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.

Flow cytometer nozzle and flow cytometer sample handling methods

Abstract: An improved nozzle system for a flow cytometer and accompanying methods have been invented for a high efficiency orientation and sorting process of a flat sample and dedicates items such as equine or bovine sperm cells. This improved nozzle system comprises a nozzle with a novel interior surface geometry that can both gently accelerate the cells and can include an elliptical-like, single torsional interior surface element within the nozzle, i.e., a single torsional orientation nozzle. The elliptical-like, single torsional interior surface element may have a laminar flow surface and may produce the simplest flow path for applying minimal forces which act in either an accelerative nature or orienting hydrodynamic forces, namely, the single torsional orientation forces, to orient a flat sample such as animal sperm cells into a proper direction for an analyzing and efficiently sorting process in clinical use, for research and for the animal insemination industry.

Ink-jet print head and ink-jet printer

Abstract: The present invention is to provide an on-demand type ink-jet printer which is free from the risk such that the nozzle is stopped and which is also free from the maintenance. An ink-jet print head comprises a liquid chamber (2) into which a carrier liquid (7) is filled, ink-jet driving means (3), (4) disposed within the liquid chamber (2), a nozzle (14) communicated with the liquid chamber (2) and a mixing unit (14a) disposed in the vicinity of the nozzle (14) for mixing an ink (9) into the carrier liquid (7). The ink (9) is mixed into the carrier liquid (7) in the liquid chamber (2) by the mixing unit (14a), pressed by the ink-jet driving means (3), (4) and then ink-jetted from the nozzle (14). Since the carrier liquid (7) is constantly filled into the nozzle (14), the nozzle (14) can be prevented from being choked up.

Gas turbine combustor including a diffusion nozzle assembly with a double cylindrical structure

Abstract: A gas turbine combustor comprises a cylindrical outer casing having one end closed by a header plate. A combustor liner provided with an inner combustion chamber which is divided into a first-stage combustion region on a side of the header plate and a second-stage combustion region formed on a downstream side of the first-stage combustion region. A first-stage fuel supply unit mounted to the header plate for injecting a first-stage fuel to the first-stage combustion region and a second-stage fuel supply unit mounted to the header plate for injecting a second-stage fuel previously mixed in a lean fuel state. The first-stage fuel supply unit includes a first-stage fuel nozzle assembly, which supplies the first-stage fuel, formed by combining a diffusion combustion nozzle and a pre-mixture combustion nozzle. The pre-mixture combustion nozzle has, at an intermediate portion thereof, a pre-mixing portion for preliminarily mixing the first-stage fuel with an air, and the pre-mixing portion having a diameter in a downstream portion thereof smaller than that of an upstream portion thereof so as to form a pre-mixed flow into a contraction flow. The pre-mixing fuel nozzle of the first stage fuel nozzle assembly is disposed so as to surround the diffusion combustion nozzle disposed in a central portion thereof.

The Effect of Hot-Streaks on HP Vane Surface and Endwall Heat Transfer: An Experimental and Numerical Study

Abstract: Pronounced non-uniformities in combustor exit flow temperature (hot-streaks), which arise because of discrete injection of fuel and dilution air jets within the combustor and because of end-wall cooling flows, affect both component life and aerodynamics. Because it is very difficult to quantitatively predict the affects of these temperature non-uniformities on the heat transfer rates, designers are forced to budget for hot-streaks in the cooling system design process. Consequently, components are designed for higher working temperatures than the mass-mean gas temperature, and this imposes a significant overall performance penalty. An inadequate cooling budget can lead to reduced component life. An improved understanding of hot-streak migration physics, or robust correlations based on reliable experimental data, would help designers minimise the overhead on cooling flow that is currently a necessity. A number of recent research projects sponsored by a range of industrial gas turbine and aero-engine manufacturers attest to the growing interest in hot-streak physics. This paper presents measurements of surface and end-wall heat transfer rate for an HP nozzle guide vane (NGV) operating as part of a full HP turbine stage in an annular transonic rotating turbine facility. Measurements were conducted with both uniform stage inlet temperature and with two non-uniform temperature profiles. The temperature profiles were non-dimensionally similar to profiles measured in an engine. A difference of one half of an NGV pitch in the circumferential (clocking) position of the hot-streak with respect to the NGV was used to investigate the affect of clocking on the vane surface and end-wall heat transfer rate. The vane surface pressure distributions, and the results of a flow-visualisation study, which are also given, are used to aid interpretation of the results. The results are compared to two-dimensional predictions conducted using two different boundary layer methods. Experiments were conducted in the Isentropic Light Piston Facility (ILPF) at QinetiQ Farnborough, a short duration engine-size turbine facility. Mach number, Reynolds number and gas-to-wall temperature ratios were correctly modelled. It is believed that the heat transfer measurements presented in this paper are the first of their kind.© 2005 ASME