ORCID Profile
0000-0001-7783-1361
Current Organisation
Deakin University
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Publisher: Elsevier BV
Date: 07-2014
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 2010
DOI: 10.2514/1.46425
Publisher: ASMEDC
Date: 2006
DOI: 10.1115/GT2006-90090
Abstract: We present an approach for the numerical prediction of the full engine performance and the assessment of multi-component behavior. In this approach, multiple components of a gas turbine are solved with different CFD solvers, each optimized for its assigned task. The solvers are executed simultaneously and during the computation exchange flow data at the interfaces. This enables efficient and accurate simulation of the entire gas turbine. We have developed a coupling software that enables multi-code/multi-physics simulations to perform seamlessly. In this paper, we will present the approach of multi-code simulations, describe the necessary interface and boundary conditions and demonstrate the value of integrated multi-code simulations for the assessment for multi-component effects. Finally, we will show and demonstrate the possibility of full engine simulations using CFD.
Publisher: Emerald
Date: 05-10-2015
Publisher: Elsevier BV
Date: 03-1970
Publisher: SAGE Publications
Date: 03-2014
Abstract: The aerodynamic design of micro air vehicles is challenging since previous studies have shown that the aerodynamic efficiency of airfoils and wings decreases substantially at low Reynolds-numbers. While many MAV approaches investigate biological designs, here a study is conducted on the aerodynamics of paper airplanes, which fly in the same Reynolds-number range as MAV, but have the advantage of simplicity compared to biological counterparts. Flow visualizations and force measurements in a water tunnel as well as large-eddy simulations are presented on one of the simplest paper airplane design: the dart. The results show that the high-sweep delta design of such an airplane provides high lift coefficients at low Reynolds-numbers. Furthermore, the centerfold of the airplane as a mean to improve the aerodynamic performance is identified.
Publisher: AIP Publishing
Date: 06-2012
DOI: 10.1063/1.4718322
Abstract: We present a numerical study on the influence of the Reynolds-number on the lift enhancing effect of a leading edge vortex. Our approach is based on a combination of large-eddy simulations and the immersed boundary technique. We determine the influence of the leading edge vortex on the unsteady lift by simulating a fast pitch-up motion of the plate and studying the lift evolution after holding the flat plate fixed at an angle of attack. Our results suggest that an optimal Reynolds-number exists that maximizes the lift of the leading edge vortex, but that the lift-to-drag ratio is largely independent of the Reynolds-number above a Reynolds-number of Rec & 2000.
Publisher: Springer Science and Business Media LLC
Date: 30-08-2014
Publisher: ASMEDC
Date: 2003
DOI: 10.1115/GT2003-38350
Abstract: The numerical prediction of the entire aero-thermal flow through an entire gas turbine is currently limited by its high computational costs. The approach presented here intends to use several specialized flow solvers based on the Reynolds-averaged Navier-Stokes equations (RANS) as well as Large Eddy Simulations (LES) running simultaneously and exchanging information at the interfaces. This study documents the development of the interface and proves its accuracy and efficiency on simple test-cases.
Publisher: SAGE Publications
Date: 24-06-2015
Abstract: Various parameters including the fins with variable span to chord ratio, curvature radius, and setting angle have been investigated between the flat fin and wrap around fin (WAF) rocket configurations at supersonic flow. The results show that under the same flight condition, the flat fins can provide a higher lift and pitching moments than the WAFs. Due to the symmetric effect, any extra side forces, moments as well as the self-induced rolling characteristics will be not generated as compared to the WAF configurations. The WAFs can greatly improve the longitudinal stability and enhance the longitudinal aerodynamic characteristics for the whole rocket. The static pressure distributions at different chordwise positions together with the force variations around the fins have been obtained computationally and analyzed in detail.
Publisher: ASME International
Date: 16-02-2005
DOI: 10.1115/1.1994877
Abstract: Full-scale numerical prediction of the aerothermal flow in gas turbine engines are currently limited by high computational costs. The approach presented here intends the use of different specialized flow solvers based on the Reynolds-averaged Navier-Stokes equations as well as large-eddy simulations for different parts of the flow domain, running simultaneously and exchanging information at the interfaces. This study documents the development of the interface and proves its accuracy and efficiency with simple test cases. Furthermore, its application to a turbomachinery application is demonstrated.
Publisher: Emerald
Date: 04-01-2016
Publisher: Informa UK Limited
Date: 10-2009
Publisher: ASMEDC
Date: 2004
DOI: 10.1115/PVP2004-3131
Abstract: The numerical prediction of the entire aero-thermal flow through an entire gas turbine is currently limited by its high computational costs. The approach presented here intends to use several specialized flow solvers based on the Reynolds-averaged Navier-Stokes equations (RANS) as well as Large Eddy Simulations (LES) running simultaneously and exchanging information at the interfaces. This study documents the development of the interface and proves its accuracy and efficiency on simple test-cases. Furthermore, its application to a turbo-machinery application is demonstrated.
Publisher: Elsevier BV
Date: 11-2013
Publisher: American Institute of Aeronautics and Astronautics (AIAA)
Date: 05-2015
DOI: 10.2514/1.B35602
Publisher: Springer Netherlands
Date: 2002
Publisher: Informa UK Limited
Date: 04-2004
Publisher: SAGE Publications
Date: 08-2014
DOI: 10.1260/0309-524X.38.4.393
Abstract: We present a novel Vertical Axis Wind Turbine (VAWT) that uses flat delta-wings instead of aerodynamically shaped blades with airfoil cross-sections. This choice lowers the manufacturing costs significantly. Furthermore, delta-wings have a good aerodynamic efficiency at low Reynolds-numbers compared to conventional blades. This is in particular an advantage, if delta-wings are used in small wind turbines. We have performed wind tunnel measurements at low tip-speed ratio and showed that the power output of the delta-wing turbine is higher than that of a conventional straight-bladed VAWT.
Publisher: ASMEDC
Date: 2005
DOI: 10.1115/GT2005-68204
Abstract: We present an approach to simulate the flow in turbomachinery and combustor simultaneously. This method allows predicting interactions between single components of a gas turbine. Two separate flow solvers, one for the turbomachinery, and one for the combustor is used. The flow solvers are executed simultaneously, each computing a section of the flow, and constantly exchanging flow information at the interfaces. We present the approach and its validation. We then apply the approach to a real engine geometry and simulate the interactions between the compressor and the prediffuser of a combustor.
Publisher: Springer Science and Business Media LLC
Date: 2001
Publisher: Cambridge University Press (CUP)
Date: 27-02-2006
Publisher: American Society of Mechanical Engineers
Date: 04-06-2001
DOI: 10.1115/2001-GT-0060
Abstract: Since the flame of high intense low NOx gas turbine combustion systems is stabilized by swirl, the analysis of the swirl flow is very crucial to the design and optimization of such combustion systems. Although a huge amount of publications have been provided on this field just a few have used Large Eddy Simulation due to limits in computer resources. Using Large Eddy Simulation the large vortical structure of the flow is resolved leading to a much better insight of the flow features. Hence, in this paper the Large Eddy Simulation has been applied to investigate the non reacting confined swirling flow downstream of a gas turbine burner. A high accuracy of the prediction of the full three dimensional simulation could be pointed out by comparison of the computational results to measurements. Further the large vortical structure and the dynamic behavior of the flow has been analyzed. The formation of a precessing vortex core is visualized. Due to the precessing motion of the central recirculation zone an alternate vortex shedding at the edges of the burner nozzle is induced. From LES Strouhal numbers for the vortex shedding process are calculated which are confirmed by hot wire measurements.
Publisher: IET
Date: 2011
DOI: 10.1049/CP.2011.0214
Publisher: Trans Tech Publications, Ltd.
Date: 10-2014
DOI: 10.4028/WWW.SCIENTIFIC.NET/AMM.629.109
Abstract: The knowledge about changes of flow field properties during axial compressor operationat high and relatively low speed is limited. This work provides a numerical approach to addressthese problems. Validations about the numerical scheme and the test of compressor performance at various operating speeds are conducted. The results show that computational fluid dynamics (CFD)is capable in predicting the compressor performance. Flow property changes during the compressoroperation are discussed and explanations are proposed. This work reinforces the understanding of compressor operation and provides valid results for future reference.
Publisher: Elsevier BV
Date: 2012
Publisher: Wiley
Date: 17-04-2013
DOI: 10.1002/FLD.3678
Location: Singapore
Location: France
Location: United States of America
No related grants have been discovered for Jorg Schluter.