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  • Polymer and Materials Science  (2,521)
  • Inorganic Chemistry  (816)
  • AIRCRAFT PROPULSION AND POWER  (270)
  • 1975-1979  (3,607)
  • 1977  (3,607)
Collection
Keywords
Publisher
Years
  • 1975-1979  (3,607)
Year
  • 1
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    New materials for high temperature turbines; ONERA's DS composites confronted with blade problems (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: ONERA's refractory DS composites were cited as materials required for use in advanced aircraft turbines, operating at high temperatures. These materials were found to be reliable in the construction of turbine blades. Requirements for a blade material in aircraft turbines operating at higher temperatures were compared with the actual performance as found in COTAC DS composite testing. The structure and properties of the more fully developed 74 and 741 types were specified. High temperature structural stability, impact of thermal and mechanical fatigue, oxidation resistance and coating capability were thoroughly evaluated. The problem of cooling passages in DS eutectic blades is also outlined.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75216 , High Temp. Probl. in Gas Turbine Eng.; 19-23 Sept. 1977; Ankara
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    High temperature corrosion-resistant protective coatings in stationary gas turbines (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Methods currently used to deposit protective coatings in gas turbines are reviewed, and the structure of the respective coatings is examined. The corrosion behavior of such coatings is discussed on the basis of experimental data. General trends in the preparation of protective coatings are noted.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75181 , Tagung in Verbundwerkstoffe; Mar 28, 1974 - Mar 29, 1974; Constance; Germany
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Aerodynamic investigation of an air-cooled axial-flow turbine. Part 2: Rotor blade tip-clearance effects on overall turbine performance and internal gas flow conditions: Experimental results and prediction methods (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Total turbine blade performance was investigated while changing the blade tip clearance in three ways. The internal flow at the moving blade outlet point was measured. Experimental results were compared with various theoretical methods. Increased blade clearance leads to decreased turbine efficiency.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75138
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Eight-bladed propeller design could bring back turboprop airplanes (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: P77-10204 , NASA-NEWS-RELEASE-77-206
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Protection of cooled blades of complex internal structure (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: The problem of general protection of cooled blades of complex internal structure was solved by a method called SF technique which makes possible the protection of both external and internal surfaces, as well as those of the orifices of cooling air, whatever their diameter. The SF method is most often applied in the case of pack process, at controlled or high activity; it can be of use on previously uncoated parts, but also on pieces already coated by a thermochemical, chemical or PVD method. The respective thickness of external and internal coatings may be precisely predetermined, no parasitic particle being liable to remain inside the parts after application of the protecting treatment. Results obtained to date by application of this method are illustrated by the presentation and examination of a various selection of advanced turbo engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75217 , AGARD-CP-229 , Conf. on High Temp. Probl. in Gas Turbine Engines; Sep 19, 1977 - Sep 23, 1977; Ankara
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Effect of Flame Stabilizer Design on Performance and Exhaust Pollutants of a Two-Row Swirl-Can Combustor Operated to Near-Stoichiometric Conditions (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Emissions and performance characteristics were determined for two full annulus modular combustors operated to near stoichiometric fuel air ratios. The tests were conducted to obtain stoichiometric data at inlet air temperatures from 756 to 894 K and to determine the effects of a flat plate circular flame stabilizer with upstream fuel injection and a contraswirl flame stabilizer with downstream fuel injection. Levels of unburned hydrocarbons were below 0.50 gram per kilogram of fuel for both combustors and thus there was no detectable difference in the two methods of fuel injection. The contraswirl flame stabilizer did not produce the level of mixing obtained with a flat plate circular flame stabilizer. It did produce higher levels of oxides of nitrogen, which peaked at a fuel air ratio of 0.037. For the flat plate circular flame stabilizer, oxides of nitrogen emission levels were still increasing with fuel air ratio to the maximum tested value of 0.045.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3495 , E-8317
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Reducing secondary losses by blowing cold air in a turbine (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Local blowing on the profile suction side of the turbine guide wheel blades can be effective in preventing the propagation of secondary flows that is, the transport of casing and hub boundary layers by pressure gradients. Some preliminary results on how the blowing should be accomplished in order to influence the secondary flows in the desired manner are given. The effectiveness of blowing is demonstrated. Blowing is also seen to be more effective than using boundary layer slots as far as diminishing losses in the rim zones is concerned.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75185 , PAPER-76-164 , DGLR Jahrestagung; Sep 14, 1976 - Sep 16, 1976; Munich
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Effects of film injection on performance of a cooled turbine (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Some of the most dramatic increases in the performance of turbojet and turbofan aircraft engines have been obtained as a result of increased thermodynamic cycle temperatures made possible by the use of film cooling techniques. The realization of the potential performance gains, however, is only possible if the quantity of cooling air and the aerodynamic mixing losses resulting from the injection of coolant in the form of film on the flowpath surfaces are minimized. Such a minimization requires a more complete understanding of the relationship between cooling and aerodynamics. A review is conducted of tests which have been conducted to determine the effects of coolant injection on turbine performance. The results obtained in the tests are compared with an analytical technique developed for predicting coolant injection effects. Particular attention is given to the effects of turbine cooling on overall cycle thermodynamic efficiency, taking into account incremental changes in turbine thermodynamic efficiency for various incremental changes in coolant flow rate.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Propulsion and Energetics Panel Meeting; Sept. 19-23, 1977; Ankara; Turkey
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    State-of-the-art of turbofan engine noise control (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A description is presented of some of the recent advances in the technology of turbofan engine noise reduction, taking into account turbomachinery noise sources, new fans for low noise, fan and core noise suppression, and a new program for improving static noise testing of fans and engines. The problem of jet noise has been substantially reduced in connection with the lower jet velocities employed in the case of the high bypass turbofan engines. The dominant noise sources are now related to the turbomachinery with the fan stage, the compressor, and the turbine. Since the fan stage is the primary source of turbomachinery noise, it has been considered in a major part of the investigations designed to reduce turbofan engine noise.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: In: NOISE-CON 77; National Conference on Noise Control Engineering; Oct 17, 1977 - Oct 19, 1977; Hampton, VA
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Effect of airstream velocity on mean drop diameters of water sprays produced by pressure and air atomizing nozzles (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A scanning radiometer was used to determine the effect of airstream velocity on the mean drop diameter of water sprays produced by pressure atomizing and air atomizing fuel nozzles used in previous combustion studies. Increasing airstream velocity from 23 to 53.4 meters per second reduced the Sauter mean diameter by approximately 50 percent with both types of fuel nozzles. The use of a sonic cup attached to the tip of an air assist nozzle reduced the Sauter mean diameter by approximately 40 percent. Test conditions included airstream velocities of 23 to 53.4 meters per second at 293 K and atmospheric pressure.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Winter Annual Meeting; Nov 27, 1977 - Dec 02, 1977; Atlanta, GA
    Format: text
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    NASA TECHNICAL REPORTS
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