Memorandum presenting an investigation of coolant-flow rates for a turbine rotor blade with return-flow type of coolant-passage configuration formed by fins within a capped blade shell with both hydrogen and methane fuels as coolants. Results regarding spanwise blade and coolant temperature distributions, effects of coolant inlet temperature on hydrogen-coolant-flow requirements, comparison of return-flow-blade coolant requirements, effect of fin thickness and fin height, comparison of hydrogen and methane as coolants, and feasibility of fuel-cooled turbines are provided.

From Introduction: "The purpose of this report was to investigate the possible use of engine fuels (hydrogen and methane) as coolants for turbine rotor blades and to determine the pressure-drop characteristics of these coolants for a turbine blade with a more effective coolant-passage configuration than that considered in reference 5 but for the same engine and flight conditions."

Report presenting an evaluation of a number of factors affecting engine-airframe arrangements in terms of range. Appropriate equations are developed and evaluated for a range of Mach numbers, ramjet and turbojet engines at several cycle temperatures, and two airplane lift-drag ratios. Some of the factors explored include inlet locations, jet cant for lift, engine moments for trim, a combination of the three factors, and the use of boundary layer in the engine.

None

This report addresses the constant-pressure leak rate gage.

Report presenting an improved air-cooled turbine blade that was described, stress-analyzed, and evaluated in a full-scale turbojet engine. The blade consists of a sheet-metal outer shell and an internal strut of partial blade length. The effect on blade rupture life of varying outer-shell thickness, strut length, blade temperature distribution, and corrugation pitch and amplitude are provided.

Report presenting a transonic investigation in the 16-foot transonic tunnel to determine the effects of spanwise location of a flap-type aileron on the lateral characteristics of a 4-percent-thick sweptback-wing-fuselage model. Results regarding the effect of aileron spanwise position on roll and lift effectiveness, tail effects, and effect of spanwise aileron position on complete model rolling-moment characteristics are provided.

A methed is descrihed for the treatment of radioactive neutralized nitric acid waste solutions. The process consists of electrolysis of sodium nitrate solutions and recycle the caustic formed to neutralize incoming nitric acid ate. Removal of a large fraction of the bulk inert substances by this method allows greater reductions in waste volume than conventional treatment by evaporation alone. Process chemistry studies show that a large fraction of the nitrate ion in alkaline solution can be electrolytically reduced to gaseous nitrogen reduction products at reasonable current efficiencies. Process engineering studies have resulted in the development of a prediction equation for the design of electrolysis cells used in the process. Pilot plant studies using cold'' nitric acid waste have demonstrated the feasibility of the electrolytic recycle methed. A preliminary cost estimate was performed which iadicates a cost of from 75 to 95 per initial gallon of waste processed. Basis for this estimate is a conceptual design of a plant capable of handling the highlevel waste produced in reprocessing one ton of uranium metal per day. These costs are considered reasonable in a nuclear power economy, and indications are that ultimate disposal of the concentrated waste in clay may be possible. (auth)

Four strut-supported, transpiration-cooled turbine blades were investigated experimentally in a turbojet engine. The blade shells were fabricated by the mold-sintering method with spherical stainless-steel powder. Two blades were investigated in order to evolve suitable capping methods for the blade tip. Two other blades were used to evaluate the durability of the porous-shell material. The blades were investigated at a turbine-tip speed of 1305 feet per second, an average turbine-inlet temperature of about 1670 F, and at a porous-shell temperature limited to a maximum of approximately 1040 F.

The principal objectives of the exploratory diamond drilling programs conducted by the U.S. Atomic Energy Commission on Frey Point Mesa were to determine the presence of minable uranium ore; to study the lithologic and structural characteristics of paleostream channels and their relation to ore occurrence; and to accumulate geologic information essential for an appraisal of the uranium resources of the area.

Memorandum presenting tests conducted to determine the flight characteristics of an F-86F airplane equipped with an area-suction-type boundary-layer control installation on the trailing-edge flaps. Measurements were made of the lift, drag, and engine bleed-air requirements. Results regarding the aerodynamic characteristics as well as some miscellaneous characteristics are provided.

Report presenting an investigation to determine and improve on the foreign-object-retention capabilities and pressure-loss characteristics of rectractable engine-inlet screens. Testing occurred with two commerically made retractable screens installed in the engine-inlet sections for which they were designed. Results regarding the retention for both the original and modified screens and pressure tests are provided.

This document provides a summary of facilities, both proposed and constructed, and programs of the Hanford Atomic Products Operation. Budgets, by program, are also provided. (FI)

Memorandum presenting various reports regarding the use of hydrogen for turbojet and ramjet powered flight. Some of the characteristics considered include the combustion properties, potential fueling problems, and flight experience with hydrogen on-board.

Memorandum presenting a seven-part investigation of hydrogen for turbojet and ramjet powered flight. The combustion characteristics of hydrogen, in ramjets and afterburners, and in turbojet engines are described.

Report presenting the aerodynamic load characteristics for a wing-body combination for a range of Mach numbers and angles of attack. Two wings with the same dimensions but different types of construction (one of solid steel, one of plastic with an inner steel core) were tested. Results regarding flow studies, chordwise pressure distributions, spanwise load distributions, panel loads, center of loads, and twist distribution are provided.

Memorandum presenting an investigation to determine the internal flow performance of a fixed 14 degree ramp inlet from zero to 20 degrees angle of attack conducted at three free-stream Mach numbers. The inlet was mounted in three circumferential fuselage locations and utilized inlet throat and fuselage boundary-layer removal.

Report presenting an investigation of resistance screens for the purpose of obtaining uniform flow in ducts. The new screen designs consisted of several different screen shapes with the elements set at oblique angles (swept) to the flow. Results regarding a rectangular channel and diffuser investigation are provided.

Report presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine the chordwise and spanwise load distribution on a thin 60 degree delta wing-fuselage model with double slotted flaps and spoilers mounted on the flap. The results are presented in the form of lateral aerodynamic characteristics of the plain-wing and double-slotted-flap configurations and as normal-force coefficients and pitching-moment coefficients of the wing, vane, flap, and spoiler, sample pressure plots, sample span-load distributions, tabulated pressure coefficients, and tabulated section normal-force coefficients and section pitching-moment coefficients.

None

Report issued by the Brookhaven National Laboratory discussing methods of processing reactor fuels such as uranium. As stated in the objective, "the primary objective of the project was to determine the effect of temperature, solution composition, and flow rate on the dissolving time for natural uranium slugs of varying history" (p. 2). This report includes tables, illustrations, and photographs.

Characteristic exhaust velocity of a 200-pound-thrust rocket engine was evaluated for fuel temperatures of -90 degrees, and 200 degrees f with a spray formed by two impinging heptane jets reacting in a highly atomized oxygen atmosphere. Tests covered a range of mixture ratios and chamber lengths. The characteristic exhaust-velocity efficiency increased 2 percent for a 290 degree f increase in fuel temperature. This increase in performance can be compared with that obtained by increasing chamber length by about 1/2 inch. The result agrees with the fuel-temperature effect predicted from an analysis based on droplet evaporation theory. Mixture ratio markedly affected characteristic exhaust velocity efficiency, but total flow rate and fuel temperature did not.

Although the Born-von Karman treatment of the dynamics of crystal lattices is superior to that of Debye, the conABSTRACTS tinuum model of Debye is more amenable to computation; therefore the Debye treatment is used to obtain frequencies at a maximum energy. From the classic Hamiltonian of the solid, quantization is carried out by the Schroedinger method. The thermodymamic functions are obtained, and the mean square displacement is derived. (J.S.R.)

Property changes in polycrystalline graphite resulting from reactor irradiations at temperatures up to 185 deg C and over a range of exposures up to 1135 Mwd/ CT have been determined. Changes in stored energy, thermal conductivity, sample length, and C/sub O/ interlayer crystallite spacing are markedly decreased as exposure temperature is increased. Electrical resistivity changes are also less at higher exposure temperatures, but this property change does not depend as strongly on temperature as the others. Isothermal annealing studies of C/sub O/ changes were conducted on a number of irradiated samples. The data were analyzed assuming a large number of processes distributed in activation energy. The results are summarized in activation energy spectra in which the distribution of C/sub O/ damage is given as a function of the activation energy required for annealing. It is found that not only does a higher exposure temperature decrease the total amount of property change, but also the distributlon of damage accumulated is considerably different. Results are discussed in terms of the radiation damage model suggested by Hennig and Hove. This model is compatible with the experimental results presented. (auth)