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  • AIRCRAFT PROPULSION AND POWER  (6)
  • FLUID MECHANICS AND HEAT TRANSFER  (4)
  • Grid generation  (1)
  • 1
    Electronic Resource
    Electronic Resource
    Algebraic grid generation for complex geometries (1991)
    Chichester : Wiley-Blackwell
    International Journal for Numerical Methods in Fluids 13 (1991), S. 1-31 
    Details
    ISSN: 0271-2091
    Keywords: Grid generation ; Surface generation ; Engineering ; Engineering General
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: An efficient computer programme called GRID2D/3D has been developed to generate single and composite grid systems within geometrically complex two- and three-dimensional (2D and 3D) spatial domains that can deform with time. GRID2D/3D generates single grid systems by using algebraic grid generation methods based on transfinite interpolation. The distribution of grid points within the spatial domain is controlled by stretching functions and grid lines can intersect boundaries of the spatial domain orthogonally. GRID2D/3D generates composite grid systems by patching together two or more single grid systems. The patching can be discontinuous or continuous. For 2D spatial domains the boundary curves are constructed by using either cubic or tension spline interpolation. For 3D spatial domains the boundary surfaces are constructed by using a new technique, developed in this study, referred to as 3D bidirectional Hermite interpolation.
    Additional Material: 15 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/fld.1650130102
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Analytical combustion/emissions research related to the NASA High-Speed Research Program (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A combustion analysis program aimed at upgrading and applying advanced computer programs for gas turbine applications is discussed. 2D and 3D codes, KIVA-II and LeRC-3D, have been used to provide insight into the combustion process and combustor design. The computations performed through these codes show their capability to produce reasonable results, despite such deficiencies in the current models as accurate chemical kinetics modeling of hydrocarbon combustion and turbulence and turbulence combustion interaction modeling.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-2252
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Three-dimensional calculation of the mixing of radial jets from slanted slots with a reactive cylindrical crossflow (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A numerical model that calculates the 3D chemically reacting flowfield in an experimental low emission combustor is described. The ICEd-ALE finite volume computational methodology is employed in this study. Radial jets issuing from slanted slots interact with a cylindrical axially flowing mainstream to produce a bulk swirl velocity downstream of the slot region. The swirl pattern at a given axial station is composed of a clockwise rotating region near the wall and a counterclockwise rotating region extending from the combustor centerline. The jet radial penetration and downstream swirl velocity axial development are shown to depend principally on the jet-to-mainstream momentum flux ratio.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-2081
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Fluid flow and fuel-air mixing in a motored two-dimensional Wankel rotary engine (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The implicit-factored method of Beam and Warming was employed to obtain numerical solutions to the conservation equations of mass, species, momentum, and energy to study the unsteady, multidimensional flow and mixing of fuel and air inside the combustion chambers of a two-dimensional Wankel rotary engine under motored conditions. The effects of the following engine design and operating parameters on fluid flow and fuel-air mixing during the intake and compression cycles were studied: engine speed, angle of gaseous fuel injection during compression cycle, and speed of the fuel leaving fuel injector.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 86-1556
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Applied Analytical Combustion/emissions Research at the NASA Lewis Research Center - a Progress Report (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Emissions of pollutants from future commercial transports are a significant concern. As a result, the Lewis Research Center (LeRC) is investigating various low emission combustor technologies. As part of this effort, a combustor analysis code development program was pursued to guide the combustor design process, to identify concepts having the greatest promise, and to optimize them at the lowest cost in the minimum time.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-3338
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Effects of nozzle lip geometry on spray atomization and emissions advanced gas turbine combustors (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A parametric study is conducted to investigate the effect of nozzle lip geometry on nozzle fuel distribution, emissions and temperature distribution for a rich burn section of a rich burn/quick quench/lean burn combustor. It is seen that the nozzle lip geometry greatly affects the fuel distribution, emissions and temperature distribution. It is determined that at an equivalence ratio of 1.6 the NO concentration could be lowered by a factor greater than three by changing the nozzle lip geometry.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-2201
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Numerical simulation of the flow field and fuel sprays in an IC engine (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A two-dimensional model for axisymmetric piston-cylinder configurations is developed to study the flow field in two-stroke direct-injection Diesel engines under motored conditions. The model accounts for turbulence by a two-equation model for the turbulence kinetic energy and its rate of dissipation. A discrete droplet model is used to simulate the fuel spray, and the effects of the gas phase turbulence on the droplets is considered. It is shown that a fluctuating velocity can be added to the mean droplet velocity every time step if the step is small enough. Good agreement with experimental data is found for a range of ambient pressures in Diesel engine-type microenvironments. The effects of the intake swirl angle in the spray penetration, vaporization, and mixing in a uniflow-scavenged two-stroke Diesel engine are analyzed. It is found that the swirl increases the gas phase turbulence levels and the rates of vaporization.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: SAE PAPER 870599
    Format: text
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  • 8
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    Emissions reduction by varying the swirler airflow split in advanced gas turbine combustors (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A rich burn/quick mix/lean burn (RQL) combustor concept for reducing pollutant emissions is currently under investigation at the NASA Lewis Research Center. The current study investigates the effect of varying the mass flow rate split between the swirler passages for an equivalance ratio of 2.0 on fuel distribution, temperature distribution, and emissions for the fuel nozzle/rich burn section of an RQL combustor. It is seen that optimizing these parameters can substantially improve combustor performance and reduce combustor emissions. The optimal mass flow rate split for reducing NO(x) emissions based on the numerical study was the same as found by experiment.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ASME PAPER 92-GT-110 , ; 8 p.|ASME, International Gas Turbine and Aeroengine Congress and Exposition; Jun 01, 1992 - Jun 04, 1992; Cologne; Germany
    Format: text
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  • 9
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    Algebraic grid generation for complex geometries (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: An efficient computer program called GRID2D/3D has been developed to generate single and composite grid systems within geometrically complex two- and three-dimensional (2D and 3D) spatial domains that can deform with time. GRID2D/3D generates single grid systems by using algebraic grid generation methods based on transfinite interpolation. The distribution of grid points within the spatial domain is controlled by stretching functions and grid lines can intersect boundaries of the spatial domain orthogonally. GRID2D/3D generates composite grid systems by patching together two or more single grid systems. The patching can be discontinuous or continuous. For 2D spatial domains the boundary curves are constructed by using either cubic or tension spline interpolation. For 3D spatial domains the boundary surfaces are constructed by using a new technique, developed in this study, referred to as 3D bidirectional Hermite interpolation.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: International Journal for Numerical Methods in Fluids (ISSN 0271-2091); 13; 1-31
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Numerical simulation of a low-emission gas turbine combustor using KIVA-II (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: A modified version of the KIVA-II code was used to obtain a multidimensional numerical solution for the turbulent two-phase chemically reacting flows inside a staged turbine combustor (STC). The STC under consideration is equipped with an advanced airblast fuel nozzle and encompasses a fuel nozzle (FN), a rich-burn (RB) zone, a converging connecting pipe, a quick-quench (QQ) zone, a diverging connecting pipe, and a lean-combustion (LC) zone. The STC was divided into two subsystems, namely, FN/RB zone and QQ/LC zones, and the numerical solutions were obtained separately for each subsystem. Preliminary data characterize the major features of the flow and temperature fields inside the STC. Information on velocity, temperature, and some critical species in the FN/RB zone is presented. In the QQ/LC zones, formation of the co- and counter-rotating bulk flow and the sandwiched-ring-shaped temperature field can be clearly seen. The calculations of the mass-weighted standard deviation and the pattern factor of temperature indicated that the mixing performance of the STC is very promising.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: International Journal for Numerical Methods in Fluids (ISSN 0271-2091); 15; 8; p. 865-881.
    Format: text
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    NASA TECHNICAL REPORTS
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