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  • 1
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    Emission reduction (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-07-16
    Beschreibung: Control of the gaseous pollutant emissions of aircraft engines is considered in terms of the emission standards for six classes of aircraft engines. Emphasis is placed on combustor design concepts to significantly reduce emissions levels and lean-burning techniques to lower flame temperature, to reduce the oxides of nitrogen in the gaseous emissions.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Aeropropulsion 1979; p 59-84
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 2
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    An experimental investigation of radiative properties of aluminum oxide particles. (1972)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: The radiative properties of aluminum oxide at high temperatures were determined at various wavelengths. Absorption cross-sections of aluminum oxide particles averaged over a particle size distribution were determined by measuring the radiative emission from the particles in a flame and by determining the particle number density and size distribution from measurements of the scattering of laser light incident on the particles in this flame. From these values of average absorption cross-section, the imaginary part of the refractive index was deduced. Results indicate that the absorption cross-section and the imaginary part of the refractive index increase as the temperature increases in the range from 1920 to 2610 K, and that these properties decrease with increasing wavelength in the interval from 0.35 to 1.2 micron, indicating a nongray-body behavior.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Journal of Quantitative Spectroscopy and Radiative Transfer; 12; Nov. 197
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 3
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    Assessment, development, and application of combustor aerothermal models (1989)
    In:  CASI
    Details
    Publikationsdatum: 2013-08-31
    Beschreibung: The gas turbine combustion system design and development effort is an engineering exercise to obtain an acceptable solution to the conflicting design trade-offs between combustion efficiency, gaseous emissions, smoke, ignition, restart, lean blowout, burner exit temperature quality, structural durability, and life cycle cost. For many years, these combustor design trade-offs have been carried out with the help of fundamental reasoning and extensive component and bench testing, backed by empirical and experience correlations. Recent advances in the capability of computational fluid dynamics codes have led to their application to complex 3-D flows such as those in the gas turbine combustor. A number of U.S. Government and industry sponsored programs have made significant contributions to the formulation, development, and verification of an analytical combustor design methodology which will better define the aerothermal loads in a combustor, and be a valuable tool for design of future combustion systems. The contributions made by NASA Hot Section Technology (HOST) sponsored Aerothermal Modeling and supporting programs are described.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Toward Improved Durability in Advanced Aircraft Engine Hot Sections; p 23-37
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 4
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    Aerothermal modeling program, phase 2 (1984)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: The accuracy and utility of current aerothermal models for gas turbine combustors must be improved. Three areas of concern are identified: improved numerical methods for turbulent viscous recirculating flows; flow interaction; and fuel injector-air swirl characterization. Progress in each area is summarized.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Turbine Engine Hot Section Technology, 1984; 4 p
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 5
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    Combustion research for gas turbine engines (1985)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-19
    Beschreibung: Research on combustion is being conducted at Lewis Research Center to provide improved analytical models of the complex flow and chemical reaction processes which occur in the combustor of gas turbine engines and other aeropropulsion systems. The objective of the research is to obtain a better understanding of the various physical processes that occur in the gas turbine combustor in order to develop models and numerical codes which can accurately describe these processes. Activities include in-house research projects, university grants, and industry contracts and are classified under the subject areas of advanced numerics, fuel sprays, fluid mixing, and radiation-chemistry. Results are high-lighted from several projects.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 6
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    Emissions control for ground power gas turbines (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: The similarities and differences of emissions reduction technology for aircraft and ground power gas turbines is described. The capability of this technology to reduce ground power emissions to meet existing and proposed emissions standards is presented and discussed. Those areas where the developing aircraft gas turbine technology may have direct application to ground power and those areas where the needed technology may be unique to the ground power mission are pointed out. Emissions reduction technology varying from simple combustor modifications to the use of advanced combustor concepts, such as catalysis, is described and discussed.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Aircraft Eng. Emissions; p 203-242
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 7
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    Detailed fuel spray analysis techniques (1984)
    In:  CASI
    Details
    Publikationsdatum: 2017-10-02
    Beschreibung: Fuel spray analyses which are a necessary input to the analytical modeling of the complex mixing and combustion processes which occur in advanced combustor systems are discussed. It is anticipated that by controlling fuel air reaction conditions, combustor temperatures can be better controlled, leading to improved combustion system durability. The capability to measure liquid droplet size, velocity, and number density throughout a fuel spray and to utilize this measurement technique in laboratory benchmark experiments was demonstrated. The experiment to characterize fuel sprays is described. The experiments and data are useful for application to and validation of turbulent flow modeling to improve the design systems of future advanced technology engines.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: AGARD Combust. Probl. in Turbine Eng. 10p (SEE N84-24732 15-25)
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 8
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    Future fundamental combustion research for aeropropulsion systems (1985)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Physical fluid mechanics, heat transfer, and chemical kinetic processes which occur in the combustion chamber of aeropropulsion systems were investigated. With the component requirements becoming more severe for future engines, the current design methodology needs the new tools to obtain the optimum configuration in a reasonable design and development cycle. Research efforts in the last few years were encouraging but to achieve these benefits research is required into the fundamental aerothermodynamic processes of combustion. It is recommended that research continues in the areas of flame stabilization, combustor aerodynamics, heat transfer, multiphase flow and atomization, turbulent reacting flows, and chemical kinetics. Associated with each of these engineering sciences is the need for research into computational methods to accurately describe and predict these complex physical processes. Research needs in each of these areas are highlighted.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: AIAA PAPER 85-1398
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 9
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    Future fundamental combustion research for aeropropulsion systems (1985)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Physical fluid mechanics, heat transfer, and chemical kinetic processes which occur in the combustion chamber of aeropropulsion systems were investigated. With the component requirements becoming more severe for future engines, the current design methodology needs the new tools to obtain the optimum configuration in a reasonable design and development cycle. Research efforts in the last few years were encouraging but to achieve these benefits research is required into the fundamental aerothermodynamic processes of combustion. It is recommended that research continues in the areas of flame stabilization, combustor aerodynamics, heat transfer, multiphase flow and atomization, turbulent reacting flows, and chemical kinetics. Associated with each of these engineering sciences is the need for research into computational methods to accurately describe and predict these complex physical processes. Research needs in each of these areas are highlighted.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-TM-87049 , E-2612 , NAS 1.15:87049 , USAAVSCOM-TR-85-C-11 , AD-A158778 , AIAA PAPER 85-1398 , Joint Propulsion Conf.; Monterey, CA; United States
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 10
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    Factors affecting altitude relight performance of a double-annular ram-induction combustor (1972)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A test program was conducted to evaluate the altitude relight capabilities of a short-length, double-annular, ram-induction combustor which was designed for Mach 3 cruise operation. The use of distorted inlet-air flow profiles was tried to evaluate their effect on the relight performance. No significant improvement in altitude relight performance was obtained with this approach. A study was also made to determine the effects of the reference Mach number, the fuel temperature, and the fuel volatility (ASTM-A1 against JP-4) on the altitude relight performance. Decreasing the reference Mach number, increasing the fuel temperature, and using more volatile fuel all decrease the combustor pressure necessary for relight.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-2630 , E-6788
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
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