Analysis of shock capturing methods for chemical species transport in unsteady compressible flow

This paper presents a chemical species transport model to account for variable composition and gas properties along the flow path in internal combustion engines. The numerical solution to adapt the gas dynamic model to chemical species transport in boundary conditions by means of the Method of Characteristics and in volumes by means of a filling and emptying model is described. The performance for chemical species transport in 1D elementsof shock-capturing methods, such as the two-step Lax Wendroff method and the Sweby s TVD scheme considering several flux limiter definitions, is carried out by means of shocktube tests. The influence of the fluid modelling as perfect or non-perfect gas on the numerical methods features and the flow characteristics on shock-tube results are analysed.This work has been partially supported by the Spanish Ministerio de Ciencia e Innovacion through grant number DPI2010-20891-C02-02.Serrano Cruz, JR.; Climent, H.; Piqueras, P.; García Afonso, Ó. (2013). Analysis of shock capturing methods for chemical species transport in unsteady compressible flow. Mathematical and Computer Modelling. 57(7-8):1751-1759. https://doi.org/10.1016/j.mcm.2011.11.026S17511759577-

Bibliography of Lewis Research Center technical publications announced in 1992

This compilation of abstracts describes and indexes the technical reporting that resulted from the scientific and engineering work performed and managed by the Lewis Research Center in 1992. All the publications were announced in the 1992 issues of STAR (Scientific and Technical Aerospace Reports) and/or IAA (International Aerospace Abstracts). Included are research reports, journal articles, conference presentations, patents and patent applications, and theses

Aeronautical engineering: A continuing bibliography with indexes (supplement 271)

This bibliography lists 666 reports, articles, and other documents introduced into the NASA scientific and technical information system in October, 1991. Subject coverage includes design, construction and testing of aircraft and aircraft engines; aircraft components, equipment and systems; ground support systems; and theoretical and applied aspects of aerodynamics and general fluid dynamics

A survey of computational aerodynamics in the United States

Programs in theoretical and computational aerodynamics in the United States are described. Those aspects of programs that relate to aeronautics are detailed. The role of analysis at various levels of sophistication is discussed as well as the inverse solution techniques that are of primary importance in design methodology. The research is divided into the broad categories of application for boundary layer flow, Navier-Stokes turbulence modeling, internal flows, two-dimensional configurations, subsonic and supersonic aircraft, transonic aircraft, and the space shuttle. A survey of representative work in each area is presented

Bibliography of Lewis Research Center technical publications announced in 1980

This compilation of abstracts describes and indexes over 780 research reports, journal articles, conference presentations, patents and patent applications, and theses resulting from the scientific and engineering work performed and managed by the Lewis Research Center in 1980. All the publications were announced in Scientific and Technical Aerospace Reports and/or International Aerospace Abstracts

Bibliography of Lewis Research Center Technical Publications announced in 1991

This compilation of abstracts describes and indexes the technical reporting that resulted from the scientific engineering work performed and managed by the Lewis Research Center in 1991. All the publications were announced in the 1991 issues of STAR (Scientific and Technical Aerospace Reports) and/or IAA (International Aerospace Abstracts). Included are research reports, journal articles, conference presentations, patents and patent applications, and theses

Bibliography of Lewis Research Center technical publications announced in 1984

This compilation of abstracts describes and indexes the technical reporting that resulted from the scientific and engineering work performed and managed by the Lewis Research Center in 1984. All the publications were announced in the 1984 issues of STAR (Scientific and Technical Aerospace Reports) and/or IAA (International Aerospace Abstracts). Included are research reports, journal articles, conference presentations, patents and patent applications, and theses

Aeronautical engineering: A continuing bibliography with indexes (supplement 270)

This bibliography lists 600 reports, articles, and other documents introduced into the NASA scientific and technical information system in September, 1991. Subject coverage includes: design, construction and testing of aircraft and aircraft engines; aircraft components, equipment and systems; ground support systems; and theoretical and applied aspects of aerodynamics and general fluid dynamics

Aeronautical engineering: A continuing bibliography with indexes (supplement 256)

This bibliography lists 426 reports, articles, and other documents introduced into the NASA scientific and technical information system in August 1990. Subject coverage includes: design, construction and testing of aircraft and aircraft engines; aircraft components, equipment and systems; ground support systems; and theoretical and applied aspects of aerodynamics and general fluid dynamics

Development of Novel Passive Control Techniques for More Uniform Temperature at Combustor Exit and Hybrid Les/Rans Modeling

Gas turbines have become an important, widespread, and reliable device in the field of power generation. For any gas turbine system, the combustor is an integral part responsible for the combustion of the fuel. A number of studies have shown that the flow field exiting a combustor is highly non-uniform in pressure, velocity and, most importantly, temperature. Hot streaks amongst other non-uniformities cause varying thermal stresses on turbine blades and put pressure on the blade materials. In particular, these non-uniformities can have detrimental effects on the performance of the engine and cause a reduction in the expected life of critical components such as the turbine vanes. Due to the importance and severity of the problem, a large portion of the total combustor development effort is devoted to achieving better temperature uniformity. The present work is another attempt to develop novel passive control techniques to enhance mixing in a facility simulating the dilution zone of a typical gas turbine combustor and produce more uniform temperature at the combustor exit. Extensive experimentation was conducted to compare the proposed dilution techniques - staggered dilution holes, staggered dilution holes with streamlined body and staggered dilution holes with guide vanes at various orientations (0°, 30°, 60° and 90°). A weighted parameter was defined called `uniformity factor (\u27χ^\u27 ) to compare how close the mixture fraction is to the equilibrium value. For the majority of the flow conditions tested, the 30° guide vanes gave the most uniform temperature flow with just about 2% higher pressure loss as compared to the staggered dilution holes geometry. The fact that the use of 30° guide vanes can provide the turbine blade with 15% more uniform temperature flow than the staggered dilution holes design with merely 2% more pressure drop, has a very important implementation in order to reduce the damage of the turbine blades due to non-uniform temperature flow and extend its life-span. This would result in an overall reduction in the maintenance cost of the gas turbine systems which is quite significant. Furthermore, it was found that the introduction of the streamlined body not only improved the mixing in some cases but also helped decrease the pressure drop from inlet to exit of the experimental set-up. This is expected to increase the overall system efficiency and decrease the operating cost of a gas turbine system. Additionally, numerical modeling was used for various parametric studies to explore the effect of jet-to-mainstream momentum flux ratio on the exit temperature uniformity, variation of the cooling rate within the dilution zone, exergy analysis, etc. The other significant part of this work comprised of development of an Algebraic Stress Model (ASM) in order to estimate the turbulence via Reynolds stresses prediction. The ASM model developed is validated for a simple two-dimensional turbulent flow over a flat plate and a complex three dimensional flow around Ahmed body. The developed model is capable of predicting Reynolds stresses for a variety of flow regimes. Based on these validation it can be concluded that adopting a hybrid approach which combines the advantages of the ASM model with other turbulence models can be sought after for a more in-depth analysis of the flow structures and turbulent quantities both near-wall and away from the boundary for any fluid flow problem. The accurate prediction of the turbulent quantities plays a significant role in not just the fluid motion/transfer phenomenon rather it governs the heat exchange process as well especially in regions close to the wall