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  • AIRCRAFT PROPULSION AND POWER  (3)
  • Aircraft Propulsion and Power; Aircraft Design, Testing and Performance  (1)
  • Biochemistry and Biotechnology  (1)
  • Engineering General  (1)
Collection
Keywords
Publisher
Years
  • 1
    Electronic Resource
    Electronic Resource
    Hydrophobic chromatography of β-galactosidase (1980)
    New York, NY [u.a.] : Wiley-Blackwell
    Biotechnology and Bioengineering 22 (1980), S. 377-399 
    Details
    ISSN: 0006-3592
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The hydrophobic interaction of β-galactosidase with Sepharose 4B substituted with 3,3′-diaminodipropylamine was studied in both batch and column experiments. The equilibrium and the binding rate constants were determined for different phosphate buffer concentrations. The equilibrium constants exhibit a hysteresis effect, i.e., desorption constants are less than adsorption constants, and the higher the ionic strength to start the desorption, the larger the effect. The rate data are not satisfactorily described by a simple reversible first-order model. The column chromatographic data are semiquantitatively described by a local equilibrium theory without axial dispersion or intraparticle diffusion.
    Additional Material: 11 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/bit.260220211
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    Paper (German National Licenses)
    Fulltext
  • 2
    Electronic Resource
    Electronic Resource
    Non-linear seismic response and liquefaction (1978)
    New York, NY [u.a.] : Wiley-Blackwell
    International Journal for Numerical and Analytical Methods in Geomechanics 2 (1978), S. 381-404 
    Details
    ISSN: 0363-9061
    Keywords: Engineering ; Engineering General
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Architecture, Civil Engineering, Surveying , Geosciences
    Notes: The essential cause of the growth of pore pressure during cyclic loading is identified as an ‘autogenous’ shrinkage or densification of the solid phase of the soil and this is related to a strain path parameter. Introduction of this ‘shrinkage’ coupled with an elasto-plastic behaviour of the soil skeleton allows a full non-linear dynamic analysis to be conducted up to the point of structural failure for any earthquake input. Explicit time marching procedures are used. The procedure outlined is applicable to all problems of complex geometry and for conditions of undrained or partially drained behaviour at a moderate computational cost.
    Additional Material: 11 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/nag.1610020407
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    Paper (German National Licenses)
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  • 3
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    An Assessment of Combustion Dynamics in a Low-Nox, Second-Generation Swirl-Venturi Lean Direct Injection Combustion Concept (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Dynamic pressure measurements were taken during flame-tube emissions testing of three second-generation swirl-venturi lean direct injection (SV-LDI) combustor configurations. These measurements show that combustion dynamics were typically small. However, a small number of points showed high combustion dynamics, with peak-to-peak dynamic pressure fluctuations above 0.5 psi. High combustion dynamics occurred at low inlet temperatures in all three SV-LDI configurations, so combustion dynamics were explored further at low temperature conditions. A point with greater than 1.5 psi peak-to-peak dynamic pressure fluctuations was identified at an inlet temperature of 450!F, a pressure of 100 psia, an air pressure drop of 3%, and an overall equivalence ratio of 0.35. This is an off design condition: the temperature and pressure are typical of 7% power conditions, but the equivalence ratio is high. At this condition, the combustion dynamics depended strongly on the fuel staging. Combustion dynamics could be reduced significantly without changing the overall equivalence ratio by shifting the fuel distribution between stages. Shifting the fuel distribution also decreased NOx emissions.
    Keywords: Aircraft Propulsion and Power; Aircraft Design, Testing and Performance
    Type: ISABE-2015-20249 , GRC-E-DAA-TN27192 , 2015 International Society for Air Breathing Engines (ISABE); Oct 26, 2015 - Oct 30, 2015; Phoenix, AZ; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Comparison of reacting and non-reacting shear layers at a high subsonic Mach number (1993)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The flow field in a hydrogen-fueled planar reacting shear layer was measured with an LDV system and is compared with a similar air to air case without combustion. Measurements were made with a speed ratio of 0.34 with the highspeed stream at Mach 0.71. They show that the shear layer with reaction grows faster than one without, and both cases are within the range of data scatter presented by the established database. The coupling between the streamwise and the cross-stream turbulence components inside the shear layer is slow, and reaction only increased it slightly. However, a more organized pattern of the Reynolds stress is present in the reacting shear layer, possibly as a result of larger scale structure formation in the layer associated with heat release.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-106198 , E-7905 , NAS 1.15:106198 , AIAA PAPER 93-2381 , Joint Propulsion Conference and Exhibit; Jun 28, 1993 - Jun 30, 1993; Monterey, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Modern CFD applications for the design of a reacting shear layer facility (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The RPLUS2D code, capable of calculating high speed reacting flows, was adopted to design a compressible shear layer facility. In order to create reacting shear layers at high convective Mach numbers, hot air streams at supersonic speeds, rendered by converging-diverging nozzles, must be provided. A finite rate chemistry model is used to simulate the nozzle flows. Results are compared with one-dimensional solutions at chemical equilibrium. Additionally, a two equation turbulence model with compressibility effects was successfully incorporated with the RPLUS code. The model was applied to simulate a supersonic shear layer. Preliminary results show favorable comparisons with the experimental data.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-104523 , E-6396 , NAS 1.15:104523 , AIAA PAPER 91-0577 , Aerospace Sciences Meeting; Jan 07, 1991 - Jan 10, 1991; Reno, NV; United States
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    NASA TECHNICAL REPORTS
  • 6
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    A planar reacting shear layer system for the study of fluid dynamics-combustion interaction (1989)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A versatile planar reacting shear layer facility is constructed at NASA-Lewis. The research objectives, as well as design, instrumentations and the operational procedures developed for the system are described. The fundamental governing equations and the type of quantitative information that are needed from experiments are described. Additionally, a review of earlier work is presented. Whenever appropriate, comparisons are made with similar systems in other facilities and the main differences are described. Finally, the nonintrusive measurement techniques (PLIF, PMS, LDV, and Schlieren photography) and the type of experiments that are planned are described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-102422 , E-5063 , NAS 1.15:102422 , AVSCOM-TR-89-C-013 , AD-A233938 , International Symposium on Combustion; Jul 22, 1990 - Jul 27, 1990; Orleans; France
    Format: application/pdf
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