Showing papers on "Nozzle published in 1969"

The Interference of Two-Dimensional Parallel Jets : 1st Report, Experiments on Dual Jet

Abstract: An experiment was carried out on the flow around a dual jet which is issued from two parallel slot nozzles set on a common end wall and is mixed turbulently with the ambient air. Distribution of cavity pressure, that of mean and fluctuating velocities, shape of the jets and cavity length were determined. From these measurements, the effect of distance between the nozzles on the flow field was studied and the following results were obtained : (1) Two jets attract each other and the axis of a jet coincides with an arc of a circle. (2) Except in the case of small distance between two nozzles, the radius of the jet axis and the cavity length increase in proportion to the nozzle distance. (3) Except in the region near the nozzle and the junction of two jets, momentum flux of the jet in flow direction is conserved.

Oral hygiene appliance

Abstract: An oral hygiene appliance comprising a housing having a hollow base member which supports a liquid reservoir container and a storage and display compartment for the jet nozzles and jet nozzle handle. A liquid pump assembly of the reciprocating piston type is mounted in the base member such that a spout in the bottom of the reservoir container feeds a liquid to the pump chamber. This liquid is converted to a sequential series of liquid pulses by the pump and then delivered through a coiled tube to a jet nozzle control handle which discharges the liquid pulses from a jet nozzle. The jet nozzle control handle has a normally closed valve element to prevent the discharge of the liquid pulses until opened by pressing down on the jet nozzle''s fluted knob and has an adjustable feedback valve element that controls the portion of each liquid pulse that is fed back through a second coiled tube to the pump.

Aerodynamic design of axisymmetric hypersonic wind-tunnel nozzles

Abstract: A unified approach to nozzle design is presented in which an inviscid contour is first determined and then corrected to account for the growth of a turbulent boundary layer along the contour. The inviscid contour is obtained by the axisymmetric method of characteristi cs from a prescribed distribution of velocity along the nozzle axis. The velocity distribution matches theoretical transonic conditions at the throat, conical-source flow conditions through an intermediate region, and design flow conditions at the nozzle exit. The second derivative of the axial velocity is continuous throughout and is zero at the exit point. The interdependence of some of the nozzle parameters is discussed. A semiempirical method is presented for calculating the boundary-layer correction. Calculated values agree within about 15% with experimental values obtained in 50-in.-diam, water-cooled nozzles over a Mach number range of 6 to 10.

Device for the continuous mixing of beverage components in a predetermined quantity ratio

Abstract: A device for the continuous combination and mixing of a plurality of liquid beverage components in an accurately maintained adjustable quantity ratio, where a jet mixer has a central pressure nozzle as part of an axially adjustable hollow plunger through which the pressurized liquid, water in the case of soft drinks, passes into a receiving nozzle past the infinitely variable annular opening of a suction chamber through which one or more admixed components are drawn into the receiving nozzle. The adjustment of the annular opening for the suction chamber determines the overall mixing ratio to water, while the flow volume of the various admixed components is controlled by separate throttle valves in their supply conduits. Distortions of the mixing ratio during startup and shutdown of the installation are minimized by accurately synchronizing all shutoff valves and by keeping the liquid volumes within the mixer cavities within predetermined ratios.

Electromagnetically operated fuel injection valve

Abstract: An electromagnetically operated fuel injection valve wherein the armature has an annular sealing surface surrounded by an annular chamber and is normally biased against the rear side of a nozzle. The chamber receives fuel by way of one or more channels which extend from the peripheral surface of the armature toward the bottom surface of the channel so that their projections into the plane of the sealing surface are tangential to the chamber. This causes fuel which enters the chamber to circulate therein whereby the magnitude of the axial component of movement of the fuel determines the rate at which the fuel enters the orifice of the nozzle when the electromagnet is energized to retract the armature from the nozzle.

Composite resin filling syringe and technique

Abstract: THIS DISCLOSURE IS DIRECTED TO A DENTAL MATERIAL CARRIER AND AN APPLICATOR GUN THEREFOR. THE DENTAL MATERIAL CARRIER COMPRISES A NOZZLE PRE-LOADED WITH A PREDETERMINED AMOUNT OF A DENTAL FILLING MATERIAL AND HAVING A DISPLACEABLE PISTON TO EFFECTIVELY SEAL THE DENTAL MATERIAL WITHIN THE NOZZLE UNTIL USED. OPERATIVELY ASSOCIATED WITH THE PRE-LOADED NOZZLE IS AN APPLICATOR GUN ADAPTED TO DETACHABLY RECEIVE THE PRE-LOADED NOZZLE AND HAVING A PLUNGER FOR EFFECTING DISPLACEMENT OF THE PISTON TO EXTRUDE THE FILLING MATERIAL FROM THE CARRIER AS DESIRED.

Some numerical results on viscous low-density nozzle flows in the slender-channel approximation

Abstract: Viscous convergent-divergent nozzle flow slender channel approximations, discussing roles of nozzle geometry, Reynolds number and wall temperature, calculating velocity, enthalpy, etc

Continuous Supersonic Plasma Wind Tunnel

Abstract: The normal magnetic field configuration of a Q device has been modified to obtain a “magnetic Laval nozzle.” Continuous supersonic plasma “winds” are obtained with March numbers ∼3. The magnetic nozzle appears well suited for the study of the interaction of supersonic plasma “winds” with either material or magnetic obstacles.

Experimental Study of the Starting Process in a Reflection Nozzle

Abstract: The unsteady events occurring during the time after the shock enters the nozzle of a shock tunnel and until a steady flow is established have been investigated for a two‐dimensional reflection nozzle by multiple shadowgraphs and interferograms. The influences of different parameters (nozzle half‐angle, throat width, and nozzle inlet radius) on the starting process are presented on x‐t diagrams for the incident shock Mach number MS = 3. The density along the nozzle axis is presented at several times during the starting process.

Catch basin and sewer pipe cleaner

Abstract: A method and apparatus for the cleaning of catch basins and sewer pipes including a single vehicle equipped to convey debris from the catch basin or manhole by means of the carrying power of air into a sealed dump body from which air is continuously pulled, to water jet propel a hose with a nozzle on the leading end thereof through a sewer pipe opening into the catch basin or manhole area and to retract the hose and nozzle for backwashing the sewer pipe debris into the catch basin. The vehicle carries a variable flow high pressure tandem piston pump reciprocated by pressurized oil from a vehicle engine driven hydraulic pump to surge water at high pressure from a vehicle tank or other source through the hose and nozzle to create a jumping action or jackhammer driving of the nozzle forcing it through and around obstructions in the sewer pipe and also preventing snagging during the backwashing operation. Liquids sucked from the catch basin are drained from the sealed dump body back to the catch basin and the solid debris is hauled away by the vehicle to be discharged at a dumping area.

Variable turbine nozzles

Abstract: TURBINE NOZZLE STRUCTURES WITH VARIABLE SETTING VANES AND SHROUD STRUCTURES TO SUPPORT THE VANES, HAVING POROUS FACINGS WHICH ARE ADAPTED FOR TRANSPIRTION COOLING BY AIR FLOWING THROUGH THE FACINGS. ARRANGEMENTS FOR MOUNTING THE FACINGS ON THE STRUCTURAL RINGS OF THE SHROUDS AND FOR SUPPORTING THE PARTS WITH FREEDOM FOR RELATIVE EXPANSION. ALSO, ARRANGEMENTS FOR SEALING AGAINST UNDUE LEAKAGE BETWEEN THE PIVOTING VANES AND THE SHROUD FACINGS.

A quasi-global chemical kinetic model for the finite rate combustion of hydrocarbon fuels with application to turbulent burning and mixing in hypersonic engines and nozzles.

Abstract: Chemical kinetic model for hydrocarbon fuels combustion and application to multidimensional finite difference mixing analyses in hypersonic engines and nozzles

Sound suppressing and thrust reversing apparatus

Abstract: Apparatus includes exhaust gas nozzle and at least two deflectors of arcuate cross section generally surrounding nozzle Trailing edges of deflectors are serrated to form spikes In first, retracted position, deflectors are streamlined with nacelle In second position, leading edges of deflectors scoop in ambient air around nozzle and some spikes overlie nozzle exit to turbulize gas stream, while others intercept ambient air, causing mixing and cooling and noise reduction In third, fully extended position deflectors join to produce reverse thrust bucket, and spikes are offset laterally to mesh and permit tight closing Nozzle may be daisy type to also produce noise suppression

Pressure wave atomizing apparatus

Abstract: The liquid preferably is a body of liquid in a container. A liquid is forced through a converging-diverging nozzle towards a nearby resonator cavity, and the gas is introduced into the flowing liquid before it reaches the cavity. Preferably, the nozzle and resonator cavity both are immersed in the body of liquid. Intimate contact between the gas and liquid results from the tiny gas bubbles which are produced in the liquid body by this device and method.

Method for the uniform extrusion coating of welding flux compositions

Abstract: A method and apparatus are provided for the uniform extrusion coating of flux mixtures on welding rod or wire, in which a sonic or ultrasonic wave vibration at a frequency from about 5,000 to about 400,000 c.p.s. is applied to the flux mixture to maintain its uniformity, and thereby prevent the obstruction to the smooth extrusion coating of the welding flux mixture as the flux mixture is fed under pressure to the extrusion nozzle.

Gas turbine engine constant speed thrust modulation

Abstract: A device is shown for modulating the thrust output of a gas turbine engine without the necessity of varying the speed of said engine. The device includes means for bypassing a portion of the compressor discharge air to a manifold surrounding the engine tail pipe, and, as required, to the turbine cooling flowpath for the purpose of transiently augmenting turbine cooling flow. The manifold is provided with a plurality of swirl inducing nozzles having inlets in fluidic flow cooperation with the manifold and outlets in fluidic flow cooperation with the tail pipe such that bypass flow is provided to the tail pipe in such a manner as to induce swirl within the main gas stream thereby significantly increasing tail pipe pressure losses and thus reducing thrust output of the engine. Engine speed may be maintained during operation of this device and delay time between increased thrust demand and actual thrust output are thereby lessened.

The Generation of Monodisperse Aerosols by Means of a Disintegrated Jet of Liquid

Abstract: A thin jet of liquid issuing from a nozzle at a high velocity disintegrates spontaneously into droplets under the action of surface tension. A periodic disturbance of the jet can be used to control the disintegration so as to make all droplets of the same size. A system for generating monodisperse sprays according to the principle outlined above has been designed and built. The jet is modulated by axial vibration of the nozzle, which is mounted at the center of a membrane. The membrane is vibrated by means of electrostrictive elements. Droplets in the diameter range 40–15 μ have been produced at a vibration frequency of 20–300 kHz. The stream of droplets has been analyzed in several ways. A jet of air perpendicular to the droplet stream has proved to be of special value. Several air jets, pulsed in suitable phase relations, are utilized to disperse the stream of droplets and to prevent the droplets from coalescing during the drying phase of the aerosol generation.

Self-purging nozzle and valve apparatus

Abstract: A nozzle and valve apparatus for aerosol dispensers and the like having means for preventing clogging or contamination of dispensed materials or residues thereof trapped between a hermetic seal and the exit orifice. Means are coupled to the actuator for providing a mechanical purging of the exit orifice after each utilization thereof. The mechanical purging and sealing means is retracted from the nozzle orifice upon actuation of the nozzle and valve apparatus so as not to interfere with the operation thereof.

Cooling of turbine rotors in gas turbine engines

Abstract: THE DISCLOSURE SHOWS A GAS TURBINE ENGINE HAVING A COMPRESSOR, COMBUSTOR, AND TURBINE SEQUENTIALLY ARRANGED. A ROTATING, AIR ENTRY CHAMBER IS FORMED AT THE BASE OF THE TANGS OF TURBINE BUCKETS, WHICH PROJECT FROM THE TURBINE ROTOR INTO THE HOT GAS STREAM FROM TEH COMBUSTOR. A RELATIVELY STATIONARY, ANNULAR NOZZLE FORMS THE ENTRANCE TO THIS ROTATING CHAMBER. AIR IS DUCTED FROM THE DISCHARGE OF THE COMPRESSOR TO THIS NOZZLE. THE NOZZLE IS PROVIDED WITH VANES WHICH ACCELERATE THE COMPRESSOR DISCHARGE AIR INTO THE ROTATING CHAMBER WHICH IS AT A LOWER PRESSURE. THE NOZZLE IMPARTS, TO THE COOLING AIR, A VELOCITY VECTOR HAVING A COMPONENT RELATIVE TO THE ROTATING CHAMBER (AND TURBINE ROTOR), WHICH IS GENERALLY AXIAL. THE AIR IS REDUCED IN STATIC TEMPERATURE, AS IT IS ACCELERATED THROUGH THE NOZZLE, AND ENERGY LOSSES ARE MINIMIZED DUE TO THE VELOCITY VECTOR OF THE COOLING AIR BEING ESSENTIALLY AXIAL RELATIVE TO OPENINGS IN THE TURBINE ROTOR, WHICH THE AIR ENTERS TO FLOW THROUGH PASSAGEWAYS PROVIDING AN INTERNAL COOLING MECHANISM FOR THE TURBINE BUCKETS.

Discharge coefficients for thick plate orifices with approach flow perpendicular and inclined to the orifice axis

Abstract: Discharge nozzle coefficients for thick plate orifices with approach flow perpendicular and inclined to orifice axis

Method and apparatus for suppressing the noise of a fan-jet engine

Abstract: A tubular housing is disposed in spaced relation around the casing of a fan-jet engine and is coterminous with the aft end thereof, fan air of said engine being discharged to the atmosphere through the annular gap between the housing and the casing. A lobed thrust nozzle is mounted on the aft end of the engine casing and extends rearwardly therefrom in coaxial relation therewith. Exhaust gas is discharged through the lobes of the nozzle and thus enters the atmosphere in separate streams spaced apart circumferentially of the aft end of said nozzle, and a portion of the fan air flows between the lobes of the nozzle and into the spaces between the streams of exhaust gas.

Liquid fuel combustion device

Abstract: Through a combination of A THE SUPPLY OF OXYGEN SUBSTANTIALLY IN THE FORM OF PURE OXYGEN IN AN AMOUNT FAR LESS THAN THAT THEORETICALLY REQUIRED FOR COMBUSTION OF LIQUID FUEL TO BE BURNED IN SUCH A MANNER AS TO ATTAIN A VERY RAPID COMBUSTION TEMPERATURE RISE, B WITH THE STRONG ACTIVATION OF THE LIQUID FUEL BY MIXING AND ATOMIZATION OF A PART OF THE FUEL LIQUID SUFFICIENTLY WITH THE OXYGEN, LIMITED IN QUANTITY, CLOSELY ADJACENT TO A LIQUID FUEL NOZZLE THEREBY TO FORM A HIGH-TEMPERATURE CENTER FLAME VERY CLOSE TO THE NOZZLE

Sound suppression system

Abstract: System includes a nozzle connected to turbine exhaust outlet to confine and direct gas stream. Nozzle is corrugated to form peripherally spaced radially extending lobes to divide gas into small jet streams. Conduit surrounds exhaust outlet and discharges to exterior of nozzle, and fan air flows through passages between lobes to meet gas streams at exit margin of nozzle. Shroud or ejector sleeve defines and surrounds a mixing zone aft of the exit margin. Leading edge of shroud is spaced aft of fan air conduit to provide annular flow path for entry of ambient air to surround and mix with fan air and gas. Shroud is retractable to surround nozzle in spaced relation and prevent dispersion of fan air before mixing in normal cruising flight.

Hypersonic turbulent boundary-layer measurements using an electron beam.

Abstract: Density and density fluctuations in hypersonic turbulent boundary layer on shock tunnel nozzle wall measured using electron beam probe

Safety air gun

Abstract: A safety air gun having a nozzle unit which protects the nozzle tip against direct contact, has pressure-reducing vents in its end surface to produce a safe pressure thereat and provides a protective air curtain or screen extending therefrom to protect against flyback.

Heated windshield washer system

Abstract: In a preferred form, this disclosure relates to a windshield washer system for washing the windshield of an automotive vehicle. The windshield washer system includes a nozzle means for directing washer fluid against the windshield, a reservoir for containing the washer fluid, a pump assembly having an inlet and an outlet, first and second conduit means for communicating the reservoir with the inlet of the pump assembly and the outlet of the pump with the nozzle means, and a heater means in the form of a conduit means through which heated engine coolant fluid is circulated. The latter conduit means is in heat exchange relationship with the reservoir, the first and second conduit means and the nozzle means whereby the washer fluid is heated while in the reservoir and throughout its path of movement from the reservoir to the nozzle means.

Vapor seal for dispensing nozzles

Abstract: Vapors displaced from a liquid fuel tank by the liquid fuel being dispensed thereinto through a nozzle are collected by means of a flexible bellows which surrounds the nozzle and one end of which is sealed to the fillpipe of the fuel tank.

Apparatus for manufacturing wire and the like

Abstract: MANUFACTURING WIRE AND THE LIKE BY MAINTAINING STATIC EQUILIBRIUM IN MOLTEN MATERIAL AT THE OUTLET OF A NOZZLE TO FORM A CONVEX MENISCUS FROM WHICH THE MATERIAL IS CONTINUOUSLY DRAWN OFF AND SOLIDIFIED BY MEANS OF A MOVING SURFACE AT CONSTANT TEMPERATURE.