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Final Report of Seamwelding Development Program on Zirconium Can End Closures
"A satisfactory welding schedule for zirconium can assemblies was demonstrated."
The Kinetics of Age Hardening
A study on the development of the conceptions on which age hardening is based. Temporary experimental data on aluminum-silver alloys
Air-flow characteristics of brazed and rolled wire filter cloth for transpiration-cooled afterburners
From Introduction: "Because of variation in the static-pressure drop across the porous material and in the cooling air required along the length of afterburner combustion chambers, a prescribed distribution of permeability is usually necessary. However, as a preliminary investigation, this report is concerned only with the attainment of uniform permeability. The results of an experimental investigation, conducted at the NACA Lewis laboratory, to determine the permeabilities of five thick meshes of wire filter cloth are presented herein."
Cooling Characteristics of a Transpiration-Cooled Afterburner With a Porous Wall of Brazed and Rolled Wire Cloth
Memorandum presenting cooling data for a transpiration-cooled afterburner with a porous combustion-chamber wall of brazed and rolled wire cloth for a range of exhaust-gas temperatures, total flow ratio of cooling air to combustion gas, and pressure altitudes. Maximum wall temperatures based on the cooling correlation were determined for a porous wall of uniform permeability at sea-level takeoff and for several flight Mach numbers. Results regarding typical data, cooling correlation, transpiration-cooling performance, comparison of transpiration and forced-convection cooling, and pressure environment of wire cloth are provided.
Cooling characteristics of a transpiration-cooled afterburner with a porous wall of brazed and rolled wire cloth
Report presenting cooling data for a transpiration-cooled afterburner with a porous combustion-chamber wall of brazed and and rolled wire cloth for a range of exhaust-gas temperatures, total flow ratios of cooling air to combustion gas, and pressure altitudes. Results regarding typical data, cooling correlation, transpiration-cooling performance, comparison of transpiration and forced-convection cooling, and pressure environment of the wire cloth are provided.
Preliminary experimental investigation of transpiration cooling for an afterburner with a sintered, porous stainless-steel combustion-chamber wall
Report presenting an experimental investigation of the application of transpiration air-cooling to the combustion-chamber wall of an afterburner. Results regarding the typical temperature and pressure profiles, correlation of wall temperatures, distribution of cooling-air flux density, longitudinal distribution of cooling air, longitudinal distribution of wall temperature, effect of permeability on cooling-air requirements, and fabricating and operating problems are provided.
A unit laboratory engine oil system providing for a remote indication of oil flow and oil consumption together with blow-by measurement
From Summary: "A unit oil system and oil-weighing device designed for laboratory engine tests to permit the remote measurement of oil-flow rate and oil consumption is described. The system regulates the oil pressure and temperature and is closed to make possible the accurate measurement of blow-by gas. The oil is weighed by a self-contained diaphragm and pilot-valve assembly, which uses compressed air as the transmitting medium. Several of those unit systems have given satisfactory service for more than a year."
Cooling Characteristics of an Experimental Tail-Pipe Burner With an Annular Cooling-Air Passage
Memorandum presenting the tail-pipe fuel ratio, mass flow of combustion gas, and radial fuel flow distribution on cooling requirements of tail-pipe burner with annular cooling-air passage.
Cooling characteristics of an experimental tail-pipe burner with an annular cooling-air passage
The effects of tail-pipe fuel-air ratio (exhaust-gas temperatures from approximately 3060 degrees to 3825 degrees R), radial distribution of tail-pipe fuel flow, and mass flow of combustion gas and the inside wall were determined for an experimental tail-pipe burner cooled by air flowing through and insulated cooling-air to combustion gas mass flow from 0.066 to 0.192 were also determined. Results regarding the reproducibility of combustion-gas temperature profiles, effect of variables on average longitudinal profiles of combustion-gas temperature, variation of gas temperatures near the wall with cooling-air flow and temperature, and effects of variables on transverse gas temperatures are provided.
Empirical Cooling Correlation for an Experimental Afterburner With an Annular Cooling Passage
Memorandum presenting an empirical cooling correlation for an experimental high-performance afterburner. The correlation relates the average combustion-chamber wall temperature at a station near the combustion-chamber outlet to the temperatures of the cooling air and combustion gas, and to the mass flows of the cooling air and combustion gas.
Empirical cooling correlation for an experimental afterburner with an annular cooling passage
Report presenting an empirical cooling correlation for an experimental high-performance afterburner. The correlation equation is useful for shortening the experimental investigation of afterburner cooling characteristics inasmuch as it provides a method for interpolating the critical wall temperatures for other combinations of operating variables.
Investigation of heat-transfer coefficients in an afterburner
Report presenting an evaluation of the relative importance of heat-transfer modes in an experimental afterburner. The convective heat-transfer coefficients near the combustion-chamber outlet were determined and the effects of three radial distributions of afterburner fuel across the turbine-outlet annulus on the convective heat-transfer coefficient were examined.
Some screeching-combustion characteristics of a transpiration-cooled afterburner having a porous wall of wire cloth
Report presenting an investigation of the screeching characteristics of two flame-holder configurations in a full-scale transpiration-cooled afterburner. The investigation indicated that a porous wall of wire cloth may be effective in eliminating or reducing the tendency to screech in some high-performance afterburners, but further testing is required. Results regarding the diametrical V-gutter, single-ring V-gutter, and durability of wire cloth are provided.
Cooling of ram jets and tail-pipe burners: analytical method for determining temperatures of combustion chamber having annular cooling passage
Report presenting an analytical method for calculating the maximum wall temperature of a tail-pipe burner or a ramjet combustion chamber cooled by air or gas flowing through a surrounding annular passage.
Investigation of a 0.6 hub-tip radius-ratio transonic turbine designed for secondary-flow study 4: rotor loss patterns as determined by hot-wire anemometers with rotor operating in a circumferentially uniform inlet flow field
Report discussing the use of hot-wire anemometers to measure circumferential traces of specific-mass-flow variation for various radial positions at the rotor exit. Results regarding the rotor blade-wake traces, relative total-pressure ratio, and centrifuging of low-momentum fluid are provided.
Smoke study of nozzle secondary flows in a low-speed turbine
Still and motion pictures were made of boundary-layer and wake secondary-flow phenomena visualized by smoke. Two annular cascades of turbine nozzles were used, both designed for constant discharge angle but differing in blade shape and suction-surface velocity distribution. Flows were similar to those obtained with pressure and angle measurements at near-sonic airspeeds. Boundary-layer cross-channel and trailing-edge radial flows caused vortices and an accumulation of low-momentum air at the hub, which may affect flow in following blade rows. Motion of a downstream rotor blade row produced pulsations in trailing-edge radial flow. The motion-picture supplement may be obtained on loan from NACA Headquarters, Washington, D.C.
Visualization of rotor tip secondary flows with blade tip air discharge and suction in a low-speed turbine
Smoke was used to visualize outer-wall secondary flows in a low-speed turbine utilizing rotor tip air discharge and suction. Photographs as well as visual observations of the effect of tip air discharge and suction were made by independently varying the direction and quantity of the tip air discharge and suction, and varying tip clearance, and main-stream air speed. In addition, the cross-sectional area of the hollow blade discharge opening was varied for the case of tip air discharge.
Experimental investigation of flow in an annular cascade of turbine nozzle blades of constant discharge angle
The experimental performance of turbine nozzle blades designed for a constant discharge angle was investigated at discharge hub Mach numbers of 1.18, 1.31, and 1.41. Flow characteristics are presented in terms of energy losses, angle gradients, and secondary flow effects. Blade efficiency decreased from 0.983 to 0.978 with increasing Mach number in the range investigated while angle variations in the loss regions became very large, indicating poorer blade performance than efficiency implies.
Development of Direct Contact Condensation Multistage Flash Distillation Process: Phase 3A
Report investigating the feasibility of the Atomics International Direct Contact Condensation Multistage Flash (DCC-MSF) Distillation process using "analytical and experimental studies on a direct contact condensation module and a plastic film heat exchanger. (p. iii) Contains further studies and evaluations of the direct-contact condensation unit and plastic film heat exchanger.
Development of Direct Contact Condensation Multistage Flash Distillation Process: Phase 1
Report investigating the feasibility of the Atomics International Direct Contact Condensation Multistage Flash (DCC-MSF) Distillation process using "analytical and experimental studies on a direct contact condensation module and a plastic film heat exchanger. (p. iii)
Development of Direct Contact Condensation Multistage Flash Distillation Process: Phase 2
Report investigating the feasibility of the Atomics International Direct Contact Condensation Multistage Flash (DCC-MSF) Distillation process using "analytical and experimental studies on a direct contact condensation module and a plastic film heat exchanger. (p. iii) Contains further studies and evaluations of the direct-contact condensation unit and plastic film heat exchanger.
Performance and Operational Studies of a Full-Scale Jet-Engine Thrust Reverser
Note presenting an axial-flow turbojet engine equipped with a hemispherical target thrust reverser that was pylon-mounted beneath the wing of a cargo airplane. Results regarding the performance of full-depth hemisphere, operational problems, and performance of modified hemisphere are provided.
Investigation of a full-scale, cascade-type thrust reverser
A double set of turning vanes was carried inside the jet tailpipe. To produce reverse thrust, the tailpipe opens into two side sections and the turning vanes move outward to form a V-shaped cascade, which deflects the exhaust-gas flow. Forward and reverse net thrust were measured over a range of engine speeds with the airplane stationary. Taxi tests were made to determine the comparative stopping distances using wheel braking and reverse thrust separately, and a combination of both. The effect of turning-vane spacing on thrust-reverser performance was determined by scale-model tests using unheated air.
Effect of Various Methods of Boundary-Layer Control on Performance of V-1710-93 Engine-Stage Supercharger
"Four methods of boundary-layer control were tried during an investigation to improve the flow in the impeller passages of a V-1710-93 engine-stage supercharger. The boundary layer along the impeller front shroud was removed by suction. In one method the removal was accomplished by recirculation of the air to the impeller inlet; in another method, by external removal. In the other methods, slots were cut through the impeller-blade faces first at 30 percent and then at 30 and 70 percent of the mean-flow-path length measured from leading edges of the rotating inlet guide vanes to introduce air from the high-pressure side of the blades into the region where stagnation and separation were suspected" (p. 1).
Performance of 19XB-2A Gas Turbine 1 - Effect of Pressure Ratio and Inlet Pressure on Turbine Performance for an Inlet Temperature of 800 Degrees R
"An investigation of the 19XB-2A gas turbine is being conducted at the Cleveland laboratory to determine the effect on turbine performance of various inlet pressures, inlet temperatures, pressure ratios, and wheel speeds. The engine of which this turbine is a component is designed to operate at an air flow of 30 pounds per second at a compressor rotor speed of 17,000 rpm at sea-level conditions. At these conditions the total-pressure ratio is 2.08 across the turbine and the turbine inlet total temperature is 2000 degrees R" (p. 1).
Effects of Partial Admission on Performance of a Gas Turbine
Report presenting an investigation of the effect of partial admission of the driving fluid on the performance of a representative full-admission, production-type gas turbine. Results regarding losses, full-admission performance, partial-admission performance, partial admission as a means of power control, and a comparison of partial admission with other methods of power control are provided.
Aerodynamic forces and moments of a seaplane on the water
From Introduction: "This report gives the results of wind-tunnel tests with a seaplane model as a contribution to the solution of the aerodynamic problems."
Pressure-Distribution Measurements on the Tail Surfaces of a Rotating Model of the Design BFW - M31
In order to obtain insight into the flow conditions on tail surfaces on airplanes during spins, pressure-distribution measurements were performed on a rotating model of the design BFW-M31. For the time being, the tests were made for only one angle of attack (alpha = 60 degrees) and various angles of yaw and rudder angles. The results of these measurements are given; the construction of the model, and the test arrangement used are described. Measurements to be performed later and alterations planned in the test arrangement are pointed out.
The Development of a Hollow Blade for Exhaust Gas Turbines
The subject of the development of German hollow turbine blades for use with internal cooling is discussed in detail. The development of a suitable blade profile from cascade theory is described. Also a discussion of the temperature distribution and stresses in a turbine blade is presented. Various methods of manufacturing hollow blades and the methods by which they are mounted in the turbine rotor are presented in detail.
Appendix I. Petrology Reports
"This appendix contains reproductions of five reports where were issued by the Petrology Laboratory of the Geochemical Support Department, Project Operations Divisions, Bendix Field Engineering Corporation (BFEC)" (p. 1 of Appendix). Each report includes a table describing the sample and representative photomicrographs for each sample category.
[Appendix II: Certificates of Assay]
"This appendix contains copies of certificates of assay that were issue by the Bendix Field Engineering Corporation (BEFC) Chemistry Laboratory, Geochemical Support Department, for analyses performed on Fission Neutron Water Factor Model samples." (p. 1 of Appendix)
Appendix IV. Construction Documents
Report containing documents related to the construction of of the Fission Neutron Water Factor Model.
A Model for Water Factor Measurements With Fission-Neutron Logging Tools
"This report describes the construction of the Fission Neutron Water Factor Model and also presents values for model parameters which are of interest in fission-neutron logging."
Appendix III. Gamma-Ray Logs from the Fission Neutron Water Factor Model
Charts depicting gamma-ray logs and and resulting tables of data resulting from the Fission Neutron Water Factor Model. "The gamma-ray logs in this appendix were run with a system known as the Calibration Facility Monitoring System. Sodium iodide detectors were used, and the system was operated in gross county mode." (p. 1 of Appendix)
Pulsed Neutron Measurement of Control Rod Worth
Reactivity measurements made by the pulsed neutron technique were compared with results obtained by conventional techniques. The pulsed neutron results were in good agreement with those obtained by stable period measurement and rod drop. Differential effectiveness of partially inserted rods was shown to be well represented by elementary perturbation theory. Finally, the pulsed neutron technique was found to be the only good method for measurement of large reactivity changes.
The Quaternary Geology of Rayburn's Salt Dome: North Louisiana Salt Dome Basin
The following report summarizes the conclusions and what's been done on the work on the Quaternary geological studies of Rayburn's Salt Dome, North Louisiana Salt Dome Basin.
Hard Rock Silo Prototype Test Site Selection Investigations
Abstract: Geologic field reconnaissance and geophysical evaluation of eight areas in the western part of the United States were made to locate a site for conducting tests of a prototype hard rock silo (HRS).
The Quaternary Geology of Vacherie Salt Dome, North Louisiana Salt Dome Basin: Volume 1
The following report summarizes the conclusions and what's been done on the work on the Quaternary geological studies on the Vacherie Salt Dome, North Louisiana Salt Dome Basin.
The Quaternary Geology of Vacherie Salt Dome, North Louisiana Salt Dome Basin: Volume 2
The following report provides a compilation of appendices focused on the geological investigations of Vacherie salt dome in the north Louisiana Salt Dome Basin.
Failure Analysis of Mark 1A Lithium/Iron Sulfide Battery
The Mark 1A lithium/iron sulfide electric-vehicle battery, which consisted of two 20-kW-hr modules containing 60 cells each, was fabricated by Eagle-Picher Industries, Inc. and delivered to ANL for testing in May 1979. During startup heating prior to electrical testing, a short circuit developed in one of the modules, which resulted in a progressive failure of the cells. The other module, which was alongside and connected in series, was unaffected by the failure. The initial indication of difficulty was a small drop in the voltage of several cells, followed by short circuits in the balance of the cells and localized temperatures above 1000 C. A team consisting of ANL and Eagle-Picher personnel conducted a detailed failure analysis as the failed module was disassembled. The other module was also examined for purposes of comparison. The general conclusion was that the short circuit was initiated by electrolyte leakage and resulting corrosion in the nearby region which formed metallic bridges between cells and the cell ray, or arcing between cells and the cell tray through the butt joints in the electrical insulation. The above two mechanisms were also believed to be responsible for the failure propagation.
Investigation in the Ames 12-Foot Pressure Wind Tunnel of a Model Horizontal Tail of Aspect Ratio 3 and Taper Ratio 0.5 Having the Quarter-Chord Line Swept Back 45 Degrees
Memorandum presenting an investigation to evaluate the effect of Reynolds number and Mach number on the aerodynamic characteristics of a horizontal tail of aspect ratio 3 equipped with a plain, sealed, full-span elevator. The line joining the quarter-chord points of the airfoil sections was swept back 45 degrees and the sections perpendicular to this line were the NACA 64A010. Results regarding the effect of Reynolds number and effects of leading-edge roughness and elevator-nose seal are provided.
Effects of Operating Propellers on the Wing-Surface Pressures of a Four-Engine Tractor Airplane Configuration Having a Wing with 40 Degrees of Sweepback
Memorandum presenting an investigation to evaluate the effects of operating propellers and of nacelles on the wing-surface pressures on a semispan model of a four-engine tractor airplane configuration with a 40 degree sweptback wing and aspect ratio of 10. Results regarding the effects of the nacelles with the propellers off, effects of flaps, and effects of operating propellers are provided.
The Forces and Pressure Distribution at Subsonic Speeds on a Plane Wing Having 45 Degrees of Sweepback, an Aspect Ratio of 3, and a Taper Ratio of 0.5
Memorandum presenting an investigation to determine the effects of scale and compressibility on the forces, moments, and pressure distribution on a wing with an aspect ratio of 3 and a taper ratio of 0.5. Lift, drag, and pitching-moment data and the chordwise distribution of static pressure at seven spanwise stations are presented for several sets of Reynolds and Mach numbers. The results indicated that for all Mach and Reynolds numbers in the test range, no apparently flow separation existed near the leading edge of the wing for lift coefficients less than 0.3.
Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel III : the effectiveness and hinge moments of a skewed wing-tip flap
Results of wind-tunnel tests of a semispan model of a triangular wing of aspect ratio 2 with a skewed wing-tip flap are presented. Lift, drag, pitching-moment, and hinge-moment data are included for subsonic Mach numbers up to 0.95. The flap showed extremely high hinge moments and low effectiveness as a longitudinal control. Although less affected by compressibility, this flap is indicated to be inferior to a constant-chord flap when applied to this triangular wing.
Pneumatic Injection Casting of Aluminum-Plutonium Fuel Elements
This report summarizes only that portion of the injection-casting experiments in which the castings were made with air pressure.
The Role of Glycolic Acid in the Oxidation Metabolism of Green Cells
In previous reports it was shown that glycolic acid appears as substrate and catalyst of oxidizing processes in the green suspension from barley leaves. In the present work are given the results of new investigations concerning the role of glycolic acids in the oxidation metabolism of green cells.
Organic Peroxide in Green Leaves
Provides chemical description of separating peroxide of formaldehyde from green extract.
Grand Canyon 1° x 2° NTMS area, Arizona: Data Report
From abstract: This data report presents results of ground water and stream/surface sediment reconnaissance in the National Topographic Map Series (NTMS) Grand Canyon 10 x 20 quadrangle. Surface samples (sediment) were collected from 1013 sites.
Grand Canyon 1° x 2° NTMS Area, Arizona: Data Report, Supplementary Data
Supplementary data containing tabulated elemental concentration data in surface sediment and ground water samples, in addition to areal distribution maps, histograms, and cumulative frequency plots, and a user's guide to accompany a hydogeochemical and stream sediment reconnaissance report of the Grand Canyon 1° x 2° NTMS Area, Arizona.
Klamath Falls 1° x 2° NTMS Area, Oregon: Data Report (Abbreviated)
This abbreviated data report presents results of groundwater and stream/surface sediment reconnaissance in the National Topographic Map Series (NTMS) Klamath Falls 1* x 2* Quadrangle.
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