Validation of uRANS-Simulations of Contra-Rotating Open Rotor-Powered Aircraft at Take-Off Conditions

Stuermer, Arne W.

doi:10.2514/6.2018-1265

Cited by 5 publications

(5 citation statements)

References 11 publications

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“…As found in previous research, [22][23][24][25] the predicition of the key mean performance metrics is less dependent on the temporal resolution used in the uRANS simulation. The overall fan pressure ration (FPR) and the mass flow rate through the aft propulsor are two of the main performance measures in focus in this study.…”

Section: Iva Urans Simulation Analysissupporting

confidence: 69%

“…The uRANS simulation approach for the complete aft propulsor aircraft configuration builds on experience gained in the recent past on similar studies on the propulsion-airframe integration for CROR and UHBR engines. [22][23][24][25] In this approach, the computations are initialized with a steady-state simulation in which the rotors remain stationary. In the subsequent unsteady simulation, a step-by-step refinement of the time-step size is performed, with the aim of studying the impact of the temporal resolution on the aerodynamic results, in particular the fan-OGV interactions.…”

Section: Iiib the Urans Simulation Approachmentioning

confidence: 99%

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Aerodynamic Analysis of a Transport Aircraft with a Boundary Layer Ingesting Aft-Propulsor at Cruise Flight Conditions

Stuermer

Spinner

Trost

et al. 2022

AIAA AVIATION 2022 Forum

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The implementation of advanced propulsion systems to ensure aviation meets the increasingly stringent environmental and economic pressures is a key building block in the development of future transport aircraft. A promising technology is the utilization of boundary layer ingesting (BLI) propulsion concepts, which are seen to offer an improvement of the engine propulsive efficiency in tandem with a reduction of the overall aircraft wake dissipation losses. In a collaborative study between the DLR Institute of Aerodynamics and Flow Technology, the DLR Institute of Propulsion Technology and industrial partners, a comprehensive study of the potential of implementing BLI concepts for future single-aisle short-to-medium range transport aircraft has been conducted. The present paper presents the result of an overall aircraft aerodynamic study, in which an aft BLI propulsor, specifically designed for this particular application, is investigated in its installation on the tail of a single aisle aircraft configuration at cruise flight conditions. A detailed aerodynamic analysis is presented, with a focus on comparing the results achievable through various BLI engine modeling approaches, which include the use of a classical engine boundary condition, a body force model as well as a full representation of the fan and OGV stage in a uRANS simulation approach. In addition to the study of the mutual aerodynamic interactions between the airframe and propulsor, some key aspects of the highest fidelity uRANS simulation approach are also discussed.

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Section: Iva Urans Simulation Analysissupporting

confidence: 69%

Section: Iiib the Urans Simulation Approachmentioning

confidence: 99%

Aerodynamic Analysis of a Transport Aircraft with a Boundary Layer Ingesting Aft-Propulsor at Cruise Flight Conditions

Stuermer

Spinner

Trost

et al. 2022

AIAA AVIATION 2022 Forum

Self Cite

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“…All CFD simulations are performed utilizing the DLR TAU-Code for both the steady RANS and the uRANS computations. For the latter, much know-how was transferred from a process chain that has already been successfully applied in a number of recent propeller and CROR investigations [1,[9][10][11][12][13][14], where validation with wind tunnel test data has shown high-quality engine performance predictions for various isolated and installed configurations is achievable, with deviations of less than 1% to the experimental values.…”

Section: Computational Strategymentioning

confidence: 99%

DLR TAU-Code uRANS Turbofan Modeling for Aircraft Aerodynamics Investigations

Stuermer¹

2019

Aerospace

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In the context of an increased focus on fuel efficiency and environmental impact, turbofan engine developments continue towards larger bypass ratio engine designs, with Ultra-High Bypass Ratio (UHBR) engines becoming a likely power plant option for future commercial transport aircraft. These engines promise low specific fuel consumption at the engine level, but the resulting size of the nacelle poses challenges in terms of the installation on the airframe. Thus, their integration on an aircraft requires careful consideration of complex engine–airframe interactions impacting performance, aeroelastics and aeroacoustics on both the airframe and the engine sides. As a partner in the EU funded Clean Sky 2 project ASPIRE, the DLR Institute of Aerodynamics and Flow Technology is contributing to an investigation of numerical analysis approaches, which draws on a generic representative UHBR engine configuration specifically designed in the frame of the project. In the present paper, project results are discussed, which aimed at demonstrating the suitability and accuracy of an unsteady RANS-based engine modeling approach in the context of external aerodynamics focused CFD simulations with the DLR TAU-Code. For this high-fidelity approach with a geometrically fully modeled fan stage, an in-depth study on spatial and temporal resolution requirements was performed, and the results were compared with simpler methods using classical engine boundary conditions. The primary aim is to identify the capabilities and shortcomings of these modeling approaches, and to develop a best-practice for the uRANS simulations as well as determine the best application scenarios.

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“…However, URANS model provide a very time effective numerical solutions for flow analysis and still a prefer approach in aerodynamic and aeroacoustics industry for large number of numerical simulations without compromising much accuracy. [40][41][42][43][44][45][46][47] Therefore, URANS model is used to simulate 392 configurations. A reference model was made without grooves and drag and lift coefficient results are validated against the study presented by Diasinos et al, 24 with less than 1% deviation.…”

Section: Numerical Configurationmentioning

confidence: 99%

Neural networks assisted computational aero-acoustic analysis of an isolated tire

Uddin

Niazi

Arafat

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part D:

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The computational aero-acoustic study of an isolated passenger car tire is carried out to understand the effect of dimensions of longitudinal tire grooves and operational parameters (velocity and temperature) on tire noise. The computational fluid dynamics and acoustic models are used to obtain aero-acoustic tire noise at near-field and far-field receivers around the tire and artificial neural networks-based regression are used to study the highly non-linear and interactive causal relationships in the system. Unsteady Reynolds-Averaged Navier-Stokes based realizable k-epsilon model is used to solve the flow field in the computational domain. The Ffowcs Williams and Hawkings model is used to obtain aero-acoustic tire noise at far-field positions. Spectral analysis is used to convert the output time domain to frequency domain and to obtain A-weighted sound pressure level. Artificial neural network–based response surface regression is conducted to understand casual relationships between A-weighted sound pressure level and control variables (Groove depth, Groove width, Temperature and velocity). Maximum A-weighted sound pressure level is observed in the wake region of the tire model. The interaction study indicates that ∼10% reduction in the aero-acoustic emissions is possible by selecting appropriate combinations of groove width and groove depth. The interaction of velocity with width is found to be most significant with respect to A-weighted sound pressure level at all receivers surrounding the tire. The interaction of operational parameters, that is, velocity and temperature are found to be significant with respect to A-weighted sound pressure level at wake and front receivers. Therefore, the regional speed limits and seasonal temperatures need to be considered while designing the tire to achieve minimum aero-acoustic emissions.

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Validation of uRANS-Simulations of Contra-Rotating Open Rotor-Powered Aircraft at Take-Off Conditions

Cited by 5 publications

References 11 publications

Aerodynamic Analysis of a Transport Aircraft with a Boundary Layer Ingesting Aft-Propulsor at Cruise Flight Conditions

Aerodynamic Analysis of a Transport Aircraft with a Boundary Layer Ingesting Aft-Propulsor at Cruise Flight Conditions

DLR TAU-Code uRANS Turbofan Modeling for Aircraft Aerodynamics Investigations

Neural networks assisted computational aero-acoustic analysis of an isolated tire

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