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  • 1
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    Coefficient of Friction, Oil Flow and Heat Balance of a Full-Journal Bearing (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-28
    Schlagwort(e): Mechanical Engineering
    Materialart: AD-B204941 , NACA-TM-1165 , NASA-TM-111363 , NAS 1.15:111363
    Format: application/pdf
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  • 2
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    Cooling of Gas Turbines (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: A theoretical analysis of the radial temperature distribution through the rotor and constant cross sectional area blades near the coolant passages of liquid cooled gas turbines was made. The analysis was applied to obtain the rotor and blade temperatures of a specific turbine using a gas flow of 55 pounds per second, a coolant flow of 6.42 pounds per second, and an average coolant temperature of 200 degrees F. The effect of using kerosene, water, and ethylene glycol was determined. The effect of varying blade length and coolant passage lengths with water as the coolant was also determined. The effective gas temperature was varied from 2000 degrees to 5000 degrees F in each investigation.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-E7B11c
    Format: application/pdf
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  • 3
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    Cooling of Gas Turbines (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: A theoretical analysis of the cross-sectional temperature distribution of a water-cooled turbine blade was made using the relaxation method to solve the differential equation derived from the analysis. The analysis was applied to specific turbine blade and the studies icluded investigations of the accuracy of simple methods to determine the temperature distribution along the mean line of the rear part of the blade, of the possible effect of varying the perimetric distribution of the hot gas-to -metal heat transfer coefficient, and of the effect of changing the thermal conductivity of the blade metal for a constant cross sectional area blade with two quarter inch diameter coolant passages.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-E7B11F
    Format: application/pdf
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  • 4
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    Investigation of 10-Stage Axial-Flow X24C-2 Compressor (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: The performance at inlet pressure of 21 inches mercury absolute and inlet temperature of 538 R for the 10-stage axial-flow X24C-2 compressor from the X24C-2 turbojet engine was investigated. the peak adiabatic temperature-rise efficiency for a given speed generally occurred at values of pressure coefficient fairly close to 0.35.For this compressor, the efficiency data at various speeds could be correlated on two converging curves by the use of a polytropic loss factor derived.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-E7G11
    Format: application/pdf
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  • 5
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    Investigations of Compression Shocks and Boundary Layers in Gases Moving at High Speed (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: The mutual influences of compression shocks and friction boundary layers were investigated by means of high speed wind tunnels.Schlieren optics provided a clear picture of the flow phenomena and were used for determining the location of the compression shocks, measurement of shock angles, and also for Mach angles. Pressure measurement and humidity measurements were also taken into consideration.Results along with a mathematical model are described.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1113 , Mitteilungen aus dem Institut fuer Aerodynamik an der Eidgenoessischen Technischen Hochschule; 10
    Format: application/pdf
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  • 6
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    Investigation of Turbine of Mark 25 Torpedo Power Plant with Five Nozzle Designs (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: Efficiency investigations were made on the two-stage turbine from a Mark 25 aerial torpedo to determine the performance of the unit with five different turbine nozzles. The output of the turbine blades was computed by analyzing the windage and mechanical-friction losses of the unit. A method was developed for measuring the change in turbine clearances with changed operating conditions. The turbine was found to be most efficient with a cast nozzle having a sharp-edged inlet to the nine nozzle ports.
    Schlagwort(e): Mechanical Engineering
    Materialart: NACA-RM-E7I03
    Format: application/pdf
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  • 7
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    Comparison of Wind-Tunnel Predictions with Flight Measurements of the Longitudinal-Stability and -Control Characteristics of a Douglas BTD-1 Airplane (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: Low Mach number longitudinal-stability and control characteristics as predicted by use of wind tunnel data from a powered 3/16-scale model are compared with flight test measurements of a Navy BTD-1 airplane. The accuracy of the wind tunnel data and the discrepancies involved in attempting to correlate with flight data are discussed and analyzed. The comparison showed that wind tunnel predictions were, in general, in good agreement with flight test data. The predicted values were for the most part sufficiently accurate to show the satisfactory and unsatisfactory characteristics in the preliminary design stage and to indicate possible methods of improvement. The discrepancies which did occur were attributed principally to physical dissimilarities between model and airplane and the instability to determine accurately the flight power conditions. The effect of Mach number was considered negligible since the maximum flight test value was about 0.5. In order to simulate more closely the flight conditions and hence obtain more accurate data for predictions, it appears desirable to perform large-scale tests of unorthodox control surfaces such as the sealed vaned elevators with which the airplane was equipped.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-RM-A6L30
    Format: application/pdf
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  • 8
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    Temperatures and Stresses on Hollow Blades For Gas Turbines (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: The present treatise reports on theoretical investigations and test-stand measurements which were carried out in the BMW Flugmotoren GMbH in developing the hollow blade for exhaust gas turbines. As an introduction the temperature variation and the stress on a turbine blade for a gas temperature of 900 degrees and circumferential velocities of 600 meters per second are discussed. The assumptions onthe heat transfer coefficients at the blade profile are supported by tests on an electrically heated blade model. The temperature distribution in the cross section of a blade Is thoroughly investigated and the temperature field determined for a special case. A method for calculation of the thermal stresses in turbine blades for a given temperature distribution is indicated. The effect of the heat radiation on the blade temperature also is dealt with. Test-stand experiments on turbine blades are evaluated, particularly with respect to temperature distribution in the cross section; maximum and minimum temperature in the cross section are ascertained. Finally, the application of the hollow blade for a stationary gas turbine is investigated. Starting from a setup for 550 C gas temperature the improvement of the thermal efficiency and the fuel consumption are considered as well as the increase of the useful power by use of high temperatures. The power required for blade cooling is taken into account.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-TM-1183 , Forschungsbericht-1879 , Zentrale fuer Wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluftzeugmeisters Berlin-Adlershof
    Format: application/pdf
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  • 9
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    On the Vortex Sound from Rotating Rods (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: The motion of different bodies imersed in liquid or gaseous media is accompanied by characteristic sound which is excited by the formation of unstable surfaces of separation behind the body, usually disintegrating into a system of discrete vortices(such as the Karman vortex street due to the flow about an infintely long rod, etc.).In the noise from fans,pumps,and similar machtnery, vortexnQif3eI?Yequently predominates. The purpose of this work is to elucidate certain questions of the dependence ofthis sound upon the aerodynamic parameters and the tip speed of the rotating rods,or blades. Although scme material is given below,insufficientto calculate the first rough approximation to the solution of this question,such as the mechanics of vortex formation,never the less certain conclusions maybe found of practical application for the reduction of noise from rotating blades.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1136 , Zhurnal Tekhnicheskoi Fiziki; 14; 9; 561
    Format: application/pdf
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  • 10
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    The Elasto-Plastic Stability of Plates (1947)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: This article explains results developed from the following research: 'The Stability of Plates and Shells beyond the Elastic Limit.' A significant improvement is found in the derivation of the relations between the stress factors and the strains resulting from the instability of plates and shells. In a strict analysis, the problem reduces to the solution of two simultaneous nonlinear partial differential equations of the fourth order in the deflection and stress function, and in the approximate analysis to a single linear equation of the Bryan type. Solutions are given for the special cases of a rectangular plate buckling into a cylindrical form, and of an arbitrarily shaped plate under uniform compression. These solutions indicate that the accuracy obtained by the approximate method is satisfactory.
    Schlagwort(e): Structural Mechanics
    Materialart: NACA-TM-1188
    Format: application/pdf
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