: 99%

Approach to Modeling Boundary Layer Ingestion using a Fully Coupled Propulsion-RANS Model

Gray

Mader

Kenway

et al. 2017

58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…The deformation of the volume mesh and change in aerodynamic loading is then iterated in a time marching scheme. A description of the solution process is presented in the following subsections for the fluidpropulsion-structural coupling: first by giving an overview of the CFD flow solver, second by describing the propulsion system model integration, third by describing AE methodology in FUN3D, and finally specific modifications to the AE model to enable APE analysis [28].…”

Section: Aero-propulso-elastic Modelmentioning

confidence: 99%

Aero-Propulso-Elastic Analysis of a Supersonic Transport

Connolly¹,

Kopasakis²,

Chwalowski³

et al. 2020

Journal of Aircraft

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An aeroelastic modeling capability of a flexible aircraft with gas turbine engines is developed using a computational fluid dynamics tool as an integration platform. The new modeling capability allows for the typical aeroelastic analysis to include a nonlinear dynamic model of the turbomachinery that is capable of capturing relevant gas dynamics. An example case of the aero-propulso-elastic (APE) modeling capability is explored for a supersonic transport vehicle with turbofan engines. An overview of the methodology for integrating the propulsion system and elastic vehicle is provided. This is followed by a study to explore coupling sensitivities compared against typical aeroelastic analysis. Dynamic and static vehicle responses are considered across key flight conditions and vehicle-level angles of attack, where the inclusion of the propulsion system has a 10% increase in vehicle wing tip deformations. It is found that the propulsion system is stable at various operating conditions, with structural oscillations having little impact on propulsion system performance. Perceived loudness, a key performance metric for a supersonic transport, is investigated using the APE model. Results lead to an approximately 4 dB increase in noise over a rigid body analysis that neglects the propulsion system. The greatest impacts are shown during off-nominal conditions.

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“…They compared the installed performance and sonic boom for two discrete inlet designs, and the limited number of configurations made manual coupling a reasonable approach. Connolly et al [20] developed a transient coupled model using an Euler aerodynamic model and 1-D gas-dynamics propulsion model for aeropropulsoservoelasticity applications. They iterated by passing boundary condition values at the interfaces between the two models at every time step to compute state derivatives for the time integration.…”

Section: Fully Coupled Modelmentioning

confidence: 99%

“…The first task toward developing a coupled analysis is to select the propulsion and aerodynamic models that capture the relevant physics. The propulsion system performance can be modeled adequately using an inexpensive 1-D thermodynamic model that represents bulk fluid properties with scalar values [18][19][20]. There are two main approaches to modeling viscous aerodynamics over three-dimensional (3-D) geometries.…”

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confidence: 99%