The Experts below are selected from a list of 258 Experts worldwide ranked by ideXlab platform
Clint Young - One of the best experts on this subject based on the ideXlab platform.
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music with the urqmd Afterburner
Nuclear Physics, 2013Co-Authors: Sangwook Ryu, Sangyong Jeon, Charles Gale, Björn Schenke, Clint YoungAbstract:As RHIC is entering the precision measurement era and the LHC is producing a copious amount of new data, the role of 3+1D event-by-event viscous hydrodynamics is more important than ever to understand the bulk data as well as providing the background for hard probes. For more meaningful comparison with the experimental data, it is also important that hydrodynamics be coupled to the hadronic Afterburner. In this proceeding we report on preliminary results of coupling MUSIC with UrQMD.
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MUSIC with the UrQMD Afterburner
Nuclear Physics A, 2013Co-Authors: Sangwook Ryu, Sangyong Jeon, Charles Gale, Björn Schenke, Clint YoungAbstract:As RHIC is entering the precision measurement era and the LHC is producing a copious amount of new data, the role of 3+1D event-by-event viscous hydrodynamics is more important than ever to understand the bulk data as well as providing the background for hard probes. For more meaningful comparison with the experimental data, it is also important that hydrodynamics be coupled to the hadronic Afterburner. In this proceeding we report on preliminary results of coupling MUSIC with UrQMD.Comment: 4 pages, 6 figures in pdf. Submitted to the proceedings of the Quark Matter 2012 conference (August 13-18, 2012, Washington D.C.
Naveed Durrani - One of the best experts on this subject based on the ideXlab platform.
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Preliminary Design of a Short Afterburner for Single-Spool Expendable Turbojet Engine
49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2011Co-Authors: Basharat Ali Haider, Nikola Davidovi, Naveed DurraniAbstract:A theoretical study related to a short Afterburner design is presented in this paper. The objective is to enhance the performance of an existing single-spool expendable turbojet engine in terms of thrust, with a xed-area exit nozzle. The expendable turbojet engines are generally used in the reconnaissance air vehicles where the engine is positioned in the fuselage near the center of gravity. Consequently, a longer exhaust duct exists before of the nozzle section which can house a short Afterburner. An in-house FORTRAN language code is developed to evaluate the performance of single-spool expendable turbojet engine without Afterburner and the results of the code are validated with the available experimental data. A short Afterburner is designed based on the available length constraints. As a result of the limited length available for the Afterburner, combustion chamber has to be considerably shorter than those usually used in the Afterburners. Afterburner pressure loss and eciency is calculated iteratively by using Afterburner inlet conditions. It is found that by adding the designed short Afterburner, about 20% increase in the thrust is achieved at the expense of 50% increase in specic fuel consumption.
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Parametric Analysis of Expendable type Single-Spool Turbojet Engine with a Short Afterburner
49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2011Co-Authors: Basharat Ali Haider, Nikola Davidovic, Naveed DurraniAbstract:A parametric, on-design performance analysis of an existing single-spool expendable turbojet engine with a short Afterburner is presented in this paper. A design point mathematical model of the engine is developed to obtain the optimum system performance conditions. This model utilizes the engine design parameters, such as operating flight conditions, compressor pressure ratio, turbine inlet temperature and Afterburner exit temperature to predict the engine performance parameters, such as specific thrust and specific fuel consumption. The results obtained are in a good agreement with commercial software, GasTurb, used for the performance analysis of gas turbine engines and with the available experimental data. Subsequently, the effects of adding a short Afterburner on the performance of the engine were studied using a parametric analysis. A theoretical database for different performance parameters was obtained as a design reference for the future work.
V. Ganesan - One of the best experts on this subject based on the ideXlab platform.
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Flow Investigations in an Aero Gas Turbine Engine Afterburner
Transportation, 2005Co-Authors: S. Suresh Kumar, V. GanesanAbstract:This paper is concerned with the prediction of flow and flame characteristics behind complex flame stabilizer used in aero gas turbine Afterburners. The numerical calculation is performed using SIMPLE algorithm with unstructured grid arrangement in which time averaged transport equation for mass, momentum, turbulence and energy are solved using finite volume method. The turbulence effects are simulated using RNG κ-ε model. Flow analysis has been carried out for the non-reacting and reacting conditions. Meshing of the flow domain is done in GAMBIT. A detailed analysis of non-reacting flow in a 60°sector Afterburner from inlet to exit of the Afterburner is carried out in FLUENT solver code. The various thermodynamic properties are analyzed and presented along the length of the Afterburner. Three different combustion models viz. prePDF, eddy dissipation and finite rate/eddy dissipation model are used in order to predict the reacting flow. An experimental investigation of the three-dimensional confined flow fields behind a “V” shaped complex flame stabilizer in an isothermal model of an Afterburner is carried out to validate the CFD code. From the present study it is concluded that the prediction procedure adopted especially for non-reacting flow can be used with confidence in the development of an Afterburner at a lower cost. Since measurements were not possible under reacting conditions no attempt has been made for reacting flow validation.
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Analysis of non-reacting flow in an aircraft gas turbine engine Afterburner model using finite volume method
Indian Journal of Engineering and Materials Sciences, 2003Co-Authors: M. Rajkumar, V. GanesanAbstract:This paper focuses on the aerodynamics of the non-reacting flow inside an aero-gas turbine engine Afterburner by carrying out a three-dimensional CFD analysis using the finite volume approach. A 60° sector of the Afterburner with all the complexities has been modelled to take advantage of the symmetry of the design. The computational methodology employed SIMPLE algorithm for pressure velocity coupling, RNG k-E model for turbulence in an unstructured and non uniform grid. The analysis has been carried out for sea level inlet conditions. A recirculation zone was seen to be formed behind the V -gutters and inner wall of the diffuser. The performance of the diffuser was found to be good and the Mach number just upstream of the V -gutter was found to be in line with requirements. The pressure loss was in line with successful designs and the nozzle performance was found to be satisfactory . The predicted flow fields are verified using exi sting experimental results . The results for various mass flow rates and different geometries are presented for the closed nozzle position. Military turbojets require greater thrust during take off and high speed 'dogfight' manoeuvers. Various methods of thrust augmentation exist and the principle is to either increase the mass flow rate (by injection of water, water alcohol mixture or refrigerants) , or increase the energy (by burning fuel in the turbine exhaust or air bled from compressor). The constraining factor being space and weight, as also the cost, the Afterburner has become the universal choice for military turbojets. It fits into the tailpipe region and has the most favourable thrust to weight ratio. But the Afterburner also entails some penalty in the form of pressure losses (cold loss) when it is not in use as also the 'hot losses' when in use. The components required for achieving the design intent in an Afterburner also cause unavoidable pressure losses in the turbojet. A diffuser is provided at the turbine exit in order to decelerate the flow so as to allow combustion to initiate . Flame stabilizer is provided in order to ensure that proper combustion takes place and blowout of flame does not take place. The fuel manifolds are provided to supply the fuel into the combustion chamber. Supporting structures al so cause obstruction in the flow and cause pressure losses.
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Mean flow fields in a confined isothermal flow downstream of an Afterburner flame stabilizer
Indian Journal of Engineering and Materials Sciences, 1994Co-Authors: M. Ravichandran, V. GanesanAbstract:An experimental investigation of the three-dimensional confined flow fields behind a typical Afterburner flame stabilizer is presented. The flame stabilizer comprises of one main ring V-gutter with twelve outer and six inner radial V-gutters, concentrically placed within a cylindrical pipe. Photography of the woollen tufts on the inner, outer and ring V-gutters clearly demonstrate the recirculation zones formed behind each of them. Five-hole pitot probe measurements along the entire length of the cylinder in three different azimuthal planes, allow the determination of three mean velocity com-.ponents which provide comprehensive information to aid understanding of such complex flows. The time-mean velocity measurements presented here constitute a much needed data base for the validation of computer prediction codes and the development of turbulence models for th~ir simulation. Conventional jet engine Afterburners and ramjet ways been a serious challenge to the researchers engines employ bluff body flame stabilizers for worldwide and significant progress has also been anchoring flames. The separated recirculating achieved in the computation of both nonreacting 7 flow which is established in the lee of bluff bodies and reacting8 flows of a two~ring flame stabilizer can be used to stabilize flames in high velocity but they suffer from lack of experimental data for reacting streams. Lundin et a/.1 have presented validation. Lixing and Jian9 have presented two the performance of different shapes of flame st&- dimensional predictions and compared them with bilizers and the effects of different parameters like experiments, but have unfortunately chosen to gutter width, number of gutters, blockage, etc., on restrict attention to Afterburner diffuser part Afterburner performance. V-gutter flame stabiliz- alone, leaving out the flame stabilizer. Branstetter ,. ers are found to be a compromise in the objec- and Reckl0 have examined the Afterburner pertives of obtaining high combustion efficiency, high formance of circular V-gutters and a sector of altitude limits, and low pressure drop. The origin parallel V-gutters for a range of inlet temperatures or mechanism of sustenance of "screech" (this up to 1255 K and this study is mostly concerned phenomenon is a combustion instability charact- with evaluating combustion efficiency, lean blowerized by high frequency, high amplitude pressure out limits and the effect of fuel spray bar to oscillations, which will eventually lead to structu- V-gutter spacing. There have been detailed and i ral failure) is associated with the aerodynamics of accurate measurements of the velocity characterisI
Sangwook Ryu - One of the best experts on this subject based on the ideXlab platform.
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music with the urqmd Afterburner
Nuclear Physics, 2013Co-Authors: Sangwook Ryu, Sangyong Jeon, Charles Gale, Björn Schenke, Clint YoungAbstract:As RHIC is entering the precision measurement era and the LHC is producing a copious amount of new data, the role of 3+1D event-by-event viscous hydrodynamics is more important than ever to understand the bulk data as well as providing the background for hard probes. For more meaningful comparison with the experimental data, it is also important that hydrodynamics be coupled to the hadronic Afterburner. In this proceeding we report on preliminary results of coupling MUSIC with UrQMD.
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MUSIC with the UrQMD Afterburner
Nuclear Physics A, 2013Co-Authors: Sangwook Ryu, Sangyong Jeon, Charles Gale, Björn Schenke, Clint YoungAbstract:As RHIC is entering the precision measurement era and the LHC is producing a copious amount of new data, the role of 3+1D event-by-event viscous hydrodynamics is more important than ever to understand the bulk data as well as providing the background for hard probes. For more meaningful comparison with the experimental data, it is also important that hydrodynamics be coupled to the hadronic Afterburner. In this proceeding we report on preliminary results of coupling MUSIC with UrQMD.Comment: 4 pages, 6 figures in pdf. Submitted to the proceedings of the Quark Matter 2012 conference (August 13-18, 2012, Washington D.C.
Basharat Ali Haider - One of the best experts on this subject based on the ideXlab platform.
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Preliminary Design of a Short Afterburner for Single-Spool Expendable Turbojet Engine
49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2011Co-Authors: Basharat Ali Haider, Nikola Davidovi, Naveed DurraniAbstract:A theoretical study related to a short Afterburner design is presented in this paper. The objective is to enhance the performance of an existing single-spool expendable turbojet engine in terms of thrust, with a xed-area exit nozzle. The expendable turbojet engines are generally used in the reconnaissance air vehicles where the engine is positioned in the fuselage near the center of gravity. Consequently, a longer exhaust duct exists before of the nozzle section which can house a short Afterburner. An in-house FORTRAN language code is developed to evaluate the performance of single-spool expendable turbojet engine without Afterburner and the results of the code are validated with the available experimental data. A short Afterburner is designed based on the available length constraints. As a result of the limited length available for the Afterburner, combustion chamber has to be considerably shorter than those usually used in the Afterburners. Afterburner pressure loss and eciency is calculated iteratively by using Afterburner inlet conditions. It is found that by adding the designed short Afterburner, about 20% increase in the thrust is achieved at the expense of 50% increase in specic fuel consumption.
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Parametric Analysis of Expendable type Single-Spool Turbojet Engine with a Short Afterburner
49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2011Co-Authors: Basharat Ali Haider, Nikola Davidovic, Naveed DurraniAbstract:A parametric, on-design performance analysis of an existing single-spool expendable turbojet engine with a short Afterburner is presented in this paper. A design point mathematical model of the engine is developed to obtain the optimum system performance conditions. This model utilizes the engine design parameters, such as operating flight conditions, compressor pressure ratio, turbine inlet temperature and Afterburner exit temperature to predict the engine performance parameters, such as specific thrust and specific fuel consumption. The results obtained are in a good agreement with commercial software, GasTurb, used for the performance analysis of gas turbine engines and with the available experimental data. Subsequently, the effects of adding a short Afterburner on the performance of the engine were studied using a parametric analysis. A theoretical database for different performance parameters was obtained as a design reference for the future work.
