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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
    Publication Date: 2019-08-28
    Keywords: Mechanical Engineering
    Type: AD-B204941 , NACA-TM-1165 , NASA-TM-111363 , NAS 1.15:111363
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Investigation of Turbine of Mark 25 Torpedo Power Plant with Five Nozzle Designs (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: 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.
    Keywords: Mechanical Engineering
    Type: NACA-RM-E7I03
    Format: application/pdf
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  • 3
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    Investigations on Experimental Impellers for Axial Blowers (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A selection of measurements obtained on experimental impellers for axial blowers will be reported. In addition to characteristic curves plotted for low and for high peripheral velocities, proportions and blade sections for six different blower models and remarks on the design of blowers will be presented.
    Keywords: Mechanical Engineering
    Type: NACA-TM-1123 , ZWB, M94, Nr. 3135; 1-28
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Performance of the 19XB 10-Stage Axial-Flow Compressor (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The 19xB compressor, which replaces the 19B coaapreseor and has the same length and diameter 88 the 19B compressor, was designed with 10 stages to deliver 30 pounds of air per second for a pressure ratio of 4.17 at an equivalent speed of 17,000 rpm; the 19B was designed with six stages for a pressure ratio of 2.7 at the same weight flow and speed as the 19XB compressor. The performance characteristics of the new compressor were determined at the NACA Cleveland laboratory at the request of the Bureau of Aeronautics, Navy Department. Results are presented of the investigation made to evaluate the over-all performance of the compressor, the effects of possible leakage past the rotor rear air seal, the effects of inserting instruments in each row of stator blades and in the first row of outlet guide vanes, and the effects of changing the temperature and the pressure of the inlet air. The results of the interstage surveys are also presented.
    Keywords: Mechanical Engineering
    Type: NACA-RM-E6L04
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Determination of the Stress Concentration Factor of a Stepped Shaft Stressed in Torsion by Means of Precision Strain Gages (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The stress distribution in stepped shafts stressed in torsion is determined by means of the electric precision strain gage the stress concentration factor is ascertained from the measurements. It is shown that the test values always are slightly lower than the values resulting from an approximate formula.
    Keywords: Mechanical Engineering
    Type: NACA-TM-1179 , Berlin-Adlershof; 20; 7; 217-219
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    NASA TECHNICAL REPORTS
  • 6
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    Cooling Characteristics of the V-1650-7 Engine. II - Effect of Coolant Conditions on Cylinder Temperatures and Heat Rejection at Several Engine Powers (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation has been conducted on a V-1650-7 engine to determine the cylinder temperatures and the coolant and oil heat rejections over a range of coolant flows (50 to 200 gal/min) and oil inlet temperatures (160 to 2150 F) for two values of coolant outlet temperature (250 deg and 275 F) at each of four power conditions ranging from approximately 1100 to 2000 brake horsepower. Data were obtained for several values of block-outlet pressure at each of the two coolant outlet temperatures. A mixture of 30 percent by volume of ethylene glycol and 70-percent water was used as the coolant. The effect of varying coolant flow, coolant outlet temperature, and coolant outlet pressure over the ranges investigated on cylinder-head temperatures was small (0 deg to 25 F) whereas the effect of increasing the engine power condition from ll00 to 2000 brake horsepower was large (maximum head-temperature increase, 110 F).
    Keywords: Mechanical Engineering
    Type: NACA-RM-SE7I02
    Format: application/pdf
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  • 7
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    Calibration Tests of a German Log Rodmeter (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A German log rodmeter of the pitot static type was calibrated in Langley tank no. 1 at speeds up to 34 knots and angles of yaw from 0 deg to plus or minus 10 3/4 degrees. The dynamic head approximated the theoretical head at 0 degrees yaw but decreased as the yaw was increased. The static head was negative and in general became more negative with increasing speed and yaw. Cavitation occurred at speeds above 31 knots at 0 deg yaw and 21 knots at 10 3/4 deg yaw.
    Keywords: Mechanical Engineering
    Type: NACA-RM-SL9C15
    Format: application/pdf
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  • 8
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    Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation was made of the first-stage turbine of a Mark 25 torpedo power plant to determine the performance of the unity with two nozzle configurations and a special rotor having 0.45-inch blades instead of the standard length of 0.40 inch. Both nozzles had smaller passages than the nozzles of similar shape that were previously investigated. The performance of the nozzle-blade combinations is evaluated in terms of brake, rotor, and blade efficiency as functions of blade-jet speed ratio for three pressure ratios. Over the range of speeds and pressure ratios investigated, the efficiency with the nozzle having rectangular passages (J) was higher than that with a nozzle having circular passages (K). The difference in blade efficiencies varied from less than 0.010 at the lower blade-jet speed ratios for the three pressure ratios investigated to 0.030 at a pressure ratio of 8 and a blade-jet speed ratio of 0.295. The efficiencies with these tow nozzles were generally lower than those obtained with nozzles previously reported in combination with the 0.45-inch blades.
    Keywords: Mechanical Engineering
    Type: NACA-RM-SE9G20A
    Format: application/pdf
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  • 9
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    Vibration Survey of Blades in 19XB Axial-Flow Compressor (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Strain-gage measurements were taken under operating conditions from blades of various stages of the 19XB axial-flow compressor in an effort to determine the reason for failures in the seventh and tenth stages. First bending-mode vibrations were detected in the first five stages of the compressor caused by each integral multiple of rotor speed from three through ten. Lead-wire failures in the last five stages resulted in incomplete data. The dynamic-vibration frequencies at various rotor speeds were compared with statically measured frequencies analytically corrected for the influence of centrifugal force. Large increases in vibration ani~litude with increased pressure ratio were observed. During surging operation, blade vibrations were not present. The effects of pressure ratio and surge indicate the existence of aerodynamic excitation as the cause of the blade vibrations.
    Keywords: Mechanical Engineering
    Type: NACA-RM-E7D09
    Format: application/pdf
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  • 10
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    An Analysis of the Full-Floating Journal Bearing (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An analysis of the operating characteristics of a full-floating bearing - a bearing in which a floating sleeve is located between the journal and bearing surfaces - is presented together with charts - from which the performance of such bearings may be predicted. Examples are presented to illustrate the use of these charts and a limited number of experiments conducted upon a glass full-floating bearing to verify some results of the analysis are reported. The floating sleeve can operate over a wide range of speeds for a given shaft speed, the exact value depending principally upon the ratio of clearances and upon the ratio of radii of the bearing. Lower operating temperatures at high rotative speeds are to be expected by using a full-floating bearing. This lower operating temperature would be obtained at the expense of the load-carrying capacity of the bearing if, for comparison, the clearances remain the same in both bearings. A full-floating bearing having the same load capacity as a conventional journal bearing may be designed if decreased clearances are allowable.
    Keywords: Mechanical Engineering
    Type: NACA-RM-E7A28a
    Format: application/pdf
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