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Intermediate Heat Exchanger and Steam Generator Final Design. Volume 4. Operation & Maintenance

Description: This technical report contains the operation and maintenance specifications for the intermediate heat exchanger and the steam generator. The report contains eight sections: (1) General Information, (2) Shipping and Installation, (3) Operation Procedures, (4) Scram and Casualty Shutdowns, (5) Leaks, (6) Instrumentation and Control, (7) Maintenance, and (8) four Appendixes (a) Boiler Water Chemistry Recommendations, (b) Final Concept Drawings, (c) Industrial Nucleonics Literature on Liquid Level… more
Date: September 30, 1960
Creator: Alco Products (Firm).
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Intermediate Heat Exchanger Preliminary Design. Vol. 1, IHX Preliminary Design

Description: Preface: The intermediate heat exchanger is designed for operation in a nuclear power plant using liquid sodium as the primary and secondary coolant. Since the primary fluid coming from the reactor is radioactive, the purpose of the IHX is to transfer heat to a nonradioactive fluid which then goes to a steam generator. Because of this activity the until will be enclosed in a concrete pit and will not be accessible during periods of operation. Immediately after shut down it will be necessary … more
Date: February 28, 1959
Creator: Alco Products (Firm)
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Intermittent-flow coefficients of a poppet valve

Description: "Flow coefficients were determined for the inlet valve of a modern air-cooled cylinder during operation of the valve. The cylinder head with valves was mounted on a large tank that could be evacuated. Operating the valve with a rotating cam allowed air to flow through the valve into the evacuated tank. The change of pressure in the tank was a measure of the amount of air flowing though the valve in a given number of cycles. The flow coefficients were determined from the pressure across the valv… more
Date: April 1939
Creator: Waldron, C. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal and external aerodynamics of ducted bodies at supersonic speeds

Description: Report presenting a method for calculating the lift, moment, and pressure drag of slender open-nose bodies of revolution at supersonic speeds. An application of the method to a typical ramjet fuselage is shown to give excellent agreement with available experimental data.
Date: April 1946
Creator: Brown, Clinton E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal Bunching in the Alternating Gradient Synchrotron (AGS)

Description: Four methods of rebunching protons within Brookhaven's AGS are discussed. The first method involving switching off the old r-f and switching on the new r-f simultaneously with the new r-f increasing adiabatically seems impractical. Two other methods utilize gradual removal of the old r-f voltage and introduction of the new r-f voltage, or the reverse. Removal of the old r-f voltage followed by introduction of the new seems to give the best results. Several phase diagrams are included. (D.C.W.)
Date: January 16, 1961
Creator: Robertson, D. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal characteristics and performance of an aerodynamically controlled, variable-discharge convergent nozzle

Description: Report presenting a study in which the effective flow area of a convergent exhaust nozzle was reduced by injecting a high-pressure secondary jet into the nozzle near the exit. Analytical expressions relating the performance with significant design and operating variables were developed. Some of the configurations, altered to operate as jet deflectors, produced significant values of side force but also operated at reduced effective flow area.
Date: July 1958
Creator: McArdle, Jack G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal characteristics and performance of several jet deflectors at primary-nozzle pressure ratios up to 3.0

Description: Report presenting testing of several model jet deflectors to determine the effects of design variables on their performance and operating characteristics. The deflectors were designed to be adaptable to convergent-nozzle, plug-nozzle, and ejector turbojet exhaust systems. Results regarding the swiveled-nozzle jet deflectors, auxiliary-nozzle jet deflectors, mechanical jet deflectors, and miscellaneous jet deflectors are provided.
Date: June 1958
Creator: McArdle, Jack G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal Conversion Coefficients of the 2+-0+, E2 Transitions in Even-Even Sm152[over]90 and Gd152[over]88

Description: From abstract: "To investigate the deviation of the internal conversion coefficients of E2 transitions from theoretical computations and their dependence on nuclear deformation, the total internal conversion coefficient of the 121.8-kev 2+-0+ transition in ellipsoidal Sm152[over]90 was measured to be 1.135 ± 0.010 with a high accuracy coincidence-sum method. The K-shell to total internal conversion ratio was determined to be 0.588 ± 0.003 with a [beta] spectrometer...The experiment revealed no … more
Date: July 17, 1961
Creator: Lu, D. C. & Schupp, G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal film cooling experiments in 4-inch duct with gas temperatures to 2000 degrees F

Description: Report presenting an investigation of the cooling effectiveness of water films on the inner surface of a well-insulated, 4-inch-diameter duct with air flowing through the duct at a range of temperature and Reynolds numbers. Results regarding the effect of the gas temperature and mass velocity on liquid-cooled length, effect of coolant flow on liquid-cooled length, and some suggestions for further investigation are provided. Equations for correlation are created from the data.
Date: September 21, 1950
Creator: Kinney, George R. & Sloop, John L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal-film-cooling experiments with 2- and 4-inch smooth-surface tubes and gas temperatures to 2000 degrees Fahrenheit

Description: Report presenting an investigation of liquid-film cooling at a variety of air temperatures and Reynolds numbers. Results regarding the effect of coolant flow per circumferential length on liquid-cooled length, correlation of heat transfer from hot gas to liquid film for constant coolant flow per circumferential length, and generalized plot of film-cooling data based on heat-transfer correlation at constant coolant flow per circumferential length are provided.
Date: April 29, 1952
Creator: Kinney, George R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal-Film Cooling of Rocket Nozzles

Description: Experiments were conducted with 1000-pound-thrust rocket engine to determine feasibility of cooling convergent-divergent nozzle by internal film of water introduced at nozzle entrance. Water flow of 3 percent of propellant flow reduced heat flow into nozzle to 55 percent of uncooled heat flow. Introduction of water by porous ring before nozzle resulted in more uniform coverage of nozzle than water introduced by single arrangement of 36 jets directed along nozzle wall. Water flow through porous … more
Date: June 8, 1948
Creator: Sloop, J. L. & Kinney, George R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal Flow and Burning Characteristics of 16-inch Ram Jet Operating in a Free Jet at Mach Numbers of 1.35 and 1.73

Description: The effects of mass-flow ratio on the additive drag and normal-shock position of a single oblique-shock diffuser are presented. Also evaluated is the variation with operating condition of the velocity distribution at the combustion-chamber inlet. A comparison with connected-pipe data is included.
Date: May 21, 1951
Creator: Perchonok, Eugene & Farley, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal-Flow Systems for Aircraft

Description: "An investigation has been made to determine efficient arrangements for an internal-flow system of an aircraft when such a system operates by itself or in combination with other flow systems. The investigation included a theoretical treatment of a problem and tests in the NACA 5-foot vertical wind tunnel of inlet and outlet openings in a flat plate and in a wing. When an internal-flow system tends to decrease the final velocity of it's wake, the results showed that it should be arranged in seri… more
Date: October 1940
Creator: Rogallo, F. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal-Flow Systems for Aircraft

Description: An investigation has been made to determine efficient arrangements for an internal-flow system of an aircraft when such a system operates by itself or in combination with other flow systems. The investigation included a theoretical treatment of the problem and tests in the NACA 5-foot vertical wind tunnel of inlet and outlet openings in a flat plate and in a wing.
Date: 1941
Creator: Rogallo, F. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal-Friction Study of Aluminum Alloy Containing 4 Weight Percent Copper

Description: Note presenting a study of aluminum alloy containing 4 weight percent copper during aging using low-frequency internal-friction measurements in torsional and flexural vibration. Both polycrystalline and single-crystal specimens exhibit an initial internal-friction peak at 173 degrees Celsius after solution treatment and quenching.
Date: August 1958
Creator: Berry, B. S. & Nowick, A. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal-liquid-film-cooling experiments with air-stream temperatures to 2000 degrees F. in 2- and 4-inch-diameter horizontal tubes

Description: Report presents the results of an investigation conducted to determine the effectiveness of liquid-cooling films on the inner surfaces of tubes containing flowing hot air. Experiments were made in 2- and 4-inch-diameter straight metal tubes with air flows at temperatures from 600 degrees to 2000 degrees F. and diameter Reynolds numbers from 2.2 to 14 x 10(5). The film coolant, water, was injected around the circumference at a single axial position on the tubes at flow rates from 0.02 to .24 pou… more
Date: May 27, 1952
Creator: Kinney, George R.; Abramson, Andrew E. & Sloop, John L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal performance at Mach number to 2.0 of two auxiliary inlets immersed in fuselage boundary layer

Description: Report presenting an experimental investigation to evaluate the internal performance of two types of auxiliary air inlets, a submerged and a scoop inlet, operating within the turbulent boundary layer existing on the bottom of a typical supersonic fighter aircraft afterbody. Results regarding boundary-layer flow and inlet performance are provided.
Date: March 10, 1954
Creator: Pennington, Donald B. & Simon, Paul C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal performance characteristics of variable-throat plug- and vaned-type convergent-divergent nozzles

Description: Investigation of the internal performance characteristics of three types of variable-throat convergent-divergent nozzles over a wide range of pressure ratios. Only small differences in peak thrust coefficient between the three types of variable-throat convergent-divergent nozzles were obtained.
Date: June 23, 1953
Creator: Krull, H. George; Steffen, Fred W. & Ciepluch, Carl C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal performance of a series of circular auxiliary-air inlets immersed in a turbulent boundary layer : Mach number range: 1.5 to 2.0

Description: Report presenting an experimental investigation to determine the internal performance characteristics of a series of circular, open-nose auxiliary air inlets immersed into the supersonic, turbulent boundary layer generated by the 8- by 6-foot supersonic wind tunnel. Inlet critical total-pressure and mass-flow ratios were reasonably predicted by theory at all conditions investigated. Results regarding boundary-layer flow, inlet performance, and diffuser-exit pressure fluctuations are provided.
Date: March 3, 1955
Creator: Simon, Paul C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal performance of several auxiliary air inlets immersed in a turbulent boundary layer at Mach numbers of 1.3, 1.5, and 2.0

Description: Internal performance of normal-shock rectangular, circular, and scoop inlets and of external-compression inlets experimentally obtained with varying immersion in a turbulent boundary layer. Recoveries varied from about 95 percent of theoretical in the free stream to 80 percent with complete immersion, while the corresponding mass flows were usually above 95 percent of theoretical. Turning of the flow through 10 degrees caused losses in pressure recovery of 0.03 to 0.07. External compression did… more
Date: January 18, 1957
Creator: Huff, Ronald G. & Anderson, Arthur R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal Performance of Several Divergent-Shroud Ejector Nozzles with High Divergence Angles

Description: From Summary: "Nine divergent-shroud ejector configurations were investigated to determine the effect of shroud divergence angle on ejector internal performance. Unheated dry air was used for both the primary and secondary flows. The decrease in the design-point thrust coefficient with increasing flow divergence angle (angle measured from primary exit to shroud exit) followed very closely a simple relation involving the cosine of the angle. This indicates that design-point thrust performance fo… more
Date: October 2, 1957
Creator: Trout, Arthur M.; Papell, S. Stephen & Povolny, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal performance of several types of jet-exit configurations for supersonic turbojet aircraft

Description: Investigation of the internal performance characteristics of several jet-exit configurations over a wide range of pressure ratios, which are summarized to provide an overall picture of jet-exit performance. The configurations investigated include a convergent nozzle, fixed convergent-divergent nozzles, an adjustable plug-type convergent-divergent nozzle, and jet ejectors. Results regarding the performance of several jet-exit configurations and matching adjustable jet exits to supersonic aircraf… more
Date: January 13, 1953
Creator: Fleming, William A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal Performance of Two-Dimensional Wedge Exhaust Nozzles

Description: Memorandum presenting an experimental investigation of four rectangular-throat two-dimensional wedge exhaust nozzles. Three of the nozzles were designed to conform to Prandtl-Meyer streamlines for pressure ratios of 5, 10, and 24, and a fourth, arbitrarily contoured, with a length less than that required for isentropic expansion, was designed for a pressure ratio of about 9.
Date: February 28, 1957
Creator: Beale, William T. & Povolny, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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