Nozzle

About: Nozzle is a research topic. Over the lifetime, 158675 publications have been published within this topic receiving 893026 citations. The topic is also known as: spout.

Control method and apparatus for liquid distributor

Abstract: A liquid sprayer has a tank for storing liquid, a boom supporting spraying nozzles, and a pump and liquid control system for supplying liquid under pressure to the spraying nozzle in a manner that maintains substantially uniform liquid dispensing density independent of variations in the ground speed of the sprayer. A ground speed sensor, a liquid pressure sensor, and a liquid flow meter sends signals to a controller to regulate a valve that controls the rate of flow of liquid to the spraying nozzles.

Fuel injection nozzle and method of use

Abstract: Atomized particles within a desired size range (eg, 1 micron to about 5 microns) are produced from two immiscible fluids, the first a fuel source containing the formulation to be atomized, and a second fluid source which is contained in a pressure chamber surrounding at least the area where the first liquid is to be provided The invention provides a method for the formation of small, relatively uniform fuel particles for use in internal combustion engines and a nozzle-type apparatus for providing the particles to a combustion chamber

Chemical Erosion of Carbon-Carbon/Graphite Nozzles in Solid-Propellant Rocket Motors

Abstract: A comprehensive theoretical/numerical framework is established and validated to study the chemical erosion of carbon-carbon/graphite nozzle materials in solid-rocket motors at practical operating conditions. The formulation takes into account detailed thermofluid dynamics for a multicomponent reacting flow, heterogeneous reactions at the nozzle surface, condensed-phase energy transport, and nozzle material properties. Many restrictive assumptions and approximations made in the previous models have been relaxed. Both metallized and nonmetallized AP/HTPB composite propellants are treated. The predicted nozzle surface recession rates compare well with three different sets of experimental data. The erosion rate follows the trend exhibited by the heat-flux distribution and is most severe in the throat region. H 2 O proved to be the most detrimental oxidizing species in dictating nozzle erosion, followed by much lesser contributions from OH and CO 2 , in that order. The erosion rate increases with increasing chamber pressure, mainly due to higher convective heat transfer and enhanced heterogeneous surface reactions. For nonmetallized propellants, the recession rate is dictated by heterogeneous chemical kinetics because the nozzle surface temperature is relatively low. For metallized propellants, the process is diffusion-controlled due to the high surface temperature. The erosion rate decreases with increasing aluminum content, a phenomenon resulting from reduced concentrations of oxidizing species H 2 O, OH, and CO 2 . The transition from the kinetics-controlled to diffusion-controlled mechanism occurs at a surface temperature of around 2800 K.

Theoretical components of the VASIMR plasma propulsion concept

Abstract: The ongoing development of the Variable Specific Impulse Magnetoplasma Rocket (VASIMR) involves basic physics analysis of its three major components: helicon plasma source, ion cyclotron-resonance heating module, and magnetic nozzle. This paper presents an overview of recent theoretical efforts associated with the project. It includes (1) a first-principle model for helicon plasma source, (2) a nonlinear theory for the deposition of rf-power at the ion cyclotron frequency into plasma flow, and (3) a discussion of the plasma detachment mechanism relevant to VASIMR.