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  • 1
    ISSN: 1432-0967
    Source: Springer Online Journal Archives 1860-2000
    Topics: Geosciences
    Notes: Abstract A simple modification was made to the reaction vessel designed by Shaw (1963) in order to use it as a hydrogen sensor instead of a hydrogen source, thereby allowing a continuous record of $$f_{H_2 } $$ to be made during an experiment. The advantage of this arrangement is that (reversed) $$f_{O_2 - } T$$ curves for minerals can be generated from a single experimental run. Other applications are possible. This method was successfully used in the determination of the Ni-NiO-H2O equilibrium between 580 ° and 830 °C at 2 kbar fluid pressure. The corrected 1 atm values are in agreement with electrochemical measurements. An Ag70Pd30 hydrogen permeable membrane was used for the experiment and flow rates of hydrogen through the membrane were calculated by monitoring the rate of increase or decrease in pressure with an induction pressure transducer. These flow rates range up to two times greater than those calculated for a pure platinum membrane.
    Type of Medium: Electronic Resource
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  • 2
    ISSN: 1432-1157
    Source: Springer Online Journal Archives 1860-2000
    Topics: Geosciences
    Type of Medium: Electronic Resource
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  • 3
    ISSN: 1432-5225
    Source: Springer Online Journal Archives 1860-2000
    Topics: Agriculture, Forestry, Horticulture, Fishery, Domestic Science, Nutrition , Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: Summary In both Douglas-fir and aspen wood, the fiber saturation point of early wood is greater than that of late wood, solvent extraction lowers the fiber saturation point, and the fiber saturation point for reaction wood is less than that for whole wood.
    Type of Medium: Electronic Resource
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  • 4
    Publication Date: 2018-12-01
    Description: An experimental investigation of the three-dimensional flow field through a low aspect ratio, transonic, axial flow fan rotor has been conducted, using an advanced laser anemometer (LA) system. Laser velocimeter measurements of the rotor flow field at the design operating speed and over a range of throughflow conditions are compared to analytical solutions. The numerical technique used herein yields the solution to the full, three-dimensional, unsteady Euler equations using an explicit time-marching, finite volume approach. The numerical analysis, when coupled with a simplified boundary layer calculation, generally yields good agreement with the experimental data. The test rotor has an aspect ratio of 1.56, a design total pressure ratio of 1.629 and a tip relative Mach number of 1.38. The high spatial resolution of the LA data matrix (9 radial x 30 axial x 50 blade-to-blade) permits details of the transonic flow field such as shock location, turning distribution, and blade loading levels to be investigated and compared to analytical results.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 84-GT-200
    Format: text
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  • 5
    Publication Date: 2013-08-31
    Description: A users manual is presented for a computer program that prepares the bulk of the input data set required for the Denton three dimensional turbomachine blade row analysis code. The Denton input is generated from a minimum of geometry and flow variable information by using cubic spline curve fitting procedures. The features of the program are discussed. The input is described and special instructions are included to assist in its preparation. Sample input and output are included.
    Keywords: AERODYNAMICS
    Type: NAS 1.15:83324 , E-1565 , NASA-TM-83324
    Format: application/pdf
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  • 6
    Publication Date: 2013-08-31
    Description: A method was developed to improve the accuracy of an existing computer program used to calculate transonic velocities on a blade-to-blade surface of a turbomachine. The method eliminates problems encountered in obtaining solutions with the velocity gradient equation when large gradients in velocity occur through the blade row. With the improved method, results indicate that the transonic solution can be obtained by scaling the velocities obtained at the reduced mass flow rate where all velocities are subsonic thereby eliminating the need for a solution of the velocity gradient equation. Solutions obtained with the scaling method on a two dimensional compressor cascade and an axial turbine stator show good agreement with experimental data. The results obtained for the stationary blade rows and comparison of analytical results obtained with and without the present method suggest that the method will yield an improved solution for centrifugal compressor impellers.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1772 , E-128
    Format: application/pdf
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  • 7
    Publication Date: 2013-08-31
    Description: A 13.65 cm tip diameter backswept centrifugal impeller having a tandem inducer and a design mass flow rate of 0.907 kg/sec was experimentally investigated to establish stage and impeller characteristics. Tests were conducted with both a cascade diffuser and a vaneless diffuser. A pressure ratio of 5.9 was obtained near surge for the smallest clearance tested. Flow range at design speed was 6.3 percent for the smallest clearance test. Impeller exit to shroud axial clearance at design speed was varied to determine the effect on stage and impeller performance.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1091
    Format: application/pdf
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  • 8
    Publication Date: 2013-08-31
    Description: A conical-flow compressor stage with a large radius change through the rotor was tested at three values of rotor tip clearance. The stage had a tandem rotor and a tandem stator. Peak efficiency at design speed was 0.774 at a pressure ratio of 2.613. The rotor was tested without the stator, and detailed survey data were obtained for each rotor blade row. Overall peak rotor efficiency was 0.871 at a pressure ratio of 2.952.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2034 , NAS 1.60:2034 , E-369 , AVRADCOM-TR-81-C-5
    Format: application/pdf
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  • 9
    Publication Date: 2017-06-26
    Description: Spacecraft quasi-isotropic antenna system for space telemetry
    Keywords: COMMUNICATIONS
    Type: R-2870-3582-B , NASA-CR-68124
    Format: application/pdf
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  • 10
    Publication Date: 2017-10-02
    Description: An experimental and computational investigation of the NASA Low-Speed Centrifugal Compressor (LSCC) flow field was conducted using laser anemometry and Dawes' 3D viscous code. The experimental configuration consists of a back-swept impeller followed by a vaneless diffuser. Measurements of the three-dimensional velocity field were acquired at several measurement planes through the compressor. The measurements describe both the throughflow and secondary velocity field along each measurement plane and, in several cases, provide details of the flow within the blade boundary layers. The experimental and computational results provide a clear understanding of the development of the throughflow momentum wake which is characteristic of centrifugal compressors.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD, Technology Requirements for Small Gas Turbines; 11 p
    Format: text
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