34results about How to "Simple and economic and efficient" patented technology

An air and fuel injection system for the back of a turbomachine's annular combustion chamber, including a central injector and a peripheral annular fuel injector including at least one fuel injection aperture made in an annular wall and emerging in a peripheral annular channel separated from a central channel by the annular wall and having an annular space of admission of air. The system also includes multiple air ejection apertures made in the annular wall downstream from the fuel ejection aperture or apertures in reference to the flow of the air stream, for an additional injection of air into the channel.

Twin-flow turbo-jet engine, comprising a cylindrical casing externally defining an annular flow space for a secondary flow, wherein the cylindrical casing is formed from a lattice framework and from removable cowling panels fixed to the framework, said framework comprising an upstream annular flange for fixing to an intermediate housing, a downstream annular flange for connecting to an exhaust housing and rigid beams parallel or inclined relative to the axis of the turbo-jet engine, connecting the two flanges to one another.

An annular shroud (42), having an internal face intended to cover the back end wall (33) of an annular combustion chamber (12) of a turbomachine (14) fitted with a centrifugal compressor, together with an external face opposite said internal face, and where said shroud includes multiple apertures (54) intended to allow fuel injectors (38, 40) supported by said back end wall (33) to pass through, together with multiple bosses (56) which extend as projections on said external face radially towards the interior respectively from the respective radially internal edges (58) of said apertures (54), such that each of said bosses (56) delimits an extension (60) of the corresponding aperture (54) open radially towards the exterior so as to form an air intake scoop.

A propulsion system for an aircraft, including a dual-flow turbojet and a mounting structure for mounting this turbojet on the wing surface or on the fuselage of an aircraft. The mounting structure includes an aft aerodynamic fairing including a thermal protection floor to protect the mounting structure from the heat of a primary airstream channelled by an exhaust nozzle of the turbojet, as well as an air inlet provided in a longitudinal aerodynamic wall washed by a secondary airstream of the turbojet and delimiting together with an other similar wall a cavity isolated from the secondary airstream for extracting a cooling airstream from the secondary airstream, and air circulation means fed by the air inlet and having at least one outlet aperture emerging in a space between the thermal protection floor and the exhaust nozzle.

A control device, including a transmission shaft adapted to be coupled to an apparatus to be controlled, a driving disk mounted on said transmission shaft to rotate thereon and driven in rotation by a motor unit, a driven disk constrained to rotate with said transmission shaft, and a rotary member carrying at least one indexing means which, due to rotation of said rotary member, can be simultaneously engaged into two respective slots of said two disks for said transmission shaft to be driven in rotation, and can be disengaged from one of said slots for said transmission shaft to be locked against rotation.

An air inlet for nacelle of an aircraft propulsion unit comprising an inner envelope provided with a plurality of orifices for passage of fluid passing through the envelope, and a lip connected to the upstream edge of the inner envelope, and having a portion devoid of orifices for passage of fluid with an axial span of between 20% and 90% of the span of the inner envelope, and a circumferential span a of between 60° and 150° about a longitudinal axis of the air inlet. A process for repairing an air inlet comprising cutting out a recess in an upstream edge of an inner envelope of the air inlet, then arranging and fixing an impermeable panel in the recess so as to create an air inlet of the type described above.

A propulsion unit for an aircraft, comprising one turbine engine and a mounting device for a turbine engine designed to be added laterally on an aircraft structure and comprising a rigid mounting structure. The rigid mounting structure supports at least one arch which is concave towards the longitudinal axis of the propulsion unit and which has a distal end at an angular distance of between 45 and 120 degrees from a vertical plane passing through the axis, on the other side of the structure, and supporting a distal connecting element connecting the turbine engine to the arch.

A combustion chamber for a turbomachine, including two coaxial walls including air inlets, each of which is configured such that its orthogonal projection, in a plane passing through the axis of the injection system closest to the inlet and perpendicular to an axial plane passing through this axis and through the axis of the combustion chamber, has an upstream edge of convex shape when seen from downstream.

A method of manufacture of a wax model of an annular bladed turbomachine stator assembly includes in succession the positioning, in a mold, of a core intended to form the impression of a cavity of a blade of the assembly, the injection of a wax in the mold, and the removal of the wax model fitted with the core from the mold. The core is manufactured in metal and is positioned such that its radially internal end is housed in the portion of the mold defining the blade including the cavity, away from the radially internal end of this portion of the mold.

Machine (10) and method for treating containers (12) of liquids comprising a loading station (15) into which baskets (23) are loaded containing, according to a desired pattern of disposition, the containers (12) to be subjected to washing, a filling station (18) in which the washed containers (12) are filled with new liquid, and a re-closing station (19) in which the containers (12) are closed by the relative lids (11). The re-closing station (19) comprises a closing device (63) provided with gripper members (70) by means of which the lids (11) are picked up and positioned so as to close the containers (12), and loading members (66) that automatically direct the lids (11) toward the closing device (63) in a manner consistent with the desired pattern of disposition of the containers (12) in the baskets (23). The closing device (63) comprises movement members (69) that move the gripper members (70) automatically between a pick-up position in correspondence with the loading members (66) and a position of closure in correspondence with the containers (12). The loading members (66) comprise stop elements (67), able to be selectively activated to automatically dispose the lids (11) in a manner consistent with the predetermined pattern of disposition of the containers (12).

A method and device for igniting a turbomachine combustion chamber including alternately: an intake phase of a fluid into a chamber through an intake port, during which a piston compresses an elastic mechanism under pressure of the fluid such that the elastic mechanism applies onto a piezoelectric element a force sufficient for the piezoelectric element to induce between the electrodes an electric voltage enabling an electric arc to be generated, until the piston reaches a predetermined position for closing a valve for sealing the intake port; and an exhaust phase of the fluid, during which the elastic mechanism pushes back the piston to induce a fluid ejection out of the chamber through an exhaust port, and the valve is open.

A removable storage device intended to be housed in a cavity of a form of packaging for transporting and / or storing radioactive materials, including several substructures movable relative to one another, positioned around a longitudinal axis, and defining multiple adjacent recesses for radioactive materials, together with means for deployment of the substructures including actuation means acting by shape collaboration on the substructures through a bearing surface having, in a section according to any plane passing through longitudinal axis, the shape of a segment inclined relative to this axis, such that displacement of actuation means in a first direction parallel to longitudinal axis causes a displacement of the substructures radially towards the exterior relative to longitudinal axis.

The invention is directed to a culture medium for Haematococcus that contains combustion gases like carbon dioxide, carbon monoxide, and oxides of nitrogen or sulfur and which fixes the carbon, nitrogen or sulfur in these combustion gases into biomass and to methods providing superior biomass yields using this culture medium to culture select species of Haematococcus such as Haematococcus sp. KAU-01.

A device for the cyclonic separation of solid particles contained in a fluid, comprising a primary cyclone chamber, a secondary cyclone chamber, an inlet channel for fluid loaded with solid particles opening into the primary cyclone chamber, an outlet channel for fluid cleaned of the solid particles connected to the secondary cyclone chamber, and a ducting unit connecting the primary cyclone chamber to the secondary cyclone chamber and surrounded by the primary cyclone chamber. The ducting unit comprises a core delimiting the secondary cyclone chamber and having at least one helical groove having a bottom which diverges away from an axis of the secondary cyclone chamber in a direction towards the latter, and a cap covering a part of the core in such a way as to delimit, with the groove, a channel connecting the primary cyclone chamber to the secondary cyclone chamber.