Turbofan Volume Dynamics Model for Investigations of Aero-Propulso-Servo-Elastic Effects in a Supersonic Commercial Transport

Connolly, Joseph W.; Kopasakis, George; Lemon, Kimberly

doi:10.2514/6.2009-4802

Cited by 6 publications

(5 citation statements)

References 12 publications

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“…Meanwhile, the engine rotor speed and turbine inlet temperature could not exceed limit in order to ensure the stability of fan, compressor, and combustion chamber. The engine used in supersonic passenger aircraft can be divided into the following: main operating conditions, engine start-up, take-off, acceleration and climbing, the subsonic flight whose airline is set in residential areas, supersonic cruise, and landing [5][6][7]. Corresponding to the different working conditions, the control tasks are different.…”

Section: Introductionmentioning

confidence: 99%

Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback

Chen

Zhang

et al. 2020

International Journal of Aerospace Engineering

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In order to consider the inlet and engine integrated model of supersonic airliner, the dynamic identification and control of inlet normal shock are studied. The research is based on the bleed air flow rate under supersonic conditions. With the two-dimensional CFD model of supersonic inlet, the dynamic and static effects of the bleeding flow rate on the normal shock position were investigated. The transfer function was identified, and simultaneously the paper carried out a comprehensive study of inlet and engine integrated model, which is established based on the inlet shock position model and engine component level model. The relationship between normal shock position and total pressure recovery coefficient has been taken into consideration in this model. Based on the inlet and engine integrated model, the closed-loop control simulation of normal shock position is carried out. The results show that the model could resist the disturbance of the inlet flow and keep the inlet and engine matching operation point stable near the optimal value.

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Section: Introductionmentioning

confidence: 99%

Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback

Chen

Zhang

et al. 2020

International Journal of Aerospace Engineering

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“…Each of these ducts are also modeled using the governing conservation equations. 4 In addition, a preliminary fan speed controller is included that was previously developed. 13 The initial operating conditions and component geometry information, as well as the component performance maps required to implement the dynamic VCE model is obtained from a design concept of a supersonic VCE implemented in the Numerical Propulsion System Simulation (NPSS).…”

Section: Figure 2 Engine Design Concept For a Variable Cycle Enginementioning

confidence: 99%

“…The modeling approach is outlined in previous works. 3,4,15 Each of the fluid flow components is modeled using a set of derived conservation equations modified from the standard Euler form and written for continuity, momentum, and energy. These equations are integrated numerically using a time marching scheme and the Seldner differencing technique of the spacial terms.…”

Section: Figure 2 Engine Design Concept For a Variable Cycle Enginementioning

confidence: 99%

Computational Fluid Dynamics Modeling of a Supersonic Nozzle and Integration into a Variable Cycle Engine Model

Connolly

Friedlander²,

Kopasakis³

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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This paper covers the development of an integrated nonlinear dynamic simulation for a variable cycle turbofan engine and nozzle that can be integrated with an overall vehicle Aero-Propulso-Servo-Elastic (APSE) model. A previously developed variable cycle turbofan engine model is used for this study and is enhanced here to include variable guide vanes allowing for operation across the supersonic flight regime. The primary focus of this study is to improve the fidelity of the model's thrust response by replacing the simple choked flow equation convergent-divergent nozzle model with a MacCormack method based quasi-1Dmodel. The dynamic response of the nozzle model using the MacCormack method is verified by comparing it against a model of the nozzle using the conservation element/solution element method. A methodology is also presented for the integration of the MacCormack nozzle model with the variable cycle engine.

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“…Thus, the leakage mass flow rate as a function of back pressure also becomes a boundary condition for the external CFD cells. The remaining states at the exit boundary can be computed by utilizing the following characteristic equation: 2 (12) To integrate the inlet to the existing engine simulations, 4,5,6 the mass flow rate demand of the engine needs to be specified as a boundary condition. However, it is not possible to directly use this boundary condition for the inlet model by itself.…”

Section: Boundary Conditionsmentioning

confidence: 99%

“…3 Thus, this modeling effort is considered to be a first step towards the development of a more comprehensive dynamic external compression inlet model, which potentially could be integrated with the rest of the propulsion system model, currently under development. 4,5,6 Recently, the modeling approaches developed and lessons learned in these efforts progressed to developing the first version of a Variable Cycle Engine (VCE) 6 model, which is considered to be a more appropriate propulsion system concept for future supersonic vehicles.…”

Section: Introductionmentioning

confidence: 99%

Quasi One-Dimensional Unsteady Modeling of External Compression Supersonic Inlets

Kopasakis

Connolly²,

Kratz

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The AeroServoElasticity task under the NASA Supersonics Project is developing dynamic models of the propulsion system and the vehicle in order to conduct research for integrated vehicle dynamic performance. As part of this effort, a nonlinear quasi 1-dimensional model of an axisymmetric external compression supersonic inlet is being developed. The model utilizes compressible flow computational fluid dynamics to model the internal inlet segment as well as the external inlet portion between the cowl lip and normal shock, and compressible flow relations with flow propagation delay to model the oblique shocks upstream of the normal shock. The external compression portion between the cowl-lip and the normal shock is also modeled with leaking fluxes crossing the sonic boundary, with a moving CFD domain at the normal shock boundary. This model has been verified in steady state against tunnel inlet test data and it's a first attempt towards developing a more comprehensive model for inlet dynamics.

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Turbofan Volume Dynamics Model for Investigations of Aero-Propulso-Servo-Elastic Effects in a Supersonic Commercial Transport

Cited by 6 publications

References 12 publications

Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback

Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback

Computational Fluid Dynamics Modeling of a Supersonic Nozzle and Integration into a Variable Cycle Engine Model

Quasi One-Dimensional Unsteady Modeling of External Compression Supersonic Inlets

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