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Investigation of Turbines for Driving Supersonic Compressors: 1: Design and Performance of First Configuration

Description: Report presenting the design and performance of a turbine to drive a supersonic compressor in order to determine the problems that would be encountered in turbines required to drive high-speed, high-weight-flow compressors. A model of the turbine was built and operated over a range of speed and total-pressure ratios. Results regarding performance, the effects of rotor choking, and possible modifications to the design are provided.
Date: June 17, 1952
Creator: Stewart, Warner L.; Schum, Harold J. & Whitney, Warren J.
Item Type: Refine your search to only Report
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Investigation of Turbines for Driving Supersonic Compressors 2: Performance of First Configuration With 2.2 Percent Reduction in Nozzle Flow Area

Description: "The experimental performance of a modified turbine for driving a supersonic compressor is presented and compared with the performance of the original configuration to illustrate the effect of small changes in the ratio of nozzle-throat area to rotor-throat area. Performance is based on the performance of turbines designed to operate with both blade rows close to choking. On the basis of the results of this investigation, the ratio of areas is concluded to become especially critical in the desi… more
Date: July 22, 1952
Creator: Stewart, Warner L.; Schum, Harold J. & Wong, Robert Y.
Item Type: Refine your search to only Report
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Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed 1: turbine-design requirements for several engine operating conditions

Description: In order to insure satisfactory turbine performance under five turbojet-engine operating conditions, turbine design requirements were determined for the following operating conditions: take-off, maximum thrust at altitude, altitude cruising at rated rotative speed, altitude cruising with maximum-thrust exhaust nozzle area, and engine acceleration at 80 percent equivalent design rotative speed. If cruising is to be at rated engine speed, both cruising and take-off should be considered in turbine… more
Date: March 4, 1952
Creator: English, Robert E.; Silvern, David H. & Davison, Elmer H.
Item Type: Refine your search to only Report
open access

Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor tip-speed 2: velocity-diagram study of turbine for engine operation with constant exhaust-nozzle area

Description: Report presenting an investigation of whether or not a two-stage turbine with the frontal area no larger than the compressor frontal area could be satisfactorily designed to drive a particular compressor under take-off conditions. The low blade-tip speed, high work, and high air flow per unit of frontal area of the compressor make it critical that a two-stage turbine is designed to drive it. Results regarding the effect of work division, effect of variation in cone angle, and effects of radial … more
Date: June 19, 1952
Creator: Davison, Elmer H. & English, Robert E.
Item Type: Refine your search to only Report
open access

Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed 3: velocity-diagram study of two-stage and downstream-stator turbines for engine operation at constant rotative speed

Description: Report presenting the use of a simplified method of analysis in order to relate the turbine operations for take-off and cruise at rotative speed. This allows turbine velocity diagrams to consider both take-off and cruising operation. Results regarding the two-stage turbine design and the downstream-stator turbine design are provided.
Date: November 21, 1952
Creator: English, Robert E. & Davison, Elmer H.
Item Type: Refine your search to only Report
open access

Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed 4: effect of increasing blade speed on velocity diagrams of turbine for engine operation at constant rotative speed

Description: Report presenting the use of a simplified method of analysis in order to estimate the turbine blade-tip speed required to design satisfactory two-stage turbines. The investigation allows for certain conditions for optimal two-stage turbine design to be determined.
Date: November 24, 1952
Creator: Davison, Elmer H. & English, Robert E.
Item Type: Refine your search to only Report
open access

Investigation of vanes immersed in the jet of a solid-fuel rocket motor

Description: Report presenting a determination of the characteristics of a particular vane configuration in the jet of a 6.25-inch Deacon solid-fuel rocket motor from static testing. The vanes were oscillated during the test to provide comprehensive data over a range of deflection angles. The effects of the rocket jet on two vane materials, the aerodynamic characteristics of the vanes, and the influence of jet vanes on rocket-motor performance were determined.
Date: September 10, 1952
Creator: Giladett, Leo V. & Wineman, Andrew R.
Item Type: Refine your search to only Report
open access

An Investigation Utilizing an Electrical Analogue of Cyclic Deicing of a Hollow Steel Propeller with an External Blade Shoe

Description: "A study has been made of the heat requirement for the cyclic de-icing of hollow steel propellers fitted with external blade heating shoes. Solutions to the equations for the heat flow in cyclic heating of propellers were obtained, using an electrical analogy. The study showed how the energy requirement for propeller de-icing with existing blade shoes could be decreased, and illustrated the effect of blade-shoe design on the energy requirement. It was demonstrated, for example, that by increas… more
Date: December 1952
Creator: Neel, Carr B., Jr.
Item Type: Refine your search to only Report
open access

Investigation with an interferometer of the flow around a circular-arc airfoil at mach numbers between 0.6 and 0.9

Description: From Summary: "The flow around a 12-percent-thick circular-arc airfoil at zero incidence was observed with an interferometer for small increments of free-stream Mach number from 0.609 to 0.896 with laminar and turbulent boundary layers. Mach number contours in the flow field and Mach number and pressure distributions on the airfoil were obtained. Conditions were determined along and at the bases of the shock waves that interacted with the turbulent boundary layer on the airfoil."
Date: October 1952
Creator: Wood, George P. & Gooderum, Paul B.
Item Type: Refine your search to only Report
open access

Investigational Drilling, Hoskinnini Mesa

Description: From to the files: To date, all the mineralization seen in the Monument Valley area in the Shinarump formation has been in scour channels. The mineralized rock occurs at or near the bottom of the channel. On Hoskinnini Mesa, all the channels examined to date contain some mineralized material. Channels observed may in some cases contain copper without apparent uranium mineralization; others definitely exhibit copper-uranium mineralization.
Date: May 15, 1952
Creator: Chester, John W. & Pitman, R. K.
Item Type: Refine your search to only Report
open access

Investigations in the Fall Creek Area, Bonneville County, Idaho, During the 1952 Field Season: A Preliminary Report

Description: Introduction: Field work during the 1952 field season has supplied new data on the areal extent, composition, and estimated reserves of uranium-bearing carbonaceous rocks in the Fall Creek.area, Bonneville County, Idaho. The following is a preliminary report of progress to describe these new data which supplement the information contained in Trace Elements Memorandum Report 340 (Vine and Moore, 1952). This work was done on behalf of the Division of Raw Materials of the U. S. Atomic Energy Commi… more
Date: November 1952
Creator: Vine, James David
Item Type: Refine your search to only Report
open access

Investigations of Air-Cooled Turbine Rotors for Turbojet Engines 1: Experimental Disk Temperature Distribution in Modified J33 Split-Disk Rotor at Speeds up to 6000 RPM

Description: "An experimental investigation is being conducted at the Lewis laboratory to establish general principles for the design of noncritical turbine rotor configurations. This investigation includes evaluation of cooling effectiveness, structural stability, cooling-air flow distribution characteristics, and methods of supplying cooling air to the turbine rotor blades. Prior to design of a noncritical rotor, a standard turbine rotor of a commerical turbojet engine was split in the plane of rotation a… more
Date: January 9, 1952
Creator: Schramm, Wilson B. & Ziemer, Robert R.
Item Type: Refine your search to only Report
open access

Investigations of air-cooled turbine rotors for turbojet engines 2: mechanical design, stress analysis, and burst test of modified J33 split-disk rotor

Description: A full-scale J33 air-cooled split turbine rotor was designed and spin-pit tested to destruction. Stress analysis and spin-pit results indicated that the rotor in a J33 turbojet engine, however, showed that the rear disk of the rotor operated at temperatures substantially higher than the forward disk. An extension of the stress analysis to include the temperature difference between the two disks indicated that engine modifications are required to permit operation of the two disks at more nearly … more
Date: January 14, 1952
Creator: Kemp, Richard H. & Moseson, Merland L.
Item Type: Refine your search to only Report
open access

Investigations of the Boundary-Layer Control on a Full Scale Swept Wing With Air Bled Off From the Turbojet

Description: "The following account reviews the various stages of a research program relative to the high-lift devices on a swept wing by combined suction and blowing (jet action), with ejectors fed by air bled off (extracted) from the turbojet. After reviewing the essential principles of the boundary-layer control obtained by comparison with theory, the electric analogies and the wind-tunnel tests as well as the essential elements of ejector operations, the writers describe the tests made in the large tunn… more
Date: April 1952
Creator: Rebuffet, Pierre & Poisson-Quinton, P.
Item Type: Refine your search to only Report
open access

Inviscid Flow About Airfoils at High Supersonic Speeds

Description: Report presenting an investigation of steady flow about curved airfoils at high supersonic speeds. Testing demonstrated that within the limitation of the assumption of ideal gas flow, the shock-expansion method may be used with good accuracy to predict pressure distributions on curved airfoils at arbitrarily high Mach numbers.
Date: March 1952
Creator: Eggers, A. J., Jr. & Syvertson, Clarence A.
Item Type: Refine your search to only Report
open access

Irradiated of 63S Aluminium Samples

Description: Summary: "Data obtained from testing and observing samples of 63S Al irradiated for approximately three months are presented. Tensile data show a slight, general increase in strength during pile exposure with a slight decrease in elongation. It is uncertain whether tkis increase in strength is a result of irradiation, exposure to slightly elevated temperatures, or a combination of the two effects. Metallographic examination revealed no apparent damage to the microstructure. As a result of these… more
Date: 1952
Creator: Wright, P. D.
Item Type: Refine your search to only Report
open access

Irradiation of 63S Aluminum Samples

Description: Data obtained from testing and observing samples of 63S Al irradiated for approximately three months are presented. Tensile data show a slight, general increase in strength during pile exposure with a slight decrease in elongation. It is uncertain whether tkis increase in strength is a result of irradiation, exposure to slightly elevated temperatures, or a combination of the two effects. Metallographic examination revealed no apparent damage to the microstructure. As a result of these tests. it… more
Date: August 21, 1952
Creator: Wright, P. D.
Item Type: Refine your search to only Report
open access

An Iterative Transformation Procedure for Numerical Solution of Flutter and Similar Characteristics-Value Problems

Description: "An iterative transformation procedure suggested by H. Wielandt for numerical solution of flutter and similar characteristic-value problems is presented. Application of this procedure to ordinary natural-vibration problems and to flutter problems is shown by numerical examples. Comparisons of computed results with experimental values and with results obtained by other methods of analysis are made" (p. 1).
Date: 1952
Creator: Gossard, Myron L.
Item Type: Refine your search to only Report
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