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An accurate and rapid method for the design of supersonic nozzles

Description: From Introduction: "This report presents a computational procedure which provides for the rapid and accurate calculation of any streamline in a series of special flows. Detailed information is given on the boundary conditions and equations used for computing the characteristic nets and stream function."
Date: February 1955
Creator: Beckwith, Ivan E & Moore, John A
Partner: UNT Libraries Government Documents Department

Analysis of heat addition in a convergent-divergent nozzle

Description: From Introduction: "The purpose of this report is to treat analytically heat addition heat addition to a divergent stream with initially sonic flow and to employ the results thus obtained in evaluating the effect of delayed combustion on convergent-divergent nozzle performance."
Date: April 1953
Creator: Hearth, Donald P & Perchonok, Eugene
Partner: UNT Libraries Government Documents Department

Annular-jet ejectors

Description: From Summary: "Included in the report are the results of total-pressure surveys made at downstream ends of the mixing tubes."
Date: November 1949
Creator: Reid, Elliott G
Partner: UNT Libraries Government Documents Department

The aerodynamic design of high Mach number nozzles utilizing axisymmetric flow with application to a nozzle of square test section

Description: From Introduction: "A method for the design of three-dimensional nozzles based on axi-symmetric flow is presented in this paper. The design method presented in this paper is general; however, as an illustrative example of the design of a Mach number 10 nozzle with square test section is included."
Date: June 1952
Creator: Beckwith, Ivan E; Ridyard, Herbert W & Cromer, Nancy
Partner: UNT Libraries Government Documents Department

The aerodynamic design and calibration of an asymmetric variable Mach number nozzle with a sliding block for the Mach number range 1.27 to 2.75

Description: From Introduction: "This paper presents the basic design method and experimental results of calibration of a nozzle which was constructed to conform to the analytically determined ordinates."
Date: April 1953
Creator: Burbank, Paige B & Byrne, Robert W
Partner: UNT Libraries Government Documents Department

Altitude performance characteristics of tail-pipe burner with variable-area exhaust nozzle

Description: From Introduction: "Data are presented to show the effects of tail-pipe fuel-air ratio, altitude, and flight Mach number on tail-pipe-burner performance at rated engine speed and approximately constant turbine-outlet temperature. Operational characteristics of the tail-pipe burner and variable-area exhaust nozzle are also reported."
Date: August 11, 1950
Creator: Jansen, Emmert T & Thorman, H Carl
Partner: UNT Libraries Government Documents Department

Analytic determination of the discharge coefficients of flow nozzles

Description: From Introduction: "In rounded-approach nozzles with discharge coefficients close to unity, the frictional effects are concentrated in the boundary layer. A method of obtaining an analytical relation among the discharge coefficient, Reynolds number, and the nozzle geometry by utilization of elementary boundary-layer theory is presented herein."
Date: April 1955
Creator: Simmons, Frederick S
Partner: UNT Libraries Government Documents Department

Analytical investigation of turbines with adjustable stator blades and effect of these turbines on jet-engine performance

Description: From Introduction: "A comparison is also made of the actual performance of two contemporary jet engines with estimated performance, assuming the engines were equipped with adjustable-angle stators and adjustable exhaust nozzles. Charts are presented that aid in estimating the performance of adjustable-stator turbines."
Date: July 17, 1950
Creator: Silvern, David H & Slivka, William R
Partner: UNT Libraries Government Documents Department

Shellside Waterflow Pressure Drop and Distribution in Industrial-Size Test Heat Exchanger

Description: The shellside pressure drop between the inlet and outlet nozzles as well as the pressure drops through individual sections of different shell-and-tube test-exchanger configurations are measured under water flow. The segmentally baffled test exchanger is nominally 0.6 m (2 ft) in diameter, 3.7 m (12 ft) long and contains a tube bundle of 19 mm (0.75 in.) outside-diameter tubes. Results are reported of 24 test cases obtained from various combinations of parameters: 30 degrees triangular or 90 degrees square tube layout patterns (all on a 1.25 pitch-to-diameter ratio), numbers of cross-passes, sizes of nozzles, plain or finned tubes, and full or special fix tube bundles. The exponential change of pressure drop as a function of flow-rate is also investigated and an attempt is made to calculate nozzle losses.
Date: January 1983
Creator: Halle, Henry & Wambsganss, M. W.
Partner: UNT Libraries Government Documents Department

Method and Apparatus for Atomizing Fluids with a Multi-Fluid Nozzle

Description: The invention relates to a method and apparatus for atomizing liquids. In particular, the present invention relates to a method and apparatus for atomizing heavy hydrocarbon fuels such as diesel, as part of a fuel reforming process. During normal operating conditions the fuel is atomized by a high pressure fluid. Under start-up conditions when only a low pressure gas is available the fuel films across part of the nozzle and is subsequently atomized by a radially directed low pressure dispersion gas.
Date: December 7, 2004
Creator: Novick, Vincent J. & Ahluwalia, Rajesh K.
Partner: UNT Libraries Government Documents Department

A Method of Calculating Boundary-Layer Thickness in Axisymmetric Nozzles with Laminar Hypersonic Flow

Description: Abstract: "The excellent agreement between measured boundary layer thickness and thickness calculated by Sivells and Payne recommends their method for calculating turbulent boundary layer growth in axisymmetric hypersonic nozzles. It was thought worthwhile to adapt their approach to the laminar boundary layer. This analysis, along with a limited amount of corroborating data, is presented herein."
Date: October 1959
Creator: Johnson, Arlo F.
Partner: UNT Libraries Government Documents Department

A Low-Waste Electrospray Method for Applying Chemicals and Finishing Agents to Textiles Zh

Description: This electrospray technology works by applying the desired chemicals onto a substrate as electrically generated, charged sprays. By imposing a potential difference between the application nozzle and the target, it is possible to precisely direct and control the spray. This electrospray method of application gives a small droplet size and a relatively uniform size distribution, with the added advantage of an easily controllable spray angle. It potentially offers substantial improvement over traditional methods in the area of application uniformity, resulting in improved product quality. Additionally, since the chemicals are electrically directed straight onto the fiber with a minimum of overspray, the electrospray method holds promise in the area of waste reduction, resulting in lowered production cost.
Date: August 1, 1999
Creator: Alexander, D.A. & Zhang, X.
Partner: UNT Libraries Government Documents Department

Synthetic jets at large Reynolds number and comparison to continuous jets

Description: Experimental measurements and flow visualization of synthetic jets and similar continuous jets are described. The dimensionless stroke length necessary to form a 2-D synthetic jet is between 5 and 10, with wider-nozzle jets consistently requiring a smaller value. Synthetic jets are wider, slower and have more momentum than similar continuous jets. Synthetic jets are generated using four nozzle widths that vary by a factor of four, and the driving frequency is varied over an order of magnitude. The resultant jets are in the range 13.5 < L{sub o}/h < 80.8 and 695 < Re{sub Uo} < 14700. In spite of the large range of stroke lengths, the near-field behavior of the synthetic jets scales with L{sub o}/h.
Date: January 1, 2001
Creator: Smith, B. L. (Barton L.) & Swift, G. W. (Gregory W.)
Partner: UNT Libraries Government Documents Department

An Experimental Investigation of Two-Phase, Two-Component Flow in a Horizontal, Converging-Diverging Nozzle

Description: Report that "describes an investigation of the flow characteristics in a horizontal, converging-diverging nozzle for a two-phase, two-component system" (p. 1) using air and water and "attempting to determine the effects of accelerating the liquid phase by the gaseous phase" (p. 1).
Date: July 1963
Creator: Vogrin, Joseph A., Jr.
Partner: UNT Libraries Government Documents Department

Experimental characterization of spin motor nozzle flow.

Description: The Mach number in the inviscid core of the flow exiting scarfed supersonic nozzles was measured using pitot probes. Nozzle characterization experiments were conducted in a modified section of an obsolete M = 7.3 test section/nozzle assembly on Sandia's Hypersonic Wind Tunnel. By capitalizing on existing hardware, the cost and time required for tunnel modifications were significantly reduced. Repeatability of pitot pressure measurements was excellent, and instrumentation errors were reduced by optimizing the pressure range of the transducers used for each test run. Bias errors in probe position prevented us from performing a successful in situ calibration of probe angle effects using pitot probes placed at an angle to the nozzle centerline. The abrupt throat geometry used in the Baseline and Configuration A and B nozzles modeled the throat geometry of the flight vehicle's spin motor nozzles. Survey data indicates that small (''unmeasurable'') differences in the nozzle throat geometries produced measurable flow asymmetries and differences in the flow fields generated by supposedly identical nozzles. Therefore, data from the Baseline and Configuration A and B nozzles cannot be used for computational fluid dynamics (CFD) code validation. Configuration C and D nozzles replaced the abrupt throat geometry of Baseline and Configuration A and B nozzles with a 0.500-inch streamwise radius of curvature in the throat region. This throat geometry eliminated the flow asymmetries, flow separation in the nozzle throat, and measurable differences between the flow fields from identical nozzles that were observed in Baseline/A/B nozzles. Data from Configuration C and D nozzles can be used for CFD code validation.
Date: November 1, 2006
Creator: Erven, Rocky J.; Peterson, Carl Williams & Henfling, John Francis
Partner: UNT Libraries Government Documents Department

Stress analyses of flat plates with attached nozzles. Vol. 3. Experimental stress analyses of a flat plate with two closely spaced nozzles of equal diameter attached

Description: The complete test results for a flat plate with two closely spaced nozzles attached are presented. Test loadings were 1:1, 1:2, and 2:1 biaxial planar tension loadings on the plate, axial thrust loadings applied separately to the nozzles, and bending moment loadings applied to the nozzles both within and normal to the plane of symmetry containing the nozzle axes. The test plate was 36 x 36 x 0.375 in., and the attached nozzles had outer diameters of 2.625 in. and wall thicknesses of 0.250 in. The nozzles were located in the center of the plate with their centers 3.0 in. apart and were considered to be free of weld distortions and irregularities in the junction region. 6 references. (auth)
Date: December 1, 1975
Creator: Bryson, J.W. & Swinson, W.F.
Partner: UNT Libraries Government Documents Department

Development test report for the high pressure water jet system nozzles

Description: The high pressure water jet nozzle tests were conducted to identify optimum water pressure, water flow rate, nozzle orifice size and fixture configuration needed to effectively decontaminate empty fuel storage canisters in KE-Basin. This report gives the tests results and recommendations from the these tests.
Date: September 28, 1995
Creator: Takasumi, D.S.
Partner: UNT Libraries Government Documents Department

Nozzle mixing apparatus

Description: This invention is comprised of a nozzle device for causing two fluids to mix together. In particular, a spray nozzle comprise two hollow, concentric housings, an inner housing and an outer housing. The inner housing has a channel formed therethrough for a first fluid. Its outer surface cooperates with the interior surface of the outer housing to define the second channel for a second fluid. The outer surface of the inner housing and the inner surface of the outer housing each carry a plurality of vanes that interleave but do not touch, each vane of one housing being between two vanes of the other housing. The vanes are curved and the inner surface of the outer housing and the outer surface of the inner housing converge to narrow the second channel. The shape of second channel results in a swirling, accelerating second fluid that will impact the first fluid just past the end of the nozzle where mixing will take place.
Date: December 31, 1992
Creator: Mensink, D.L.
Partner: UNT Libraries Government Documents Department

Comparison of ASME Code NB-3200 and NB-3600 results for fatigue analysis of B31.1 branch nozzles

Description: Fatigue analyses wre conducted on two reactor coolant system branch nozzles in an operating PWR designed to the B31.1 Code, for which no explicit fatigue analysis was required by the licensing basis. These analyses were performed as part of resolving issues connected with NRC`s Fatigue Action Plan to determine if the cumulative usage factor (CUF) for these nozzles, using the 1992 ASME Code and representative PWR transients, were comparable to nozzles designed and analyzed to the ASME Code. Both NB-3200 and NB-3600 ASME Code methods were used. NB-3200 analyses included the development of finite element models for each nozzle. Although detailed thermal transients were not available for the plant analyzed, representative transients from similar PWRs were applied in each method. CUFs calculated using NB-3200 methods were significantly less than using NB-3600. The paper points out differences in analysis methods and highlights difficulties and unknowns in performing more detailed analyses to reduce conservative assumptions.
Date: June 1, 1996
Creator: Nitzel, M.E.; Ware, A.G. & Morton, D.K.
Partner: UNT Libraries Government Documents Department


Description: We have continued to carry out creative small-scale experiments in the deep ocean to investigate the science underlying questions of possible future large-scale deep-ocean CO{sub 2} sequestration as a means of ameliorating greenhouse gas growth rates in the atmosphere. This project is closely linked to additional research funded by the DoE Office of Science, and to support from the Monterey Bay Aquarium Research Institute. The listing of project achievements here over the past year reflects these combined resources. Within the last project year we have: (1) Published a significant workshop report (58 pages) entitled ''Direct Ocean Sequestration Expert's Workshop'', based upon a meeting held at MBARI in 2001. The report is available both in hard copy, and on the NETL web site. (2) Carried out three major, deep ocean, (3600m) cruises to examine the physical chemistry, and biological consequences, of several liter quantities released on the ocean floor. (3) Carried out two successful short cruises in collaboration with Dr. Izuo Aya and colleagues (NMRI, Osaka, Japan) to examine the fate of cold (-55 C) CO{sub 2} released at relatively shallow ocean depth. (4) Carried out two short cruises in collaboration with Dr. Costas Tsouris, ORNL, to field test an injection nozzle designed to transform liquid CO{sub 2} into a hydrate slurry at {approx}1000m depth. (5) In collaboration with Prof. Jill Pasteris (Washington University) we have successfully accomplished the first field test of a deep ocean laser Raman spectrometer for probing in situ the physical chemistry of the CO{sub 2} system. (6) Submitted the first major paper on biological impacts as determined from our field studies. (7) Submitted a paper on our measurements of the fate of a rising stream of liquid CO{sub 2} droplets to Environmental Science & Technology. (8) Have had accepted for publication in Eos the first brief ...
Date: September 30, 2002
Creator: Brewer, Dr. Peter & Barry, Dr. James
Partner: UNT Libraries Government Documents Department

D0 Silicon Upgrade: Estimates of the Deflections and Stresses of the Toshiba Cold Mass Support System

Description: Tensile stresses in the Toshiba cold mass support links generated by the loadings the coil is subject to, and the deflections the coil experiences as a result of these loadings, are estimated. The axial links are conservatively designed and it should be reasonably easy to ensure that the three links at each end of the coil carry approximately equal loads. Small deviations from this ideal should not have great consequence as a system-of-three is somewhat forgiving in this regard. The use of preload makes the north operating deflection equal to the smaller south operating deflection, possibly a convenience when the nozzle design is contemplated. Toshiba has indicated they will establish the desired preload using strain gauges near the warm ends of the links.
Date: November 22, 1995
Creator: Smith, R.P.
Partner: UNT Libraries Government Documents Department


Description: The injectors for the Capstone turbine have the general design shown in figure 1 below. It consists of an airblast atomizer with a cylindrical fuel nozzle and an annular air passage surrounding it. The airblast atomizer is surrounded by a 'mixing tube' with circular holes just downstream of the atomizer outlet and swirler holes further downstream. During operation, these holes bring 'hot' air/gases to help vaporize and provide premixed fuel and air for combustion downstream of the 'mixing' tube.
Date: January 1, 2007
Creator: KRISHNA,C.R.
Partner: UNT Libraries Government Documents Department