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  • 1
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    Advanced Measurement Systems Available to PIWG Members (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: It was developed advanced measurement technologies to meet NASA goals: reduce design cycle time, reduce emission, reduce testing time, increase safety. The technology are saving money. This technology are available now for technology transfer: optical diagnostics, the film technology and MEMS devices.
    Keywords: Instrumentation and Photography
    Type: PIWG Road Show, GEAE; May 25, 2000; Cleveland, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Non-Intrusive Laser-Induced Imaging for Speciation and Patternation in High Pressure Gas Turbine Combustors (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The next generation of was turbine combustors for aerospace applications will be required to meet increasingly stringent constraints on fuel efficiency, noise abatement, and emissions. The power plants being designed to meet these constraints will operate at extreme conditions of temperature and pressure, thereby generating unique challenges to the previously employed diagnostic methodologies. Current efforts at NASA Glenn Research Center (GRC) utilize optically accessible, high pressure flametubes and sector combustor rigs to probe, via advanced nonintrusive laser techniques, the complex flowfields encountered in advanced combustor designs. The fuel-air mixing process is of particular concern for lowering NO(x) emissions generated in lean, premixed engine concepts. Using planar laser-induced fluorescence (PLIF) we have obtained real-time, detailed imaging of the fuel spray distribution for a number of fuel injector over a wide range of operational conditions that closely match those expected in the proposed propulsion systems. Using a novel combination of planar imaging, of fuel fluorescence and computational analysis that allows an examination of the flowfield from any perspective, we have produced spatially and temporally resolved fuel-air distribution maps. These maps provide detailed insight into the fuel injection at actual conditions never before possible, thereby greatly enhancing the evaluation of fuel injector performance and combustion phenomena.
    Keywords: Instrumentation and Photography
    Type: NASA/TM-1999-209395 , NAS 1.15:209395 , E-11829 , Optical Diagnostics for Fluids, Heat, Combustion, and Photomechanics of Solids; Jul 18, 1999 - Jul 23, 1999; Denver, CO; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Non-Intrusive, Laser-Based Imaging of Jet-A Fuel Injection and Combustion Species in High Pressure, Subsonic Flows (2001)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The emphasis of combustion research efforts at NASA Glenn Research Center (GRC) is on collaborating with industry to design and test gas-turbine combustors and subcomponents for both sub- and supersonic applications. These next-generation aircraft combustors are required to meet strict international environmental restrictions limiting emissions. To meet these goals, innovative combustor concepts require operation at temperatures and pressures far exceeding those of cur-rent designs. New and innovative diagnostic tools are necessary to characterize these flow streams since existing methods are inadequate. The combustion diagnostics team at GRC has implemented a suite of highly sensitive, nonintrusive optical imaging methods to diagnose the flowfields of these new engine concepts. By using optically accessible combustors and flametubes, imaging of fuel and intermediate combustion species via planar laser-induced fluorescence (PLIF) at realistic pressures are now possible. Direct imaging of the fuel injection process through both planar Mie scattering and PLIF methods is also performed. Additionally, a novel combination of planar fuel fluorescence imaging and computational analysis allows a 3-D examination of the flowfield, resulting in spatially and temporally resolved fuel/air volume distribution maps. These maps provide detailed insight into the fuel injection process at actual conditions, thereby greatly enhancing the evaluation of fuel injector performance and other combustion phenomena. Stable species such as CO2, O2, N2O. and hydrocarbons are also investigated by a newly demonstrated 1-D, spontaneous Raman spectroscopic method. This visible wavelength Raman technique allows the acquisition of quantitative. stable species concentration measurements from the flow.
    Keywords: Instrumentation and Photography
    Type: NASA/TM-2001-211113 , E-12960 , NAS 1.15:211113 , 37th Combustion Subcommittee Meeting; Nov 13, 2000 - Nov 17, 2000; Monterey, CA; United States|25th Airbreathing Propulsion Subcommitte Meeting; Nov 13, 2000 - Nov 17, 2000; Monterey, CA; United States|19th Propulsion Systems Hazards Subcommittee Meeting; Nov 13, 2000 - Nov 17, 2000; Monterey, CA; United States|Joint First Modeling and Simulation Subcommittee Meeting; Nov 13, 2000 - Nov 17, 2000; Monterey, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Laser-Based Flowfield Imaging in a Lean Premixed Prevaporized Sector Combustor (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: OH and fuel planar laser-induced fluorescence (PLIF) is used qualitatively in this study to observe the flame structure resultant from different fuel injector dome configurations within the 3-cup sector combustor test rig. The fluorescence images are compared with some computational fluid dynamics (CFD) results. Interferences in obtaining OH fluorescence signals due to the emission of other species are assessed. NO PLIF images are presented and compared to gas analysis results. The comparison shows that PLIF NO can be an excellent method for measuring NO in the flame. Additionally, we present flow visualization of the molecular species C2.
    Keywords: Instrumentation and Photography
    Type: NASA/TM-2005-213402 , E-14909
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Combustion Temperature Measurement by Spontaneous Raman Scattering in a Jet-A Fueled Gas Turbine Combustor Sector (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Spontaneous vibrational Raman scattering was used to measure temperature in an aviation combustor sector burning jet fuel. The inlet temperature ranged from 670 K (750 F) to 756 K (900 F) and pressures from 13 to 55 bar. With the exception of a discrepancy that we attribute to soot, good agreement was seen between the Raman-derived temperatures and the theoretical temperatures calculated from the inlet conditions. The technique used to obtain the temperature uses the relationship between the N2 anti-Stokes and Stokes signals, within a given Raman spectrum. The test was performed using a NASA-concept fuel injector and Jet-A fuel over a range of fuel/air ratios. This work represents the first such measurements in a high-pressure, research aero-combustor facility.
    Keywords: Instrumentation and Photography
    Type: NASA/TM-2002-211588 , NAS 1.15:211588 , E-13373
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Rotational Raman-Based Temperature Measurements in a High-Velocity Turbulent Jet (2017)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: No abstract available
    Keywords: Instrumentation and Photography
    Type: NASA/TM-2017-219504/SUPPL , E-19366 , MSFC-E-DAA-TN40888
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Neural Network for Image-to-Image Control of Optical Tweezers (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A method is discussed for using neural networks to control optical tweezers. Neural-net outputs are combined with scaling and tiling to generate 480 by 480-pixel control patterns for a spatial light modulator (SLM). The SLM can be combined in various ways with a microscope to create movable tweezers traps with controllable profiles. The neural nets are intended to respond to scattered light from carbon and silicon carbide nanotube sensors. The nanotube sensors are to be held by the traps for manipulation and calibration. Scaling and tiling allow the 100 by 100-pixel maximum resolution of the neural-net software to be applied in stages to exploit the full 480 by 480-pixel resolution of the SLM. One of these stages is intended to create sensitive null detectors for detecting variations in the scattered light from the nanotube sensors.
    Keywords: Instrumentation and Photography
    Type: NASA/TM-2004-213201 , E-14710 , 2004 Annual Meeting; Aug 02, 2004 - Aug 06, 2004; Denver, CO; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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