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  • Organic Chemistry  (363)
  • AIRCRAFT PROPULSION AND POWER  (278)
  • 1975-1979  (447)
  • 1955-1959  (194)
  • 1
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    Laboratory studies of lean combustion (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The fundamental processes controlling lean combustion were observed for better understanding, with particular emphasis on the formation and measurement of gas-phase pollutants, the stability of the combustion process (blowout limits), methods of improving stability, and the application of probe and optical diagnostics for flow field characterization, temperature mapping, and composition measurements. The following areas of investigation are described in detail: (1) axisymmetric, opposed-reacting-jet-stabilized combustor studies; (2) stabilization through heat recirculation; (3) two dimensional combustor studies; and (4) spectroscopic methods. A departure from conventional combustor design to a premixed/prevaporized, lean combustion configuration is attractive for the control of oxides of nitrogen and smoke emissions, the promotion of uniform turbine inlet temperatures, and, possibly, the reduction of carbon monoxide and hydrocarbons at idle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 417-436
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    The effect of ambient conditions on the emissions of an idling gas turbine (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Changes in ambient conditions - pressure, temperature, and humidity - affect the exhaust emissions of a gas turbine engine. Such variations must be compensated for during engine certification. The results of a test program employing a JT8D-17 combustor are presented which quantize the effect of carefully controlled changes on unburned hydrocarbons, carbon monoxide, and oxides of nitrogen at simulated idle operating conditions. Analytical results are given to explain the observed hydrocarbon and carbon monoxide behavior. It is shown that for a complete range of possible ambient variations, significant changes do occur in the amount of pollutants emitted by an idling gas turbine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-3 , Aerospace Sciences Meeting; Jan 16, 1978 - Jan 18, 1978; Huntsville, AL
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Fuel-conservative engine technology (1975)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: Aircraft fuel consumption is discussed in terms of its efficient use, and the conversion of energy from sources other than petroleum. Topics discussed include: fuel from coal and oil shale, hydrogen deficiency of alternate sources, alternate fuels evaluation program, and future engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 157-190
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    General aviation piston-engine exhaust emission reduction (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: To support the promulgation of aircraft regulations, two airports were examined, Van Nuys and Tamiami. It was determined that the carbon monoxide (CO) emissions from piston-engine aircraft have a significant influence on the CO levels in the ambient air in and around airports, where workers and travelers would be exposed. Emissions standards were set up for control of emissions from aircraft piston engines manufactured after December 31, 1979. The standards selected were based on a technologically feasible and economically reasonable control of carbon monoxide. It was concluded that substantial CO reductions could be realized if the range of typical fuel-air ratios could be narrowed. Thus, improvements in fuel management were determined as reasonable controls.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Eng. Emissions; p 243-275
    Format: application/pdf
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  • 5
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    TF34 engine compression system computer study (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The stability of the fan and the compressor components was examined individually using linearized and time dependent, one dimensional stability analysis techniques. The stability of the fan core integrated compression system was investigated using a two dimensional compression system model. The analytical equations on which this model was based satisfied the mass, axial momentum, radial momentum, and energy conservation equations for flow through a finite control volume. The results gave an accurate simulation of the flow through the compression system. The speed lines of the components were reproduced; the points of instability were accurately predicted; the locations where the instability was initiated in the fan and the core were indicated; and the variation of the bypass ratio during flow throttling was calculated. The validity of the analytical techniques was then established by comparing these results with test data and with results obtained from the steady state cycle deck.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159889 , R78AEG612
    Format: application/pdf
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  • 6
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    Redundant disc (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A rotatable disc is described that consists of parallel plates tightly joined together for rotation about a hub. Each plate is provided with several angularly projecting spaced lands. The lands of each plate are interposed in alternating relationship between the lands of the next adjacent plate. In this manner, circumferential displacement of adjacent sectors in any one plate is prevented in the event that a crack develops. Each plate is redundantly sized so that, in event of structural failure of one plate, the remaining plates support a proportionate share of the load of the failed plate. The plates are prevented from separating laterally through the inclusion of generally radially extending splines which are inserted to interlock cooperating, circumferentially adjacent lands.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Format: application/pdf
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  • 7
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    Blade row dynamic digital compression program. Volume 2: J85 circumferential distortion redistribution model, effect of Stator characteristics, and stage characteristics sensitivity study (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of dynamic digital blade row compressor model studies of a J85-13 engine are reported. The initial portion of the study was concerned with the calculation of the circumferential redistribution effects in the blade-free volumes forward and aft of the compression component. Although blade-free redistribution effects were estimated, no significant improvement over the parallel-compressor type solution in the prediction of total-pressure inlet distortion stability limit was obtained for the J85-13 engine. Further analysis was directed to identifying the rotor dynamic response to spatial circumferential distortions. Inclusion of the rotor dynamic response led to a considerable gain in the ability of the model to match the test data. The impact of variable stator loss on the prediction of the stability limit was evaluated. An assessment of measurement error on the derivation of the stage characteristics and predicted stability limit of the compressor was also performed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134953 , R76AEG484-VOL-2
    Format: application/pdf
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  • 8
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    Aircraft gas turbine low-power emissions reduction technology program (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Advanced aircraft turbine engine combustor technology was used to reduce low-power emissions of carbon monoxide and unburned hydrocarbons to levels significantly lower than those which were achieved with current technology. Three combustor design concepts, which were designated as the hot-wall liner concept, the recuperative-cooled liner concept, and the catalyst converter concept, were evaluated in a series of CF6-50 engine size 40 degree-sector combustor rig tests. Twenty-one configurations were tested at operating conditions spanning the design condition which was an inlet temperature and pressure of 422 K and 304 kPa, a reference velocity of 23 m/s and a fuel-air-ration of 10.5 g/kg. At the design condition typical of aircraft turbine engine ground idle operation, the best configurations of all three concepts met the stringent emission goals which were 10, 1, and 4 g/kg for CO, HC, and Nox, respectively.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135434 , DOC-R78AEG408
    Format: application/pdf
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  • 9
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    Advanced optical blade tip clearance measurement system (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An advanced electro-optical system was developed to measure single blade tip clearances and average blade tip clearances between a rotor and its gas path seal in an operating gas turbine engine. This system is applicable to fan, compressor, and turbine blade tip clearance measurement requirements, and the system probe is particularly suitable for operation in the extreme turbine environment. A study of optical properties of blade tips was conducted to establish measurement system application limitations. A series of laboratory tests was conducted to determine the measurement system's operational performance characteristics and to demonstrate system capability under simulated operating gas turbine environmental conditions. Operational and environmental performance test data are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159402 , FR-10200A
    Format: application/pdf
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  • 10
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    Augmentor emissions reduction technology program (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Technology to reduce pollutant emissions from duct-burner-type augmentors for use on advanced supersonic cruise aircraft was investigated. Test configurations, representing variations of two duct-burner design concepts, were tested in a rectangular sector rig at inlet temperature and pressure conditions corresponding to takeoff, transonic climb, and supersonic cruise flight conditions. Both design concepts used piloted flameholders to stabilize combustion of lean, premixed fuel/air mixtures. The concepts differed in the flameholder type used. High combustion efficiency (97%) and low levels of emissions (1.19 g/kg fuel) were achieved. The detailed measurements suggested the direction that future development efforts should take to obtain further reductions in emission levels and associated improvements in combustion efficiency over an increased range of temperature rise conditions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135215 , R77AEG593
    Format: application/pdf
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