189 results about "Supersonic nozzle" patented technology

A method of operation of a plasma torch and the plasma apparatus to produce a hot gas jet stream directed towards a workpiece to be coated by first injecting a cold high pressure carrier gas containing a powder material into a cold main high pressure gas flow and then directing this combined high pressure gas flow coaxially around a plasma exiting from an operating plasma generator and converging directly into the hot plasma effluent, thereby mixing with the hot plasma effluent to form a gas stream with a net temperature based on the enthalpy of the plasma stream and the temperature and volume of the cold high pressure converging gas, establishing a net temperature of the gas stream at a temperature such that the powdered material will not melt or soften, and projecting the powder particles at high velocity onto a workpiece surface. The improvement resides in mixing a cold high pressure carrier gas with powder material entrained in it, with a cold high pressure gas flow of gas prior to mixing this combined gas flow with the plasma effluent which is utilized to heat the combined gas flow to an elevated temperature limited to not exceeding the softening point or melting point of the powder material. The resulting hot high pressure gas flow is directed through a supersonic nozzle to accelerate this heated gas flow to supersonic velocities, thereby providing sufficient velocity to the particles striking the workpiece to achieve a kinetic energy transformation into elastic deformation of the particles as they impact the onto the workpiece surface and forming a dense, tightly adhering cohesive coating. Preferably the powder material is of metals, alloys, polymers and mixtures thereof or with semiconductors or ceramics and the powder material is preferably of a particle size range exceeding 50 microns. The system also includes a rotating member for coating concave surfaces and internal bores or other such devices which can be better coated using rotation.

An improved method and apparatus for EAF steelmaking wherein the method provides additional thermal energy to the steel making process, carbon injection for the formation of foamy slag, and oxygen injection for the decarburization of the melt, the formation of foamy slag and post combustion burning of carbon monoxide. The apparatus comprises a unique burner configuration which has a central conduit for alternatively supplying fluid hydrocarbon fuel or particulate carbon with a carrier gas which are discharged through a exit opening. The fuel or carbon is mixed with a high speed, preferably supersonic, stream of oxidizing gas. The high speed stream of oxidizing gas is provided by an annular supersonic nozzle which causes the oxidizing gas to surround the fuel or the particulates with an annular flow. The annular nozzle design can be adjusted to direct the flows of particulates and oxidizing gases in the areas and shapes desired for efficient management of the steelmaking process. Optionally, the burner can have another conduit for the secondary supply of a pressurized flow of hydrocarbon fluid fuel to a series of apertures which surround the annular flow. Further, optionally, the burner can have another conduit for the supply of a pressurized flow of a secondary oxidizing gas to a series of apertures which surround the annular flow.

The invention provides a mass spectrometric method for analyzing a sample in a solution, including the steps of directing a flow of a solution containing sample compounds to be analyzed towards a supersonic nozzle having an input end and an output end; vaporizing the solution and sample prior to its expansion from the output end of said supersonic nozzle; allowing expansion of the vaporized sample and solution from said supersonic nozzle into a vacuum system, forming a supersonic molecular beam with vibrationally cold sample molecules; ionizing the vaporized sample compounds with electrons while contained as vibrationally cold molecules in said supersonic molecular beam; mass analyzing the ions formed from said sample compounds; detecting said ions formed from said sample compounds after mass analysis, and processing the data obtained from the resulting mass spectral information, for identifying and/or quantifying the chemical content of said sample. The invention also provides apparatus for analyzing a sample in a solution.

The invention relates to the field of surface coating preparation and particularly relates to a cold spray device and method for preparing a metal composite gradient quasicrystal coating. A quasicrystal powder feeder and a metal or alloy powder feeder of the device are respectively connected to a gas-solid mixing chamber through a pipeline to form a dual-channel powder feeding structure, a quasicrystal heater and a metal or alloy powder heater are respectively arranged on the pipelines, a gas heater is connected with the gas-solid mixing chamber through a pipeline and a supersonic flow nozzle is arranged at an outlet of the gas-solid mixing chamber. One path of the gas source compressed gas enters into the quasicrystal powder feeder, one path enters into the metal powder feeder, and one path enters into the heater, the gas and the powders enter into the supersonic flow nozzle via the gas-solid mixing chamber to form gas-solid dual-phase flow, solid particles in the gas-solid dual-phase flow are injected onto the surface of a workpiece and generate severe plastic deformation and finally deposit on the surface of the workpiece. The method provided by the invention can solve the problems of fragility and phase change and the like of coatings, and can be used for preparing two-component or multi-component alloy quasicrystal gradient coatings of various series.

The invention relates to a manufacturing method of a composite coating layer on the surface of a high-resistant crystallizer or a crystallizing roller. The manufacturing method is as follows: adopting a preparation technology of a cold-gas dynamic spraying composite coating layer; utilizing high-pressure gas to carry metal or mixed particles of alloy matrix particles and hard reinforcement particles; increasing the speed of the metal or the mixed particles by a supersonic nozzle to be extremely high so as to collide with the surface of a copper alloy matrix of the crystallizer or the crystallizing roller; and generating strong plastic deformation by the metal or the alloy particles so as to lead the metal or the alloy particles to be bonded on the surface of the crystallizer or the crystallizing roller to form a composite coating layer. By utilizing the manufacturing method, good heat conductivity of the metal or the alloy matrix and excellent wear-resistant performance of a reinforcement are utilized comprehensively, the surface coating layer of the crystallizer or the crystallizing roller with good comprehensive performance is obtained, and the online service life of the crystallizer or the crystallizing roller is prolonged.

A modified high efficiency kinetic spray nozzle is disclosed. The modified nozzle has a rapid expansion rate in the diverging region relative to prior art nozzles, which enables one to achieve much higher particle velocities without an increase in the main gas temperature. Preferably, the expansion rate of the supersonic nozzle in a portion of the diverging region is at least 1 mm² per millimeter, more preferably 2 mm² per millimeter, more preferably 5 mm² per mm, with a most preferable expansion rate being 10 mm² per millimeter.

The invention adds details and alternate design supplementing the concept established with my patent application Ser. No. 12/013,431, Aircraft Propulsion System (APS). The APS ultimate fuel economy objectives requires long term design development, and this invention compromises some fuel economy for the expediency of short term implementation of a heat regeneration for turbofans via the re-arrangement of existing components and a few unique items readily designed. While this Velarus Propulsion (VPx) attains only 42% fuel economy, it retains the original APS fundamental architecture implementing heat regeneration for a turbofan engine, as well as the additional benefits of noise and emission abatement. This invention consists of the three APS technologies as follows:

• • a) A novel arrangement of the power generation core features the turbine exhaust entering directly into the thrust chamber, thus providing heat regeneration with an appropriate configuration of the thrust chamber.
  • b) The design of a modified combustor introduces the concept of a supersonic nozzle driving the turbines which allows for greater combustor's chamber temperature while injecting the gases at temperatures acceptable to current turbine blade metallurgy. This feature increases the engine thermal efficiency.
  • c) The hub design allows for two options, a simpler fixed fanblade design or an advanced controllable pitch fan blade, increasing the mission and performance flexibility of a given turbofan size.

In addition, this invention adds functionality to the aft cone, such as debris purge, accessories installation, and thrust reversers free from hot gases.

Disclosed is a coated member on which a porous metal coating layer is formed and a method of producing the same. The method comprises providing the mother material, feeding powder having a metal composition, which includes at least two different metals selected from the group consisting of Al, Mg, Zn, and Sn and which is expressed by xA-(1−x)B (0<x<1, where x is a weight ratio of A and B), onto the mother material, supplying high pressure gas to the powder, applying the metal powder using on the mother material by spraying the metal powder using the high pressure gas through an supersonic nozzle, and heat-treating the coated mother material to form the porous coating layer. In the method, it is possible to freely control the pore size and porosity of the coated member. Accordingly, it is available to various members for thermal and mechanical applications.

This invention opens one kind of gas dynamic powder spraying device which is composed with compression gas source,powder feed unit and spray mechanism.The spray mechanism includes gas heater and supersonic nozzle that is rigid linkage structure of coaxial setting.Gas heater includes metal shell,heat element and electrothermal insulator.One end of metal shell is fixed coaxial with the supersonic nozzle,the other end of metal shell is equipped with carrier gas joint and feed powder joint.The electrothermal insulator which is installed in the metal shell is composed with two coaxial emboitement internal and external tube,the center of the internal tube has a channel which two ends respectively connect powder feed unit and supersonic nozzle.In the exine of the internal tube,there are agroove gas direct channels which connect to the compress gas source,the heat element lies in the agroove gas direct channals.This invention which can be used to prepared monolayer and multi-layer coating widens industry application,reduces equipment weight,simplifies design structure and equipment maintanance and improves the spraying efficiency,being suitable for mechanical energy and metallurgy etc.

A converging diverging supersonic nozzle for a kinetic spray system is disclosed. In one embodiment, the supersonic nozzle has a first end opposite an exit end and a diverging region adjacent the exit end. A removable throat insert has an entrance cone and a throat and is received in the first end with the throat positioned adjacent the diverging region. In another embodiment, the removable throat insert has an entrance cone, a diverging region and a throat positioned between the entrance cone and the diverging region. The disclosed replaceable throat inserts address the problem of excessive wear in the throat relative to the rest of the supersonic nozzle which has plagued other kinetic spray systems. With the disclosed inserts a worn throat can rapidly and economically be replaced while saving the rest of the supersonic nozzle.

The plasma spraying gun mainly comprises gun body, insulator, gas spiral-flow ring, flow divider, anode nozzle, front pressure cap, cathode body, inner pressure cap, insulating cover and outer pressure cap, in which the anode nozzle is connected with gun body by means of inner pressure cap, the flow divider is fixed in the interior of gun body by means of tight fit, the gas sprial-flow ring and insulator are connected with gun body by means of inner pressure cap,and the cathode body is fixed in the interior of gun body by means of insualting cover, outer pressure cap and in sulator. Said invention adopts integrated structure design, its structure is compact and beautiful.

The invention provides a high-temperature combustion-gas flow supersonic wind tunnel test system and relates to the technical field of aircraft thermal protection ground test. The system comprises a heater, a supersonic nozzle, a test cabin, a diffuser and an exhaust system. One end of the heater is connected with an external energy system; one end of the supersonic nozzle is fixedly connected with the heater, and the other end of the supersonic nozzle is fixedly connected with the test cabin; the diffuser is fixedly arranged at one end of the test cabin; and one end of the exhaust system is fixedly connected with the diffuser, and the other end of the exhaust system is connected with the outside world directly. The high-temperature combustion-gas flow supersonic wind tunnel test system is a system having hundred-megawatt power and meter-scale jet size, and the power thereof reaches more than 200 megawatts, and the jet size reaches 1.5 m; and aircraft thermal protection system global and regional 1:1 large-size model heat check can be realized.

The invention relates to a yaw control device for an aircraft fitted with a supersonic nozzle having a rectangular or flat section comprising a supersonic throat extended by a diverging portion in which supersonic flow occurs. In order to enable the aircraft to be controlled in yaw in the absence of a vertical fin, the device of the invention makes use of jet control surfaces in the form of airfoils disposed in the diverging portion of the nozzle. The control surfaces are movable about respective pivot axes in order to generate a lateral force when in a deflected position, so as to enable the aircraft to turn about its yaw axis.