238 results about "Annular duct" patented technology

A method for controlling in-plane uniformity of a substrate processed by plasma-assisted process in a reactor, includes: supplying a principal gas to a reaction space, and discharging radially the principal gas from the reaction space through an annular duct; and supplying an secondary gas to the reaction space from an area in close proximity to an outer periphery of a susceptor, outside an outer circumference of the substrate as viewed from above, so as to flow at least partially in an inward direction passing the outer circumference of the substrate, reversing the direction of the secondary gas to flow toward the annular duct in a vicinity of the outer circumference of the substrate, and discharging radially the secondary gas together with the principal gas from the reaction space through the annular duct.

The invention involving a magnetorheological fluid damping device for automobile suspension system.The magnetic field generator of this damping device consists of permanent magnet and electromagnetic coil.On the top of the damping device,there are guide apparatus and damping regulator,the function of which is that to ensure the damping channel is uniform annular duct and to meet the high-damp requirement in the restoration process and low-damp requirement in the compression process of damper seperately.The current in the electromagnetic coil designs of bi-directional and this controls the magnetic field intersity of the damping channel,decreases the excitation current of the electromagnetic coil,reduces energy consumption and decreases damper fever.On the non-controlling conditions,this damping device has the equivalent characteristics of the traditional shock absorber and can instead the passive shock absorber,after equiping corresponding current controller,this device can regulate the damping characteristics of suspension system,which improves the automobile driving safety and ride comfort.

A gas turbine engine case having a working fluid flow, includes inner and outer case portions defining an annular duct for directing the working fluid flow, and a plurality of struts positioned within the annular duct and extending between the inner and outer case portions. The struts are welded to the inner and outer case portions with a first weld along a peripheral line of the respective struts and with second weld, of fillet type, in selected locations for additionally connecting a portion of each strut to the respective inner and outer case portions.

In certain exemplary embodiments, a system includes an annular duct having an inner annular wall and an outer annular wall. The system also includes a plurality of injector vanes configured to mix air and fuel to produce an air-fuel mixture, and configured to inject the air-fuel mixture into a central chamber between the inner and outer annular walls.

A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow. The assembly further includes a stator assembly including a stator vane that extends into the mainstream hot gas flow path and a turbine rotor assembly downstream of the stator assembly that includes a turbine disk and a turbine blade extending from the turbine disk into the mainstream hot gas flow path. The stator assembly and turbine assembly define a turbine disk cavity, and the turbine disk cavity includes a recirculation cavity configured to recirculate gas ingested from the mainstream hot gas flow path back into the mainstream hot gas flow path.

In an exhaust gas housing (1) of a thermal engine, a radially outer housing casing (9) and a radially inner housing casing (10) arranged on the hub side are connected to one another via at least one thermally insulated carrying rib (3) acted upon by a cooling medium. A carrying rib (3) has at least two passage ducts (7) and (8) for the cooling medium, at least one passage duct (7) possessing a cooling medium supply (6) and at least one passage duct (8) possessing a cooling medium outlet (12), and these passage ducts (7) and (8) being in communicating connection in the radially inner hub-side end region via a deflection duct (11). The cooling medium is led from an external pressure source (5) through the carrying rib (3) to the region of the deflecting duct (11) arranged on the hub-side casing (10) and from there through the carrying rib (3) back again into a collecting duct (15) which issues preferably into an annular duct (26) for cooling the exhaust gas housing flange (24).

One or more heat exchangers mounted in a duct have heat transfer cooling passages therein and a variable geometry flow restrictor is integral with each of the heat exchangers. An annular slide valve axially translatable within the duct is operable to open and close or vary a variable area between the heat exchangers and one of inner and outer casings bounding the duct. The heat exchangers may be being circumferentially distributed around an annular duct and include radial or circumferentially curved heat transfer tubes or vanes.

A static vane ring for gas turbine engines includes a plurality of radial struts extending between and interconnecting outer and inner duct walls which define an annular duct therebetween. A load transfer apparatus is attached to at least one of the outer and inner duct walls to transfer load from vane to ring, and between vanes.

A thrust reverser for a turbofan jet engine having a stationary structure defining an upstream part of a fan cowling and an axially displaceable, annular structure located downstream of the stationary structure, wherein the inner surface of the fan cowling is spaced from an outer surface of an engine cowling to form an annular duct. A plurality of flaps form a portion of the inner surface of the fan cowling during a forward thrust position, and in a reverse thrust position, the flaps pivotably rotate about a stationary pivot so that their first edges are adjacent with the outer surface of the engine cowling to block the annular duct. A plurality of thrust reverser baffle portions are covered by the flaps during the forward thrust position, and during the reverse thrust position, the thrust reverser baffle portions cover a passageway in the fan cowling between the stationary structure and the displaceable structure. The plurality of thrust reverser baffle portions are radially offset and substantially parallel, and comprise a stationary baffle portion and at least one movable baffle portion. In a reverse thrust position, the movable baffle portions are displaced so that the plurality of thrust reverser baffles are longitudinally juxtaposed, redirecting the deflected gas flow.

A gas turbine engine is provided having an annular duct having an inner duct wall and an outer duct wall. At least one strut extends between the inner duct wall and the outer duct wall. The strut has an aerodynamic shape. At least one vane located circumferentially adjacent the strut and axially behind a leading edge of the strut, and an aerodynamic deflector located circumferentially between each strut and each vane. The aerodynamic deflector may positioned axially upstream of a flow separation point which would otherwise be caused by the strut.

The invention relates to a ventilator flap, making up the terminal part of a main air duct providing an upstream air flow (3), said ventilator flap being provided with diffusion means, directing means, and control means for going from one mode to the other which comprises a central duct (5), at least partly coaxial to an annular duct (8), the two ducts (5, 8) having the upstream ends thereof (2) connected to the principal air duct and each having, at the downstream end thereof, one of said diffusion and directing means and a control bush (12), which may be displaced between a first position, in which the above serves to close a connection between the central duct (5) and the annular duct (8) and a second position in which the above serves to open said connection.

A circumferential row of aerofoil members span an annular duct for carrying a flow of compressible fluid. The duct is centered on the axis of a turbomachine. Pressure and suction surfaces of neighboring aerofoil members bound respective sectoral passages which receive the flow of compressible fluid. The row of aerofoil members includes at least one radial endwall to which the tangent to the trailing edge of each aerofoil member at midspan is substantially orthogonal. Each aerofoil member has reverse compound lean. Each aerofoil member further has a leading edge which has a position at the endwall which is upstream of its position at midspan. The endwall at each sectoral passage has a non-axisymmetrical cross-section formed by a region that, in meridional section, is convexly profiled immediately adjacent the pressure surface and a region that, in meridional section, is concavely profiled immediately adjacent the suction surface.

A circumferential row of aerofoil members span an annular duct for carrying a flow of compressible fluid. The duct is centred on the axis of a turbomachine. Pressure and suction surfaces of neighbouring aerofoil members bound respective sectoral passages which receive the flow of compressible fluid. The row comprises at least one radial endwall to which the tangent to the trailing edge of each aerofoil member at midspan is substantially orthogonal. Each aerofoil member has reverse compound lean. Each aerofoil member further has a leading edge which has a position at the endwall which is upstream of its position at midspan.

In an onboard air conditioning system, a light source (25) for conditioned air is provided in association with an air outlet (31), and the color of the light emitted from the light source changes in dependence on the temperature of the conditioned air. The light source may consist of a linear light source at least partly surrounding the air outlet. Thereby, the vehicle occupant can visually recognize the operating condition of the air conditioning system. The air outlet may be at least partly-surrounded by an annular duct (20) defining a central chamber (21) that has a closed bottom and an open top defining the air outlet, the annular air duct being provided with a communication hole (23) communicating an interior of the annular duct with the central chamber, and the air outlet is covered by an air permeable sheet (30). The conditioned air is thus turned into a mild one because the central chamber is typically large in size, and the velocity of the expelled air may be extremely small for a given volume of conditioned air.

A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.

A gas turbine engine is provided having an annular duct having an inner duct wall and an outer duct wall. At least one strut extends between the inner duct wall and the outer duct wall. The strut has an aerodynamic shape. At least one vane located circumferentially adjacent the strut and axially behind a leading edge of the strut, and an aerodynamic deflector located circumferentially between each strut and each vane. The aerodynamic deflector may positioned axially upstream of a flow separation point which would otherwise be caused by the strut.

A thrust reverser is adapted to be fixed within a turbofan engine nacelle that extends substantially about an engine core cowl. The nacelle and engine core cowl together define an axially extending annular duct for receiving an aft flowing fan bypass air stream that is forwardly redirected upon deployment of the thrust reverser. The nacelle includes an axially translating sleeve, circumferentially arranged translating cascade sets, and axially translatable blocker doors adapted to pivot radially inwardly from the translating sleeve to extend at least partially into the fan bypass air stream. A blocker door deployment drag linkage is pivotally coupled to each of the translating sleeve and the blocker doors. When stowed, an axially extending outer wall of the bypass duct is radially interposed between each blocker door and the fan bypass air stream to assure that the blocker doors remain entirely concealed from the fan bypass air stream.

In certain exemplary embodiments, a system includes an annular duct having an inner annular wall and an outer annular wall. The system also includes a plurality of injector vanes configured to mix air and fuel to produce an air-fuel mixture, and configured to inject the air-fuel mixture into a central chamber between the inner and outer annular walls.

A fuel supply system for a gas turbine combustor includes an annular duct that at least partially defines a hot gas path within the combustor. An orifice is at least partially defined by the annular duct and defines a flow path through the annular duct into the hot gas path. A plurality of fuel injectors are arranged circumferentially around the annular duct to provide for fluid communication through the annular duct into the hot gas path. A fuel distribution manifold is disposed adjacent to an outer side of the annular duct. The fuel distribution manifold includes a main body that at least partially defines an inlet for receiving fuel, an outlet that is in fluid communication with the fuel injectors, and a fuel purge passage that provides for fluid communication between the inlet and the orifice.

A spray nozzle designed to be mounted in a push button of a liquid distribution system, including a body equipped with an assembly tube that is defined by a front wall in which a distribution orifice is formed, wherein the inside face of the front wall is equipped with a vortex chamber that communicates with the distribution orifice, at least two radial tubes to supply liquid to the vortex chamber, and an annular duct to supply liquid to the upstream end of the tubes, in which the lateral inside wall of the tube is equipped with at least two axial grooves which respectively extend between an upstream end opening onto the rear edge of the tube and a downstream end opening onto the annular duct, wherein the grooves are positioned angularly so that each downstream end of a groove is equidistant from the two upstream ends of the tube adjacent to it on either side along the length of the annular duct.

A gas turbine engine case having a working fluid flow, includes inner and outer case portions defining an annular duct for directing the working fluid flow, and a plurality of struts positioned within the annular duct and extending between the inner and outer case portions. The struts are welded to the inner and outer case portions with a first weld along a peripheral line of the respective struts and with second weld, of fillet type, in selected locations for additionally connecting a portion of each strut to the respective inner and outer case portions.

An annular duct insulation structure includes a substantially rigid annular insulation-retaining insert having a substantially cylindrical outer surface. A viscoelastic insulation foam layer is disposed around the substantially cylindrical outer surface of the insert so as to result in a composite insulation structure of the foam layer and the insert. The foam layer is formed of at least one of (A) a compressed open-cell foam layer or (B) a compressed closed-cell foam layer in which at least a portion of the closed cells has been opened, wherein the foam layer has been compressed sufficiently to permit the composite insulation structure to be slipped into an annular duct without substantial friction, and wherein the foam layer decompresses so as to substantially fill a void between an inner surface of the duct and an outer surface of the foam layer of the composite insulation structure.

A sanitary warm water system comprises an annular water duct, a pump, a heater, withdrawing ducts connected to the annular duct and a supply duct, a monochloramine generator which synthesises and adds monochloramine to the warm water in the annular duct at a disinfection point, an ammonium ion abatement device which adds chlorine or hypochlorites to the warm water in the annular duct, an ammonium detector which detects the concentration of ammonium ions in the warm water and a control system which activates the monochloramine generator and activates the ammonium ion abatement device and controls the addition of chlorine or hypochlorite as a function of the ammonium concentration signals, independently of the activation of the monochloramine generator.

A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.

The invention is an annular ducted lift fan system for a VTOL type aircraft. In detail, the invention comprises an annular duct, a lift fan set, engines, a central fuselage, a peripheral wing, and means for pneumatic coupling or mechanic coupling of engines and the lift fan set. The lift fan set is mounted in the annular duct and powered by the engines through pneumatic coupling or mechanic coupling. The annular duct is opened with the lift fan set working to provide high lift efficiency in VTOL mode and transition mode and is closed off to reduce drag in cruise mode.

The invention discloses a circular cooler air-feeding system, comprising an circular air pipe and a branch air pipe communicated with the circular air pipe; the branch air pipe is communicated with an circular air channel; the outlet of the circular air channel is communicated with a trolley air inlet pipe which is communicated with a trolley; the circular air channel consists of a circular liquid cell and a door-shaped sealing device; the door-shaped sealing device is connected with the trolley air inlet pipe; the circular liquid cell is covered by a sealing cover plate of the door-shaped sealing device; a door-shaped air-channel inner circular plate and a door-shaped air-channel outer circular plate of the door-shaped sealing device are extended downward to be below the liquid level of the circular liquid cell; the circular liquid cell consists of a circular air-channel liquid-groove inner circular plate, a circular air-channel liquid-groove outer circular plate, a liquid cell inner circular plate and a liquid cell outer circular plate; and the inner circular plate and outer circular plate of the circular air-channel liquid cell are all provided with the double-layer wall structure in the high-temperature zone of the circular cooler. The invention also discloses the circular air channel and the circular liquid cell of the circular cooler. The invention can prevent the liquid in the circular liquid cell from being gasified when the hot off-gas of the circular cooler is recycled so as to guarantee the normal work of the circular cooler.