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  • Industrial Chemistry  (233)
  • Fluid Mechanics and Heat Transfer  (25)
  • 1985-1989
  • 1960-1964  (258)
  • 1960  (258)
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Publisher
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  • 1985-1989
  • 1960-1964  (258)
Year
  • 1
    Publication Date: 2019-08-17
    Description: Photographs are presented of various models coated with fluorescent oil to show evidence of surface vortices at a Mach number of 3.03. Vortex formation was evidently present on models with forward-facing steps, rearward-facing steps, wires, discrete surface particles, or unswept flat surfaces with sharp leading edges. Some photographs are also presented for the models coated with a sublimation material which clearly indicates the location of boundary-layer transition; however, it does not show the vortices as clearly as the fluorescent oil. The study was made on the models at an angle of attack of 0 deg at unit Reynolds numbers of 7.7 and 10.7 million per foot. The spacing of the vortices as indicated by the flow studies on the unswept model was smaller at the higher Reynolds number in accordance with Gortler's theory. The flow studies also indicated that stable surface vortices produced by either steps or surface roughness persisted over model areas known to have turbulent boundary layers.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-328
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  • 2
    Publication Date: 2019-08-17
    Description: An investigation was conducted in the Ames 12-Foot Low-Turbulence Pressure Tunnel to determine the effects of sweep on the boundary-layer stability characteristics of an untapered variable-sweep wing having an NACA 64(2)A015 section normal to the leading edge. Pressure distribution and transition were measured on the wing at low speeds at sweep angles of 0, 10, 20, 30, 40, and 50 deg. and at angles of attack from -3 to 3 deg. The investigation also included flow-visualization studies on the surface at sweep angles from 0 to 50 deg. and total pressure surveys in the boundary layer at a sweep angle of 30 deg. for angles of attack from -12 to 0 deg. It was found that sweep caused premature transition on the wing under certain conditions. This effect resulted from the formation of vortices in the boundary layer when a critical combination of sweep angle, pressure gradient, and stream Reynolds number was attained. A useful parameter in indicating the combined effect of these flow variables on vortex formation and on beginning transition is the crossflow Reynolds number. The critical values of crossflow Reynolds number for vortex formation found in this investigation range from about 135 to 190 and are in good agreement with those reported in previous investigations. The values of crossflow Reynolds number for beginning transitions were found to be between 190 and 260. For each condition (i.e., development of vortices and initiation of transition at a given location) the lower values in the specified ranges were obtained with a light coating of flow-visualization material on the surface. A method is presented for the rapid computation of crossflow Reynolds number on any swept surface for which the pressure distribution is known. From calculations based on this method, it was found that the maximum values of crossflow Reynolds number are attained under conditions of a strong pressure gradient and at a sweep angle of about 50 deg. Due to the primary dependence on pressure gradient, effects of sweep in causing premature transition are generally first encountered on the lower surfaces of wings operating at positive angles of attack.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-338
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  • 3
    Publication Date: 2019-08-17
    Description: A configuration of a wing segment having constant chord thickness, 0 deg. sweep, a porous steel semicircular leading edge, and solid Inconel surfaces was tested in a Mach number 2.0 ethlyene-heated high-temperature air jet. Measurements were made of the wing surface temperatures at chordwise stations for several rates of helium flow through the porous leading edge. The investigation was conducted at stagnation temperatures ranging from 500 F to 2,400 F, at Reynolds numbers per foot ranging from 0.3 x 10(exp 7) to 1.2 x 10(exp 7), and at angles of attack of 0, +/- 5, and +/- 15 deg. The results indicated that the reduction of wing surface temperatures with respect to their values for no coolant flow, depended on the helium coolant flow rates and the distance behind the area of injection. The results were correlated in terms of the wall cooling parameter and the coolant flow-rate parameter, where the nondimensional flow rate was referenced to the cooled area up to the downstream position. For the same coolant flow rate, lower surface temperatures are achieved with a porous-wall cooling system. However, since flow-rate requirements decrease with increasing allowable surface temperatures, the higher allowable wall temperatures of the solid wall as compared to the structurally weaker porous wall- sharply reduce the flow-rate requirements of a downstream cooling system. Thus, for certain flight conditions it is possible to compensate for the lower efficiency of the downstream or solid-wall cooling system. For example, a downstream cooling system using solid walls that must be maintained at 1,800 F would require less coolant for Mach numbers up to 5.5 than would a porous-wall cooling system for which the walls must be maintained at temperatures less than or equal to 9000 F.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TM-X-235
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  • 4
    Publication Date: 2019-08-16
    Description: A study was made to determine the effect of coolant injection angularity on gaseous film-cooling effectiveness. In the correlation of experimental data an effective injection angle was defined by a vector summation of the coolant and mainstream gas flows. The cosine of this angle was used as a parameter to empirically develop a corrective term to qualify a correlating equation presented in Technical Note D-130 that was limited to tangential injection of the coolant. Data were also obtained for coolant injection through rows of holes normal to the test plate. The slot correlating equation was adapted to fit these data by the definition of an effective slot height. An additional corrective term was then determined to correlate these data.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-299 , E-689
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  • 5
    Publication Date: 2019-08-16
    Description: Measurements of the time-averaged induced velocities were obtained for rotor tip speeds as great as 1,100 feet per second (tip Mach number of 0.98) and measurements of the instantaneous induced velocities were obtained for rotor tip speeds as great as 900 feet per second. The results indicate that the small effects on the wake with increasing Mach number are primarily due to the changes in rotor-load distribution resulting from changes in Mach number rather than to compressibility effects on the wake itself. No effect of tip Mach number on the instantaneous velocities was observed. Under conditions for which the blade tip was operated at negative pitch angles, an erratic circulatory flow was observed.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-393 , L-836
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  • 6
    Publication Date: 2019-08-15
    Description: A review is made of some of the experimental data and analyses applicable to convective heat transfer in fully turbulent flow in smooth tubes with liquid metals and viscous Newtonian fluids. An empirical equation is evolved that closely approximates heat-transfer values obtained from selected analyses and experimental data for Prandtl numbers from 0.001 to 1000. The terms included in the equation are Reynolds number, Prandtl number, and an empirical diffusivity ratio between heat and momentum.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-483
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  • 7
    Publication Date: 2019-08-15
    Description: The experimental and analytical results to date of a study of a two-component gaseous vortex system are presented in this paper. Analytical expressions for tangential velocity and static-pressure profiles in a turbulent vortex show good agreement with experimental data. Airflow rates from 0.075 to 0.14 pound per second and corresponding tangential velocities from 160 to 440 feet per second are correlated by turbulent Reynolds numbers from 1.95 to 2.4. An analysis of an air-bromine gas mixture in a turbulent vortex indicates that a boundary value of bromine-to-air radial velocity ratio (u(2)/u(1)) of 0.999 gives essentially no bromine buildup, while a value of 0.833 results in considerable separation. For a constant value of (u(2)/u(1))(0) the bromine buildup increases as (1) the tangential velocity increases, (2) the air-to-bromine weight-flow ratio decreases, (3) the airflow rate decreases, (4) the temperature decreases, and (5) the turbulence decreases. Analytical temperature, pressure, and tangential-velocity profiles are also presented. Preliminary experimental results indicate that the flow of an air-bromine mixture through a vortex field results in a bromine density increase to a maximum value; followed by a decrease; the air density exhibits a uniform decrease from the outer vortex radius to the exhaust-nozzle radius.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-288 , E-800 , Nov 16, 1959 - Nov 21, 1959; Washington, DC; United States
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  • 8
    Publication Date: 2019-08-15
    Description: A series of rocket motors with varying exit to throat area ratios was tested in the 8- by 6-foot wind tunnel to determine the effects of mixing on jet diameter and temperature decay at large distances (x/d 〉 30) from the nozzle exit. An approximate method to account for effects of the initial expansion was evolved. It was determined that the combustion efficiency has an important effect on jet spreading, since the unburned products can burn downstream of the nozzle. The data showed considerable scatter; however, mixing rates were, in general, lower than those observed for subsonic jets. Data for angles of attack of 5 and 10 deg are also presented, giving the respective centerline shift and temperature decay as a function of axial distance.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TM-X-151
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  • 9
    Publication Date: 2019-08-15
    Description: Induced discharges are advantageous for ionizing low-density flows in that they introduce no electrode contamination into the flow and they provide a relatively high degree of ionization with good coupling of power into the gas. In this investigation a 40-megacycle oscillator was used to produce and maintain induced discharges in argon and mercury-vapor flows. Methods for preventing blowout of the discharge were determined, and power measurements were made with an in-line wattmeter. Some results with damped oscillations pulsed at 1,000 pulses per second are also presented.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-431 , L-986
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  • 10
    Publication Date: 2019-08-15
    Description: An investigation of laminar boundary-layer control by suction for purposes of drag reduction at low speed and high Reynolds numbers has been conducted in the Ames 12-Foot Pressure Wind Tunnel. The model was a 72.96-inch-chord wing panel, swept back 30 deg., which was installed between end plates to approximate a wing of infinite span. The airfoil section employed was a modified NACA 66-012 in the streamwise direction. Tests were limited to controlling the flow over only the upper surface of the model. Seventeen individually controllable suction chambers were provided below the surface to induce flow through 93 spanwise slots in the surface between the 0.0052- and 0.97-chord stations. Tests were made at angles of attack of 0 deg., +/- 1.0 deg., +/- 1.5 deg., and -2.0 deg. for Reynolds numbers from approximately 1.5 x 10(exp 6) to 4.0 x 10(exp 6) per foot. In general, essentially full-chord laminar flow was obtained for all conditions with small suction quantities. Minimum profile-drag coefficients of about 0.0005 to 0.0006 were obtained for the slotted surface at maximum values of the Reynolds number; these values include the Power required to induce suction as an equivalent drag.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-320
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  • 11
    Publication Date: 2019-08-15
    Description: The real-gas hypersonic flow parameters for helium have been calculated for stagnation temperatures from 0 F to 600 F and stagnation pressures up to 6,000 pounds per square inch absolute. The results of these calculations are presented in the form of simple correction factors which must be applied to the tabulated ideal-gas parameters. It has been shown that the deviations from the ideal-gas law which exist at high pressures may cause a corresponding significant error in the hypersonic flow parameters when calculated as an ideal gas. For example the ratio of the free-stream static to stagnation pressure as calculated from the thermodynamic properties of helium for a stagnation temperature of 80 F and pressure of 4,000 pounds per square inch absolute was found to be approximately 13 percent greater than that determined from the ideal-gas tabulation with a specific heat ratio of 5/3.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-462 , L-1135
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  • 12
    Publication Date: 2019-08-15
    Description: Hovering and steady low-speed forward-flight tests were run on a 4-foot-diameter rotor at a ground height of 1 rotor radius. The two blades had a 2 to 1 taper ratio and were mounted in a see-saw hub. The solidity ratio was 0.05. Measurements were made of the rotor rpm, collective pitch, and forward-flight velocity. Smoke was introduced into the tip vortex and the resulting vortex pattern was photographed from two positions. Using the data obtained from these photographs, wire models of the tip vortex configurations were constructed and the distribution of the normal component of induced velocity at the blade feathering axis that is associated with these tip vortex configurations was experimentally determined at 450 increments in azimuth position from this electromagnetic analog. Three steady-state conditions were analyzed. The first was hovering flight; the second, a flight velocity just under the wake "tuck under" speed; and the third, a flight velocity just above this speed. These corresponded to advance ratios of 0, 0.022, and 0.030 (or ratios of forward velocity to calculated hovering induced velocity of approximately 0, 0.48, and 0.65), respectively, for the model test rotor. Cross sections of the wake at 450 intervals in azimuth angle as determined from the path of the tip vortex are presented graphically for all three cases. The nondimensional normal component of the induced velocity that is associated with the tip vortex as determined by an electromagnetic analog at 450 increments in azimuth position and at the blade feathering axis is presented graphically. It is shown that the mean value of this component of the induced velocity is appreciably less after tuck-under than before. It is concluded that this method yields results of engineering accuracy and is a very useful means of studying vortex fields.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-458 , W-143
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  • 13
    Publication Date: 2019-08-15
    Description: A semiempirical analysis of the equation for incompressible fluctuations in a turbulent fluid, using similarity relations for round subsonic jets with uniform exit velocity, is used to predict the shape of the time-averaged fluctuation-pressure distribution along the mean-velocity boundary of jets. The predicted distribution is independent of distance downstream of the nozzle exit along the mixing region, inversely proportional to the distance downstream along the region of mean-velocity self-preservation, and proportional to the inverse square of the distance downstream along the fully developed region. Experimental results were in fair agreement with the theory. However, the measured fluctuation-pressure distributions were found to be very sensitive to changes in jet temperature and jet-nozzle profile, especially near the nozzle. These factors are not included in the theory. Increased jet temperatures produce increased pressure fluctuations and violation of similarity conditions. Nozzle-profile modifications may lead to violation of the uniform-exit-velocity requirement imposed in the theory.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-468 , E-780
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  • 14
    Publication Date: 2019-08-15
    Description: The sonic-wedge characteristics method has been used to obtain the shock shapes and surface pressure distributions on several blunt two-dimensional shapes in a hypersonic stream for several values of the ratio of specific heats. These shapes include the blunt slab at angle of attack and power profiles of the form yb = a)P, where 0 les than m less than 1, Yb and x are coordinates of the body surface, and a is a constant. These numerical results have been compared with the results of blast-wave theory, and methods of predicting the pressure distributions and shock shapes are proposed in each case. The effects of a free-stream conical-flow gradient on the pressure distribution on a blunt slab in hypersonic flow were investigated by the sonic-wedge characteristics method and were found to be sizable in many cases. Procedures which are satisfactory for reducing pressure data obtained in conical flows with small gradients are presented.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-408 , L-897
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  • 15
    Publication Date: 2019-08-15
    Description: It is shown that adequate means are available for calculating inviscid direct and induced pressures on simple axisymmetric bodies at zero angle of attack. The extent to which viscous effects can alter these predictions is indicated. It is also shown that inviscid induced pressures can significantly affect the stability of blunt, two-dimensional flat wings at low angles of attack. However, at high angles of attack, the inviscid induced pressure effects are negligible.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-449 , L-1051
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  • 16
    Publication Date: 2019-08-15
    Description: Convective heat-transfer tests were made on a 5-inch-diameter hemisphere to determine the variation of Stanton number with the ratio of wall temperature to total temperature. The tests were made at a nominal Mach number of 2 for stagnation temperatures of 760 deg R, 1,030 deg R, and 1,380 deg R. The model was constructed so that radiation effects and also streamwise conduction effects within the model skin were minimized. The results of the tests verified that these effects were small. Tests which were made with different masses of air inside the model to check for conduction effects to the internal air cavity showed these effects to be negligible. For laminar flow on the hemisphere, the Stanton number remained essentially constant as the ratio of wall temperature to total temperature increased. However, for fully established turbulent flow, the Stanton number at some stations decreased on the order of 50 percent as the ratio of wall temperature to total temperature increased. A theory which agreed fairly well with the trend of this decrease is shown for comparison.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-399 , L-463
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  • 17
    Publication Date: 2019-08-15
    Description: An experimental investigation has been made in the Langley highspeed hydrodynamics facility to determine the force and moment characteristics of two hydrofoils (one having an aspect ratio of 1 and the other having an aspect ratio of 3) designed to have improved lift-drag ratios when operating under either supercavitating or ventilated conditions. Measurements were made of lift, drag, and pitching moment over a range of angles of attack from 40 to 200 for depths of submersion varying from 0 to approximately 1 chord. The range of speed for the investigation was from 110 to 200 feet per second. When the upper surface of the hydrofoils was completely unwetted, the experimental values of lift and drag forces were in good agreement with the theoretical values obtained from the zero-cavitation-number theory. The theoretical values for minimum angle of attack for operation with the upper surface of the hydrofoil unwetted define the lower limits of angle of attack for which the experimental values of lift coefficient are either in agreement with or slightly greater than those predicted by theory.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-436 , L-913
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  • 18
    Publication Date: 2019-08-15
    Description: An experimental investigation was conducted to evaluate the heat-transfer characteristics of a hypersonic glide configuration having 79.5 deg of sweepback (measured in the plane of the leading edges) and 45 of dihedral. The tests were conducted at a nominal Mach number of 4.95 and a stagnation temperature of 400 F. The test-section unit Reynolds number was varied from 1.95 x 10(exp 6) to 12.24 x 10(exp 6) per foot. The results indicated that the laminar-flow heat-transfer rate to the lower surface of the model decreased as the distance from the ridge line increased except for thermocouples located near the semispan at an angle of attack of 00 with respect to the plane of the leading edges. The heat-transfer distribution (local heating rate relative to the ridge-line heating rate) was similar to the theoretical heat-transfer distribution for a two-dimensional blunt body, if the ridge line was assumed to be the stagnation line, and could be predicted by this theory provided a modified Newtonian pressure distribution was used. Except in the vicinity of the apex, the ridge-line heat-transfer rate could also be predicted from two-dimensional blunt-body heat-transfer theory provided it was assumed that the stagnation-line heat-transfer rate varied as the cosine of the effective sweep (sine of the angle of attack of the ridge line). The heat-transfer level on the lower surface and the nondimensional heat-transfer distribution around the body on the lower surface were in qualitative agreement with the results of a geometric study of highly swept delta wings with large positive dihedrals made in reference 1.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TM-X-247
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  • 19
    Publication Date: 2019-08-15
    Description: The results are presented for a flight test program using a fighter type jet aircraft flying at pressure altitudes of 10,000, 20,000, and 30,000 feet at Mach numbers from 0.3 to 0.8. Specially designed apparatus was used to measure and record the output of microphones and hot-wire anemometers mounted on the forward-fuselage section and wing of the airplane. Mean-velocity profiles in the boundary layers were obtained from total-pressure measurements. The ratio of the root-mean-square fluctuating wall pressure to the free-stream dynamic pressure is presented as a function of Reynolds number and Mach number. The longitudinal component of the turbulent-velocity fluctuations was measured, and the turbulence-intensity profiles are presented for the wing and forward-fuselage section. In general, the results are in agreement with wind-tunnel measurements which have been-reported in the literature. For example, the variation the square root of p(sup 2)/q times the square root of p(sup 2) is the root mean square of the wall-pressure fluctuation, and q is the free-stream dynamic pressure) with Reynolds number was found to be essentially constant for the forward-fuselage-section boundary layer, while variations at the wing station were probably unduly affected by the microphone diameter (5/8 in.), which was large compared with the boundary-layer thickness.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-280
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  • 20
    Publication Date: 2019-08-15
    Description: The laminar compressible boundary layer in the two-dimensional and axisymmetric stagnation regions has been analyzed to show the effects of the injection of a radiation absorbing foreign gas on an incident radiation field, and on the enthalpy profiles across the boundary layer. Total heat transfer to the stagnation region is evaluated for numerous cases and the results are compared with the no shielding case. Required absorption properties of the foreign gas are determined and compared with properties of known gases.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-329
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  • 21
    Publication Date: 2019-08-16
    Description: The spatial characteristics of a spray formed by two impinging water jets in quiescent air were studied over a range of nominal jet velocities of 30 to 74 feet per second. The total included angle between the 0.089-inch jets was 90 deg. The jet velocity, spray velocity, disappearance of the ligaments just before drop formation, mass distribution, and size and position of the largest drops were measured in a circumferential survey around the point of jet impingement. Photographic techniques were used in the evaluations. The distance from the point of jet impingement to ligament breakup into drops was about 4 inches on the spray axis and about 1.3 inches in the radial position +/-90 deg from the axis. The distance tended to increase slightly with increase in jet velocity. The spray velocity varied from about 99 to about 72 percent of the jet velocity for a change in circumferential position from the spray axis to the +/-80 deg positions. The percentages tended to increase slightly with an increase in jet velocity. Fifty percent of the mass was distributed about the spray axis in an included angle of slightly less than 40 deg. The effect of jet velocity was small. The largest observed drops (2260-micron or 0.090-in. diam.) were found on and about the spray axis. The size of the largest drops decreased for an increase in radial angular position, being about 1860 microns (0.074 in.) at the +/-90 deg positions. The largest drop sizes tended to decrease for an increase in jet velocity, although the velocity effect was small. A drop-size distribution analysis indicated a mass mean drop size equal to 54 percent of an extrapolated maximum drop size.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-301 , E-419
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  • 22
    Publication Date: 2019-08-16
    Description: The results are reported of hot-wire anemometer measurements of the fluctuating longitudinal component of the turbulent velocities in the mean flow downstream of screens in an air jet. These measurements have been analyzed by well-established techniques to give the influence of tile screen mesh size on the turbulent intensity, scale, and the power-spectral-density. The results show a linear dependence of the intensity upon the screen mesh size for locations within the central core of the air jet. The spectral-density curves show that the screens redistribute the turbulent energy from the low frequencies (〈1000 cps) to the high frequencies (〉1000 cps). The effects of the screens are overwhelmed in the mixing region of the jet flow by the turbulence levels existing there. The large pressure drops occurring across the screens reduce the velocity of the jet as compared to the jet without screens by approximately one-third for the velocity and range of mesh sizes investigated and reported in this report. The turbulence scale is a linear function of distance from the nozzle exit and is somewhat greater than comparable jets without screens.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-297 , E-798
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  • 23
    Publication Date: 2019-08-16
    Description: Measurements of the location of boundary-layer transition and the local heat transfer have been made on 2-inch-diameter hemispheres in the Langley gas dynamics laboratory at a Mach number of 4.95, a Reynolds number per foot of 73.2 x 10(exp 6), and a stagnation temperature of approximately 400 F. The transient-heating thin-skin calorimeter technique was used, and the initial values of the wall-to-stream stagnation- temperature ratios were 0.16 (cold-model tests) and 0.65 (hot-model test). During two of the four cold tests, the boundary-layer flow changed from turbulent to laminar over large regions of the hemisphere as the model heated. On the basis of a detailed consideration of the magnitude of roughness possibly present during these two cold tests, it appears that this destabilizing effect of low wall temperatures (cooling) was not caused by roughness as a dominant influence. This idea of a decrease in boundary-layer stability with cooling has been previously suggested. (See, for example, NASA Memorandum 10-8-58E.) For the laminar data obtained during the early part of the hot test, the correlation of the local-heating data with laminar theory was excellent.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-391 , L-752
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  • 24
    Publication Date: 2019-08-16
    Description: The problem of noise suppression of turbojet engines has shown a need for turbulence data within the flow field of various types of nozzles used in ad hoc investigations of the sound power. The result of turbulence studies in a nozzle configuration of four parallel rectangular slots is presented in this report with special attention to the effect of the spacing of the nozzles on the intensity of turbulence, scale of turbulence, spectrum of turbulence, and the mean stream velocity. Taylor's hypothesis, which describes the convection of the turbulence eddies, was tested and found correct within experimental error and certain experimental and theoretical limitations. The convection of the pressure patterns was also investigated, and the value of the convection velocity was found to be about 0.43 times the central core velocity of the jets. The effect of the spacing-to-width ratio of the nozzles upon the turbulence intensity, the scale of turbulence, and the spectral distribution of the noise was found in general to produce a maximum change for spacing-to-width ratios of 1.5 to 2.0. These changes may be the cause of the reduction in sound power reported for similar full-scale nozzles and test conditions under actual (static) engine operation. A noise reduction parameter is defined from Lighthill's theory which gives qualitative agreement with experiments which show the noise reduction is greatest for spacing-to-width ratios of 1.5 to 2.0.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-294 , E-384
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  • 25
    Publication Date: 2019-08-16
    Description: A full-scale wind-tunnel test was conducted of two boundary-layer-control applications to a 44-foot diameter helicopter rotor. Blowing from a nozzle near the leading edge of the blades delayed retreating blade stall. Results also indicated that delay of retreating blade stall could be obtained by cyclic blowing with a lower flow rate than that required for continuous blowing. It was found that blowing applied through a nozzle at mid-chord had no effect on retreating blade stall.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-335 , A-380
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  • 26
    Electronic Resource
    Electronic Resource
    Weinheim : Wiley-Blackwell
    Chemie Ingenieur Technik - CIT 32 (1960), S. 630-633 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Additional Material: 6 Ill.
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  • 27
    Electronic Resource
    Electronic Resource
    Weinheim : Wiley-Blackwell
    Chemie Ingenieur Technik - CIT 32 (1960), S. 635-636 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
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  • 28
    Electronic Resource
    Electronic Resource
    Weinheim : Wiley-Blackwell
    Chemie Ingenieur Technik - CIT 32 (1960) 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
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  • 29
    Electronic Resource
    Electronic Resource
    Weinheim : Wiley-Blackwell
    Chemie Ingenieur Technik - CIT 32 (1960), S. 641-650 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Synthese und Analyse sind die integrierenden Arbeitsweisen der Chemie. Die synthetischen Methoden gestatten, aus bekannten, meist einfacheren Stoffen kompliziertere Verbindungen aufzubauen, wobei die Arbeitsschritte i. allg. auf Analogieschlüssen zu bereits durchgeführten Synthesen beruhen. Der Erfolg einer Synthese wird mittels analytischer Methoden verfolgt, sei es, daß die stofflichen Umsätze bestimmt, sei es, daß die Reaktionsprodukte nach Art, Menge und Molekülstruktur erfaßt werden sollen. Nimmt man zu den Analysen synthetischer Produkte noch die naturgegebener Substanzen und Prozesse hinzu, so ist das gesamte Betätigungsgebiet für analytische Arbeiten umrissen, nämlich Methoden zu finden und zu erproben, die gestatten, Bestandteile von Stoffen und Stoffgemischen qualitativ zu erkennen, quantitativ zu bestimmen und ihre makroskopische, mikroskopische oder auch molekulare Struktur aufzuklären.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 669-674 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Es wird ein robustes Gleichlichtgerät mit positiver Filterung und Selbstkompensation der nicht-selektiven Strahlungseinflüsse beschrieben, das bei guter Konstanz des Nullpunktes und der Empfindlichkeit relativ wartungsarm arbeitet und sich daher für Betriebsmessungen eignet.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 695-696 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: In Bezugselektroden Ag/AgCl zur Bestimmung von Potentialen in Salzschmelzen läßt sich Silber durch silbergefüllten Graphit oder Silber-Graphit-Keramik ersetzen. Diese Werkstoffe zeigen in der Schmelze eine bessere Formkonstanz, da der thermochemische Effekt des Silbers unterdrückt wird.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 685-691 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Maßgebend für das Verhalten eines Thermostaten ist seine Totzeit und Zeitkonstante. Neben indirekten Verfahren der Temperaturregelung kommt bei den direkten Verfahren den einfachen und robusten Zweipunktreglern besondere Bedeutung zu, die aber nicht beliebig begrenzbare Regelschwingungen ausführen. Der Zweipunktregler läßt sich durch empfindlichere Meßschaltungen, Kompensation der Totzeit durch Rückführungen und Dämpfungsglieder nach Tian verbessern. Noch wirkungsvoller ist die Umwandlung des unstetigen Zweipunktreglers in einen quasi-stetigen Proportionalregler mit Hilfe des einfachen G o u y - Modulators. Bei der Anwendung von Galvanometern zur Anzeige der Regelabweichungen in Verbindung mit Photozellenrelais lassen sich einfache Möglichkeiten zur Modulation ohne Störung des Meßkreises verwirklichen, so daß mit Doppelthermostaten Temperaturen bis 1000 °C auf einige 0,001 ° genau geregelt werden können.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 704-705 
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    Keywords: Chemistry ; Industrial Chemistry
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    Notes: Mit Hilfe der Leistungszahl kann die Güte von Füllkörperschüttungen im Hinblick auf die Belastbarkeit, die Kosten u. a. einwandfrei verglichen werden. Der Einfluß des Druckes ist groß. Unter gewissen Voraussetzungen läßt er sich mittels der Ähnlichkeitstheorie erfassen.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 740-747 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Während im Teil l die Zersetzung von Polyvinylalkohol im Vakuum untersucht wurde, befaßt sich Teil ll mit der Anlagerung von Sauerstoff an die im Vakuum hergestellten Zersetzungsprodukte des Kunststoffs. Dabei wird sowohl eine Vernetzung der Polyvinyl-Kette über Sauerstoff-Brücken angenommen, als auch eine direkte Vernetzung, die durch Sauerstoff katalysiert wird. Es werden die Bedingungen untersucht, unter denen die Oxydationsreaktionen zur Selbstentzündung des Kunststoffs führen.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 762-764 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 765-773 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Salzschmelzen können in der Kerntechnik als Lösungs- bzw. Extraktionsmittel bei der Aufarbeitung spezieller Kernbrennstoffe, als Moderator und Lösungsmittel für den Spaltstoff homogener Leistungsreaktoren sowie als Hochtemperaturkühlmittel von Kernreaktoren verwendet werden. Der gegenwärtige Stand dieser Entwicklung und einige sich daraus ergebende chemische Probleme werden erörtert.
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    Chemie Ingenieur Technik - CIT 32 (1960) 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 796-801 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Bei dem Wirbelschichtverfahren zur Erzeugung von Äthylen aus Rohöl entsteht als Nebenprodukt eine C4-Fraktion, die 45 Gew.-% Butadien, 50 Gew.-% Butene und 5 Gew.-% Butane enthält. Zur quantitativen Abtrennung des Butadiens wurde ein Verfahren der selektiven Absorption ausgearbeitet. Bodenzahlen und BetriebsGrößen konnten mit Hilfe eines Iterations-Verfahrens unter Verwendung einer elektronischen Rechenanlage berechnet werden. Experimentelle Ergebnisse, die an einer Versuchsanlage gewonnen wurden, stimmen mit den errechneten Werten überein.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 839-841 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 837-837 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 109-117 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 118-121 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 121-121 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 122-122 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 121-121 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 123-125 
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    Chemie Ingenieur Technik - CIT 32 (1960) 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 125-128 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 129-135 
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    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Für die Strahlmahlung, eine Art der Prallzerkleinerung, werden die Möglichkeiten der Einstellung und Beeinflussung der Beanspruchungsvorgänge untersucht. In der Strahlmühle sind bei richtiger Strahlführung die gegenseitigen Teilchenstöße gegenüber den Wandstößen vorherrschend. Die gewünschte Prallgeschwindigkeit wird durch die pneumatische Beschleunigung der Teilchen im Strahl eingestellt. Dies verlangt in Abhängigkeit von der Strahlgeschwindigkeit und der Teilchengröße eine bestimmte Beschleunigungsstrecke, die sich überschlägig berechnen läßt. Man braucht also eine bestimmte Mindestlänge des Strahles, die mit der Korngröße des Gutes stark anwächst. Da die turbulente Vermischung die Strahlgeschwindigkeit herabsetzt, gehört zu einer bestimmten Strahllänge und Strahlgeschwindigkeit auch eine bestimmte Düsenöffnung.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 136-142 
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    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: In dieser Arbeit wird versucht, einen Beitrag zur Klärung der Grundlagen der Prallzerkleinerung zu liefern. Aus der Vielzahl der in einer solchen Maschine ablaufenden Vorgänge wird nur der Grundvorgang, der gerade zentrale Stoß betrachtet. Es wird der eigentliche Zerkleinerungsvorgang beim Auftreffen eines Körpers auf eine starre Wand durch funkenkinematographische Aufnahmen sichtbar gemacht. In weiteren Untersuchungen wird der Einfluß der Aufgabekorngröße und der Prallwand diskutiert. Schließlich wird die Möglichkeit erörtert, ein Gesetz für die Prallzerkleinerung aufzustellen. Die optimale Aufprallgeschwindigkeit liegt bei etwa 300 bis 500 m/s, sie wird in den üblichen Prallzerkleinerungsmaschinen bei weitem nicht erreicht. Auch für die selektive Zerkleinerung, für die eine Zerkleinerung durch Prallbeanspruchung besonders günstig ist, sind so hohe Auftreffgeschwindigkeiten erwünscht.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 143-154 
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    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Die Verfahren der modernen mathematischen Statistik stellen ein Hilfsmittel dar, dessen Bedeutung noch nicht überall in der Forschung und Industrie erkannt worden ist. Sie sind besonders dann wertvoll, wenn man Schlüsse ziehen oder Entscheidungen treffen muß auf Grund von Zahlenwerten, die durch störende Versuchsschwankungen, unvermeidliche Meßfehler oder dergleichen beeinflußt worden sind. Solange die Meßwerte gegenüber ihren zufälligen Schwankungen groß sind, kommt man zuweilen auch ohne Statistik zu richtigen Entscheidungen. Bei gleicher Größenordnung von Effekt und Schwankung ist jedoch ohne statistisches Denken keine einwandfreie Entscheidung möglich. Das wird beispielhaft gezeigt an Problemen der Probenahme und an der Ermittlung optimaler Betriebsbedingungen für eine chemische Reaktion, die von verschiedenen Einflußgrößen, wie Stoffmenge, Druck, Temperatur u. a., abhängt.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 155-163 
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    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Jeder technische Scheidungsvorgang, der sich an einer Körnung vollzieht, ist eine Summe von Teilungsvorgängen, die innerhalb eines gewissen Eigenschaftsbereiches (Trennfehlerzone) stattfinden. Die verschiedenen Scheidungsvorgänge verlaufen nach einem bisher nur angenähert bekannten statistischen Gesetz, das sich in einem S-förmigen Verlauf der sog. Teilungs-Kurve (T-Kurve) manifestiert. Diese Kurven haben nur einen begrenzten Geltungsbereich, der durch die Trennbarkeit des Rohstoffes sowie durch betriebliche Bedingungen (z. B. Überlastung) eingeschränkt wird. Diese Begrenzung vermindert jedoch keineswegs den Wert der T-Kurve, weil die Apparate für die verschiedenen Scheidungsvorgänge praktisch nur für diesen Bereich ausgelegt sind. Wird dieser Bereich überschritten, dann verändert sich die Form der T-Kurve in charakteristischer Weise. Aus solchen Veränderungen kann der erfahrene Praktiker auf ihre Ursachen schließen.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 171-171 
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    Notes: Pneumatische bzw. hydraulische Förderanlagen zeichnen sich durch geringe Anlagekosten und einen kleinen Platzbedarf aus, dagegen sind die Betriebskosten im allgemeinen größer als bei den klassischen Förderverfahren. Der kleinste Arbeitsaufwand pro Gewichtseinheit gefördertes Gut längs einer bestimmten Förderstrecke läßt sich vor allem bei verhältnismäßig niedrigen Fördergeschwindigkeiten und hohen Materialbeladungen in der Nähe der Stopfgrenze erzielen. Bei horizontaler Förderung muß im allgemeinen mit höheren Geschwindigkeiten als bei vertikaler Förderung gearbeitet werden. Die Erkenntnisse und Gesetzmäßigkeiten bei der pneumatischen Förderung werden auf die hydraulische Förderung übertragen. Günstige Verhältnisse in bezug auf die Wirtschaftlichkeit der Anlage sind vor allem bei großen Rohrdurchmessern zu erwarten.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 172-178 
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    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Bei der Verschwelung, Vergasung und Verbrennung von festen Brennstoffen wirkt sich eine Druckerhöhung in mehrfacher Hinsicht auf den Verfahrensgang aus, etwa in der Qualität der erhaltenen Produkte, in einer Verbesserung der Strömungsverhältnisse, in einer Leistungssteigerung und damit auch in einer Kostensenkung. Umgekehrt bedingt sie betriebliche Erschwerungen. Es muß daher sorgfältig erwogen werden, ob die Umstellung eines bisher bei Normaldruck verwendeten Verfahrens auf Hochdruck wirtschaftlich aussichtsreich ist. Dies wird an einigen speziellen Beispielen gezeigt.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 178-184 
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    Notes: Das sog. LR-Entgasungsverfahren für feinkörnige Kohle, entwickelt von den Firmen Lurgi und Ruhrgas AG, ist durch die Verwendung feinkörniger Wärmeträger gekennzeichnet. Hier werden Ergebnisse von Laboratoriumsversuchen zur Klärung chemisch-physikalischer Grundfragen des Verfahrens zusammengestellt. Über die Arbeiten in halbtechnischen und großtechnischen Anlagen wird später berichtet.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 185-190 
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    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Zur Eisen-Gewinnung außerhalb des Hochofens durch Reduktion mit Gasen sind in den letzten Jahren einige neue Reduktionsverfahren (Wirbelschicht- und Ruheschicht-Verfahren) entwickelt worden, die vorzugsweise Wasserstoff benutzen. Da der Umsatz der Reduktionsgase bei einmaligem Durchgang nur gering ist, wird mit Kreislaufführung gearbeitet oder aber für die Abgase eine andere wirtschaftliche Verwendung gesucht.  -  Eine grundsätzlich andere Lösung stellt das sog. CO-C-Eisen-Verfahren dar, das in zwei Stufen arbeitet (Kohlenstoffabscheidung und Vorreduktion; Endreduktion) und dessen Grundzüge hier beschrieben werden.
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    Notes: Es werden die heute bei der Ammoniak- und Schwefelwasserstoff-Wäsche gebräuchlichen Wascher (Kittelboden-Wascher, Düsen-Wascher, Horden-Wascher, Glockenboden-Wascher, Raschigring-Wascher und Streckmetall-Wirbelstrom-Wascher) an Hand von Betriebswerten verglichen.
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    Notes: Es wird die Frage diskutiert, ob die Hochschulausbildung des Ingenieurs, Physikers und Chemikers die richtige Ausbildung für das Gebiet der Kohlenveredelung ist. Zur Beantwortung werden die in der Kohlenveredelung vorliegenden Aufgaben verfahrenstechnischer Art dargestellt. An Einzelheiten wird gezeigt, daß den vielseitigen Aufgaben die Ausbildung des Verfahrens-Ingenieurs weitgehend gerecht wird.
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    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Am Beispiel der Carbid-Ofen-Entwicklung wird gezeigt, wie durch Änderung des Verfahrens im großen Stile die Staubemission praktisch vermieden werden kann. Aber auch im bescheideneren Maße kann durch sinnvolle Umstellung des Verfahrens, z. B. bei einer Sinteranlage für die Phosphor-Erzeugung, der Staubauswurf auf ein erträgliches Maß herabgesetzt werden, ohne zunächst besondere Abscheider einzubauen. Für besonders schwierige Fälle der Staubabsaugung werden konstruktive Lösungen gezeigt. Zwei neue Abscheiderbauarten haben sich im Betrieb bewährt.
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    Notes: Der Carbid-Ofenstaub stammt zum Teil aus dem Abrieb des Möllers, zum Teil entsteht er innerhalb des Ofens. Dort werden Magnesiumoxyd und Siliciumdioxyd bei über 2000 °C zu den Elementen reduziert und verdampft. Außerhalb des Ofens werden sie durch Kohlenoxyd reoxydiert und als Staub emittiert. Infolge Anreicherung des Staubes an Magnesiumoxyd läßt sich in der Umgebung der Carbid-Werke der Carbid-Staub in den Staubniederschlägen gut erkennen und so seine Reichweite bestimmen. Die weitaus größte Menge des Staubes aus Cardid-Öfen wird schon innerhalb einer Entfernung zwischen 2 und 2,5 km abgeschieden, da sich unmittelbar nach Verlassen des Ofenherdes große und spezifisch schwere Teilchen bilden. Mit einem Konimeter wurde der Gehalt der Luft an Staubteilchen unter 10 μ gemessen und festgestellt, daß die Teilchenzahl pro cm3 Luft nur zum Teil von der Entfernung von der Emissionsquelle, zum anderen Teil aber von der Teilchengröße abhängig ist.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 217-222 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Die Berechnung und Messung der Dehnung an einem Großbehälter ergaben, daß dieser unzulässig hohe Spanungen bei dem noch zulässigen Betriebsdruck zeigt, so daß die Gefahr der Spannungskorrosion besteht. Aus diesem Grund wird zunächst die Theorie der biegesteifen Schalen weitgehend vereinfacht, um Lösungen für die verschiedenen in der Technik vorkommenden Schalenformen zu gewinnen. Ein Beispiel zeigt die Übereinstimmung von Theorie und Messung. Durch Modellmessungen werden die systematischen Fehler bestimmt, die bei dem durchgerechneten Beispiel bis zu ± 13% betragen können.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 228-230 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 223-227 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Für Zweistoffgemische wurde unter Anwendung des McCabe-Thiele-Verfahrens ein Rechenprogramm für die elektronische IBM-Rechenanlage 705 entwickelt. Unter der in der Praxis vielfach hinreichenden Voraussetzung, daß die molare Verdampfungswärme unabhängig von der Konzentration ist und keine Lösungswärme auftreten, können Bodenzahlen für Zweistoffgemische idealen, nicht-idealen und nicht-idealen azeotropen Charakters berechnet werden. Über Lochkarten werden die Gleichgewichtskurve und die Zulauf-, Kopf- und Sumpfkonzentration in das vorhandene Programm eingespeist. Die Rechenzeiten liegen zwischen 15 s und 5 min pro Aufgabe. Das von der Maschine erstellte Druckbild liefert für jede Aufgabe eine Folge von möglichen Bodenzahlen in Abhängigkeit vom Rücklaufverhältnis bzw. Rückverdampfungsverhältnis.
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    Notes: Den kritischen Zustand bestimmt man in der Regel, indem man beobachtet, wann der sog. Meniskus, die Trennfläche zwischen den beiden Phasen Flüssigkeit und Dampf, verschwindet. Die Genauigkeit dieses Verfahrens läßt sich erheblich steigern, wenn man statt des Verschwindens einer sichtbaren Trennfläche die Brechungszahl oberhalb und unterhalb des verschwindenden Meniskus mißt. Dabei zeigte sich bei Messungen an Kohlendioxyd, daß nach Unsichtbarwerden des Meniskus noch erhebliche Dichteunterschiede sowohl bei überkritischen Temperaturen, als auch bei unterkritischen Zuständen bestehen bleiben.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 242-244 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 233-240 
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    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Für die Gewinnung des stabilen Sauerstoff-Isotops 18O sind verschiedene Trennverfahren vorgeschlagen und angewandt worden, wie z. B. die Thermodiffusion und chemische Austauschverfahren. Am wirtschaftlichsten erscheint jedoch eine Gegenstromdestillation von Wasser, wobei sich das H218O am Kolonnenfuß anreichert. Es werden Apparaturen für die diskontinuierliche und die kontinuierliche Arbeitsweise sowie kombinierte Verfahren mit Kaskaden beschrieben, mit denen sich 18O bis auf 95 Atom-% anreichern ließ.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 245-246 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 247-249 
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    Notes: Für diesen ersten vollständig in der Bundesrepublik entwickelten Leistungsreaktor wurde im August 1959 von der Arbeitsgemeinschaft Versuchs-Reaktor AVR, GmbH., der Bauauftrag erteilt. Es ist zugleich der erste Bauauftrag für einen gasgekühlten Hochtemperaturreaktor.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 250-252 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 250-252 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 253-257 
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    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Beim Wirbelstoßverfahren wird ebenso wie in der Wirbelschict ein Schüttgut von Gasen durchströmt. Durch eine besondere Gasführung gelingt es, die Kanalbildung, auch bei Produkten mit starken Zwischenpartikelkräften, zu unterbinden. Der Abrieb kann klein gehalten werden. Um optimale Bedingungen für die Trocknung von Schüttgütern zu erhalten, sind verschiedene Ausführungsarten des Wirbelstoßverfahrens entwickelt worden. Eine Übersicht über die Erfahrungen mit Wirbelstoßtrocknern wird gegeben.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 258-260 
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    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Rippenrohre bieten neben der Verbesserung der Wärmeübertragungsverhältnisse die Möglichkeit, die Wandtemperaturen von Wärmeübertragern zu variieren. Die quantitativen Zusammenhänge werden abgeleitet und die sich daraus ergebenden Möglichkeiten an einem ölbeheizten Luftvorwärmer für Kupolöfen und an der Aufheizung von Bitumen erläutert.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 260-266 
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    Notes: Infolge der zunehmenden Wasserverknappung geht man bei der Abführung von Wärme immer mehr auf Verdunstungskühlung über. Kühltürme werden jetzt nicht nur als Bauwerke erstellt, sondern insbesondere für kleinere Anlagen als typisierte und in Serien produzierte Einheiten geliefert. Leichte Füllkörper in Verbindung mit Umkleidungen aus glasfaserverstärkten Polyesterharzen ermöglichen bei guter Beständigkeit eine Kostensenkung beim Transport und bei der Aufstellung. Mit der Einführung von Kennzahlen lassen sich für Kühltürme allgemeingültige Gleichungen schaffen und optimale Prozesse verwirklichen. Programmgesteuerte Rechenmaschinen ermöglichen die Übertragung auf Leistungsdiagramme für alle Betriebsbedingungen. Einzelrechnungen können durch eine Ersatzfunktion verkürzt werden.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 285-288 
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    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Nach kurzer Erörterung der Berechnungsgrundlagen werden vor allem Betriebserfahrungen und Prüfstandergebnisse mit doppeltwirkenden Gleitringdichtungen mitgeteilt.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 279-284 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Der Hydrozyklon wird in verschiedenen Konstruktionen zum Klassieren, Sortieren und Eindicken für Feststoffgrößen zwischen 3 und 250 μ verwendet. Bewährt haben sich Kombinationen von Hydrozyklonen mit Filtern, Eindickern und Zentrifugen, wie an Anwendungsbeispielen aus der Erzaufbereitung der Schwerindustrie, der Kali-Industrie, der Erdöl-Bohrung und der chemischen Industrie gezeigt wird.
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    Notes: Es wurden Zirkonsteine, Zirkoncristobalit- und Korund-Steine mit über 99% Aluminiumoxyd als neue hochfeuerfeste Steine entwickelt. Ihre Eigenschaften wurden durch Kontaktreaktionen, in reduzierender Ofenatmosphäre und im Natriumsulfat-Dampf sowie beim Angriff durch Ölaschen geprüft. Daraus werden Folgerungen für zweckmäßige Anwendungen in Chemie-Öfen gezogen.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 288-290 
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    Notes: Es werden druckfest gekapselte explosionsgeschützte Verteilungen beschrieben und die Besonderheiten der Freiluftaufstellung im einzelnen dargestellt.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 298-298 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 297-298 
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    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Für die Haltbarkeit von Lebensmitteln ist die Gas- und Wasserdampfdurchlässigkeit der zur Verpackung geeigneten Folien von wesentlicher Bedeutung. Es wird über den Einfluß hoher Strahlendosen bis zu 20 Mr weicher Röntgenstrahlen auf die Durchlässigkeit einiger mit Polyäthylen beschichteter schweißbarer Folien gegenüber Luft und Sauerstoff sowie gegenüber Wasserdampf mit und ohne Kontakt zwischen Folien und Wasser berichtet. Ferner werden Maßzahlen für die bei der Bestrahlung der Folien auftretenden Farbänderungen angegeben.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 299-304 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 305-308 
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    Notes: Um genauere Einblicke in das beim Heißsiegeln von thermoplastischen Folien entstehende instationäre Temperaturfeld zu erhalten, wurde ein Meßverfahren entwickelt, mit dem die Temperaturleitzahl bis in den Schmelzbereich des Materials ermittelt werden kann. Die Temperaturleitzahl wird dabei bestimmt aus der zeitlichen Änderung der Temperatur in der Probenmitte eines Kunststoff-Zylinders, der sich in Heizbädern mit stufenweise steigenden Temperaturen befindet, und seiner Längenänderung mit der Temperatur. Die Meßergebnisse werden als Temperaturausgleichskurven erhalten, wobei jeder Heizbadtemperatur eine Kurve entspricht. Auf Grund der Meßergebnisse werden die Anwendungsgrenzen des Verfahrens und die Genauigkeit diskutiert.
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 309-309 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 311-314 
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    Chemie Ingenieur Technik - CIT 32 (1960), S. 343-349 
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    Notes: Um die Vorgänge in Mischern für rieselfähige Güter zu klären, wird eine Gleichung zur Darstellung des zeitlichen Ablaufes eines Mischungsvorganges abgeleitet und an fremden sowie an eigenen Versuchen nachgeprüft. Aus der Auswertung der eigenen Versuche mit der Gleichung ergibt sich die überlegene Wirkung eines neu entwickelten Tetraeder-Mischers.
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    Notes: Aus der Betrachtung des Strömungsvorganges durch Schüttschichten wird eine allgemeingültige Druckverlustgleichung abgeleitet. Mit Hilfe von Druckverlustmessungen an Kugel-, Zylinder- und Raschig-Ring-Schüttungen verschiedener Füllkörper- und Säulenabmessungen bei Variation der Schüttdichte wird diese hinsichtlich des Lückenvolumeneinflusses auf ihre Gültigkeit untersucht. Eigene Messungen sowie die Meßergebnisse anderer Autoren werden durch diese Druckverlustgleichung gut wiedergegeben. Aus der experimentell bestimmten Verteilung des Lückenvolumens über dem Querschnitt einer Füllkörpersäule wird die Abhängigkeit des Druckverlustes vom Durchmesser des Füllkörpers und der Säule sowie das Geschwindigkeitsfeld bestimmt und mit bekannten Meßergebnissen verglichen.
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    Notes: Beim System Stickstoff/Sauerstoff wurden bei Atmosphärendruck Wärme- und Stoffaustausch zwischen Dampf und Flüssigkeit verfolgt. Das Gas strömte dabei in Blasen, die an einer einzelnen Öffnung mit Kreisquerschnitt gebildet wurden, durch eine ruhende Flüssigkeit. Gaszusammensetzung, Flüssigkeits-zusammensetzung und Flüssigkeitsstand über der Düse konnten dabei beliebig, die Temperatur der Flüssigkeit, die Eintrittstemperatur des Gases, Düsendurchmesser und eingeblasener Gasstrom beschränkt variiert werden. Entstehung und Aufstieg der Blasen in der Flüssigkeit wurden in Zeitdehner-filmen festgehalten. Dabei wurde festgestellt, daß das Verstärkungsverhältnis in den untersuchten Intervallen der Variablen von folgenden Größen abhängt: Flüssigkeitszusammensetzung, Durchsatz durch die Düse, Austauschstrecke des Dampfes durch die Flüssigkeit und Richtungssinn des Stoffaustausches.
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Da die Randbedingungen für die Strahlausbildung und Teilchenbewegung in Strahlmühlen nicht genügend definiert sind, wurden Einzelstrahlen untersucht. Die Geschwindigkeit von Glasperlen, die von außen in einen runden Freistrahl eintreten, wurde stroposkopisch gemessen. Aus den Teilchengeschwindigkeiten läßt sich die Strahlgeschwindigkeit längs der Teilchenbahn errechnen. Das Geschwindigkeitsprofil in Mündungsnähe stimmt ziemlich gut mit den von Kuethe für wesentlich größeren Strahldurchmesser und kleineren Geschwindigkeiten gemessenen Profilen überein. Die maximal erreichbare Geschwindigkeit der in der Strahlachse bewegten Teilchen läßt sich vorausberechnen. Der Einfluß der Turbulenz auf die Teilchenbewegung im Strahl wurde rechnerisch abgeschätzt. Die Zerkleinerung in Strahlmühlen findet vorwiegend in der Nähe der Düsenmündung staff. Mahlungen von Zucker in Strahlmühlen bestätigen diese Erwartung. Man erkennt wegen der Leuchterscheinungen den Ort der Zerkleinerung.
    Additional Material: 30 Ill.
    Type of Medium: Electronic Resource
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