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  • 1
    Online Resource
    Online Resource
    SAGE Publications ; 1991
    In:  International Journal of STD & AIDS Vol. 2, No. 3 ( 1991-05), p. 213-214
    In: International Journal of STD & AIDS, SAGE Publications, Vol. 2, No. 3 ( 1991-05), p. 213-214
    Type of Medium: Online Resource
    ISSN: 0956-4624 , 1758-1052
    Language: English
    Publisher: SAGE Publications
    Publication Date: 1991
    detail.hit.zdb_id: 2009782-7
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  • 2
    Online Resource
    Online Resource
    SAGE Publications ; 2004
    In:  Ear, Nose & Throat Journal Vol. 83, No. 9 ( 2004-09), p. 640-644
    In: Ear, Nose & Throat Journal, SAGE Publications, Vol. 83, No. 9 ( 2004-09), p. 640-644
    Abstract: Embryologic anomalies of the fourth branchial pouch are rarely seen. They usually present as recurring episodes of deep neck infections and/or abscesses or acute suppurative thyroiditis. Failure to recognize these unusual cases may result in misdiagnosis, inadequate treatment, and subsequent recurrence. We report 3 cases of patients with fourth branchial anomalies. Diagnosis starts with a preoperative evaluation consisting of a barium swallow or sonogram followed by direct hypopharyngoscopy at the time of surgery. Treatment of acutely infected sinuses is best done with appropriate antibiotics and, if necessary, with incision and drainage. Surgical excision should be planned after the inflammation has completely resolved.
    Type of Medium: Online Resource
    ISSN: 0145-5613 , 1942-7522
    Language: English
    Publisher: SAGE Publications
    Publication Date: 2004
    detail.hit.zdb_id: 2067528-8
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  • 3
    Online Resource
    Online Resource
    SAGE Publications ; 2018
    In:  Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering Vol. 232, No. 1 ( 2018-01), p. 180-184
    In: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, SAGE Publications, Vol. 232, No. 1 ( 2018-01), p. 180-184
    Abstract: In this research, the effect of finite width cavities in supersonic flow field is experimentally investigated. The test facility consists of a supersonic nozzle, which provides flow Mach number of 1.9. A circular cross-sectional test section is fastened at the exit of the nozzle. Cavities are incorporated in the test section at a distance of 20 mm from the inlet. Cavities of constant length and width, and varying depth are used for the study. Entrainment of flow in the main stream is observed immediate downstream of the cavity aft edge due to three dimensional effect. As the depth of the cavity is increased, residence time of the fluid as well as the mixing characteristics are enhanced and stagnation pressure loss also increased. Twin cavities are also arranged symmetrically, which further leads to an improvement in mixing with marginal rise in stagnation pressure loss.
    Type of Medium: Online Resource
    ISSN: 0954-4100 , 2041-3025
    Language: English
    Publisher: SAGE Publications
    Publication Date: 2018
    detail.hit.zdb_id: 2032759-6
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  • 4
    Online Resource
    Online Resource
    SAGE Publications ; 2023
    In:  Proceedings of the Institution of Mechanical Engineers, Part E: Journal of Process Mechanical Engineering Vol. 237, No. 2 ( 2023-04), p. 149-161
    In: Proceedings of the Institution of Mechanical Engineers, Part E: Journal of Process Mechanical Engineering, SAGE Publications, Vol. 237, No. 2 ( 2023-04), p. 149-161
    Abstract: Wire arc additive manufacturing (WAAM) has long been considered an efficient method for producing medium- and large-sized components, due to its minimal material consumption, high deposition, superior structural quality and environmental friendliness. The ER 316L wire was employed as the filler metal in the fabrication process with varying heat input by altering welding current (C), wire feed speed (WFS) and travel speed (TS). The first portion of the studies involved producing single-bead welds by adjusting the heat input condition, while the second part involved fabricating three single-bead walls using optimum parameters determined in the first part of the research. The mechanical properties of SS316L samples remained impressively constant when WFS and TS were varied. The macroscopic morphology and microstructure of a thick-walled component were studied using a metallurgical microscope and optical electron microscopy. The mechanical properties of tensile study and micro-hardness analysis were reported. From a microstructural study, it can be observed that the deposited weld beads consist of a columnar structure with primary dendrites. The cooling rate and heat dissipation during the weld deposition process affect the variance of microstructure in different areas. The average micro-hardness value of various linear heat input manufactured components demonstrated stability, with values of 313, 249 and 398 HV, respectively. The hardness results of as-deposited walls provide a higher value in bottom regions due to heat accumulation. Tensile properties were determined parallel and perpendicular to the deposition directions; decreased heat input resulted in superior mechanical properties in terms of tensile characteristics. From the tensile properties, the mean values of various heat input SS 316L ultimate tensile strength, yield strength and elongation were found to be 426 MPa, 304 MPa and 20%, respectively. Fractography showed typical dimple fracture characteristics in all the specimens. It is clear from the current research that parts made by WAAM exceed their 316L casting parts and wrought alloy.
    Type of Medium: Online Resource
    ISSN: 0954-4089 , 2041-3009
    Language: English
    Publisher: SAGE Publications
    Publication Date: 2023
    detail.hit.zdb_id: 2024897-0
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  • 5
    Online Resource
    Online Resource
    SAGE Publications ; 2021
    In:  Proceedings of the Institution of Mechanical Engineers, Part M: Journal of Engineering for the Maritime Environment Vol. 235, No. 2 ( 2021-05), p. 600-606
    In: Proceedings of the Institution of Mechanical Engineers, Part M: Journal of Engineering for the Maritime Environment, SAGE Publications, Vol. 235, No. 2 ( 2021-05), p. 600-606
    Abstract: Flow noise originating in the turbulent boundary layer (TBL) often severely limits the performance of towed sonar array. Therefore, it is necessary to predict this noise for the design of an efficient towed array. This paper presents large eddy simulation methodology to establish the TBL properties and wall pressure fluctuations on a 12 m long towed array with length to diameter ratio of 1200 in the operating tow speed range of 2 to 5 knots in water. The computed flow noise levels are compared with experimental measurements available in the literature successfully. The effectiveness of scaling the flow noise spectra with the diameter and tow speed is discussed, and non-dimensional wall pressure spectra presented with respect to non-dimensional frequency. The overall sound pressure levels are also compared with experimental data that show good accuracy achieved by the proposed numerical methodology.
    Type of Medium: Online Resource
    ISSN: 1475-0902 , 2041-3084
    Language: English
    Publisher: SAGE Publications
    Publication Date: 2021
    detail.hit.zdb_id: 2089895-2
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  • 6
    Online Resource
    Online Resource
    SAGE Publications ; 2022
    In:  International Journal of Engine Research Vol. 23, No. 9 ( 2022-09), p. 1495-1502
    In: International Journal of Engine Research, SAGE Publications, Vol. 23, No. 9 ( 2022-09), p. 1495-1502
    Abstract: The influence of pylon and wall injection in coaxial jets of a Dual Combustion Ramjet engine is numerically investigated in a non-reacting flow field. The supersonic combustor is modeled and analyzed using the commercial CFD software ANSYS 18.0. The three-dimensional compressible Reynolds-averaged Navier-Stokes (RANS) equations coupled with the SST k-ω turbulence model have been used to analyze the coaxial mixing characteristics of the jets. The numerical study is validated with the experimental data of the wall static pressures measured in the combustor’s flow direction. The pylon and wall injectors are located symmetrically at the gas generator’s exit nozzle, and the air is used as the injectant to simulate gaseous fuel. Three injection pressures are used for the study to understand the flow field characteristics in the injector regime. Also, the gas generator downstream direction is investigated. The shock waves generated from the gas generator nozzle enhance the mixing of the coaxial jets with minimum total pressure loss. The shock wave interactions are noticed with reducing intensity within the supersonic combustor for pylon injection, leading to higher total pressure loss than the wall injection. The pylon injection provides the spatial distribution of fuels compared to the wall injection in the coaxial supersonic flow field.
    Type of Medium: Online Resource
    ISSN: 1468-0874 , 2041-3149
    RVK:
    Language: English
    Publisher: SAGE Publications
    Publication Date: 2022
    detail.hit.zdb_id: 2030603-9
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  • 7
    Online Resource
    Online Resource
    SAGE Publications ; 1995
    In:  International Journal of STD & AIDS Vol. 6, No. 1 ( 1995-01), p. 52-53
    In: International Journal of STD & AIDS, SAGE Publications, Vol. 6, No. 1 ( 1995-01), p. 52-53
    Type of Medium: Online Resource
    ISSN: 0956-4624 , 1758-1052
    Language: English
    Publisher: SAGE Publications
    Publication Date: 1995
    detail.hit.zdb_id: 2009782-7
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  • 8
    Online Resource
    Online Resource
    SAGE Publications ; 2023
    In:  International Journal of Engine Research Vol. 24, No. 5 ( 2023-05), p. 2025-2038
    In: International Journal of Engine Research, SAGE Publications, Vol. 24, No. 5 ( 2023-05), p. 2025-2038
    Abstract: This numerical study addresses the performance of double ramps in a strut injection scramjet combustor. Reynolds Averaged Navier Stokes (RANS) equations with the Shear Stress Transport SST k-[Formula: see text] turbulence model are used for numerical analysis. The dual ramps are located symmetrically at the top and bottom wall of a scramjet combustor downstream of the strut injector. The influence of the location of ramps in the scramjet combustor is analyzed based on the key parameters such as shock waves, static pressures, and temperature distribution across the combustor, which are verified with available DLR scramjet experimental data that show similar acceptable values within the range. Simulation is extended for the investigation of other configurations. The performance of the scramjet configurations has been analyzed using the variables such as shock patterns, Mach number contours, wall static pressures, mass fractions of the reactants and products, combustion efficiency, and stagnation pressure loss of combustor. Numerical shadowgraph indicates that numerous shock reflections occur for the dual ramp cases that decelerate the combustor’s flow downstream. In addition, the recirculation regions are created for the dual ramp cases, which help in anchoring the flame. The static pressure distributions show the variation of peaks due to shock patterns and their interactions. The combustion efficiency increases as the ramps are positioned downstream of the strut injector. The mass fractions of reactants and products indicate complete combustion of the hydrogen issued from the combustor in the vicinity of the cavities. The total pressure loss for the DLR strut model is comparatively lower than dual ramp cases due to the multiple shocks from the ramp decelerating the flow downstream of the combustor.
    Type of Medium: Online Resource
    ISSN: 1468-0874 , 2041-3149
    RVK:
    Language: English
    Publisher: SAGE Publications
    Publication Date: 2023
    detail.hit.zdb_id: 2030603-9
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  • 9
    Online Resource
    Online Resource
    SAGE Publications ; 2017
    In:  Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering Vol. 231, No. 14 ( 2017-12), p. 2570-2577
    In: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, SAGE Publications, Vol. 231, No. 14 ( 2017-12), p. 2570-2577
    Abstract: The effective means of air fuel mixing and flame holding can be achieved by incorporating cavity in supersonic combustor. Understanding the complex flow field of cavity flow is essential for the design of supersonic combustor. An attempt is made to understand the characteristics of supersonic flow past axisymmetric cavity, and a series of nonreacting experiments are carried out in a blow-down type supersonic flow facility. The facility consists of a supersonic nozzle, issues a flow Mach number of 1.80 into a circular cross sectional supersonic combustor in which axisymmetric cavity is placed. Cavity of two consecutive aft wall angles is the key parameter for the study. The performance of the cavity is investigated based on the static pressure measurement, momentum flux distribution at the exit plane of the combustor, and the stagnation pressure loss of the flow. Wall static pressure distribution revealed that pressure increases with decrease in the secondary aft wall angle below 45° due to stronger recompression of shear layers. Moreover, decreasing primary aft wall angle provides a uniform mixing profile along with decrease in stagnation pressure loss across the combustor.
    Type of Medium: Online Resource
    ISSN: 0954-4100 , 2041-3025
    Language: English
    Publisher: SAGE Publications
    Publication Date: 2017
    detail.hit.zdb_id: 2032759-6
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  • 10
    Online Resource
    Online Resource
    SAGE Publications ; 2021
    In:  Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science Vol. 235, No. 11 ( 2021-06), p. 1979-1991
    In: Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science, SAGE Publications, Vol. 235, No. 11 ( 2021-06), p. 1979-1991
    Abstract: Motivated by the requirement to lessen the aerodynamic drag and aeroacoustic sound of the bluff bodies, the present paper is devoted to a numerical analysis of the aerodynamics and aeroacoustics related with the flow past wavy circular cylinders. Based on the efficient flow control method, as has been presented by preceding researchers, the existing work embarks upon an investigation on the wavy cylinder at a various wavelength and amplitude conditions. Computations are performed for a circular cylinder of the length-to-diameter ratio ( L/ D) of 25 at a Reynolds number ( Re) of 97300 using large eddy simulation and Ffowcs Williams- Hawking’s acoustic analogy. Firstly, the cylinder without waviness is subjected to a uniform incoming flow is considered for validation against measurements. Secondly, various collection of wave shape parameters, specifically dimensionless wavelength λ/ D (=1 to 2.5), and wave amplitude a/ D (=0.05 to 0.2) have been taken into consideration. It is disclosed that the proper selection of shape parameters could significantly reduce the drag and sound emission levels, compared to the normal cylinder. Finally, a multi-objective particle swarm optimization was performed using the radial basis neural network to simultaneously reduce the aerodynamic drag and sound emission, with λ/ D and a/ D as design variables. We recognized a critical λ/ D and a/ D for the wavy circular cylinder at the considered subcritical Re.
    Type of Medium: Online Resource
    ISSN: 0954-4062 , 2041-2983
    Language: English
    Publisher: SAGE Publications
    Publication Date: 2021
    detail.hit.zdb_id: 2024890-8
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