57results about How to "Saving in mass" patented technology

A turbomachine has inner and outer annular shells of metal material containing, in a gas flow direction F, a fuel injector assembly, an annular combustion chamber of composite material, and an annular nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine. Provision is made for the combustion chamber to be held in position between the inner and outer metal annular shells by a plurality of flexible metal tabs having first ends interconnected by a metal ring fixed securely to each of the annular shells by first fixing means, and second ends fixed by second fixing means on a ring of composite material fixed securely to said composite material combustion chamber, the flexibility of said metal fixing tongues allowing expansion to take place freely in a radial direction at high temperatures between said composite material combustion chamber and said metal annular shells.

A turbomachine has inner and outer annular shells of metal material containing, in a gas flow direction F, a fuel injector assembly, an annular combustion chamber of composite material, and an annular nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine. Provision is made for the combustion chamber to be held in position between the inner and outer metal annular shells by a plurality of flexible metal tabs having first ends interconnected by a metal ring fixed securely to each of the annular shells by first fixing means, and second ends fixed by second fixing means on a ring of composite material fixed securely to said composite material combustion chamber, the flexibility of said metal fixing tongues allowing expansion to take place freely in a radial direction at high temperatures between said composite material combustion chamber and said metal annular shells.

A turbomachine has inner and outer annular shells of metal material containing, in a gas flow direction F, a fuel injector assembly, a composite material annular combustion chamber, and an nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine. Provision is made for the combustion chamber to be held in position between the inner and outer metal annular shells by a plurality of flexible metal tabs having first ends interconnected by a flange-forming metal ring fixed securely to each of the annular shells by first fixing means, and second ends fixed by second fixing means firstly to the composite material combustion chamber and secondly to one end of a composite material wall whose other end forms a bearing plane for a sealing element secured to the nozzle and providing sealing for the gas stream between the combustion chamber and the nozzle.

For material reduction, a fan blade made of solid material for a gas-turbine engine is provided in the area of the blade tip with at least one cavity (5) extending from the face of the blade tip. Thus, apart from the aspect of weight saving, the vibration amplitudes and the centrifugal forces can be reduced considerably and the natural vibration behavior improved in a simple manner, ultimately increasing mechanical strength.

A method of enhancing a geologic model of a subsurface region is provided. A bed topography of the subsurface region is obtained. The bed topography is defined by a plurality of cells with an elevation associated with each cell center. The bed topography is represented as a cell-centered piecewise constant representation based on the elevations associated with the cells. The bed topography is reconstructed to produce a spatially continuous surface. Flux and gravitation al force-related source terms are calculated based on the reconstructed bed topography. Fluxes are calculated between at least two of the cells. Fluid flow, deposition of sediments onto the bed, and / or erosion of sediments from the bed are predicted using the fluxes and gravitational force-related source terms. The predictions are inputted into the geologic model to predict characteristics of the subsurface region, and the predicted characteristics are outputted.

A turbomachine has inner and outer annular shells of metal material containing, in a gas flow direction F, a fuel injector assembly, a composite material annular combustion chamber, and an nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine. Provision is made for the combustion chamber to be held in position between the inner and outer metal annular shells by a plurality of flexible metal tabs having first ends interconnected by a flange-forming metal ring fixed securely to each of the annular shells by first fixing means, and second ends fixed by second fixing means firstly to the composite material combustion chamber and secondly to one end of a composite material wall whose other end forms a bearing plane for a sealing element secured to the nozzle and providing sealing for the gas stream between the combustion chamber and the nozzle.

An apparatus and method for balancing the emission current of neutralizers in ion thruster arrays is disclosed that allows a single power processing unit (PPU) to be used to drive the array. A typical embodiment includes at least one voltage-regulated power supply, each voltage-regulated power supply for driving a common element in each of the plurality of ion thrusters, the common element in each of the plurality of ion thrusters being coupled together at a common point, and a current balance circuit for providing a substantially balanced current to each neutralizer cathode of the plurality of ion thrusters by providing a voltage to the neutralizer cathodes relative to the common point.

The present invention relates to wind turbine towers and in particular to such towers having a damper for use when erecting the tower and prior to installing a nacelle on the top of the tower. The invention also relates to a method for damping wind turbine towers. One aspect of the invention involves a wind turbine tower (2) with an upper tower structure (24) and a damper (5) comprising, —a liquidless damper housing (7,8) fixed to the upper structure, —a cylindrical interior surface of the damper housing, and —a damper mass having a horizontal extent which is less than a horizontal extent of the cylindrical interior surface of the damper housing, and —at least one shock absorbing structure, where the damper mass is arranged to, when the tower oscillates, essentially stay in a standstill location, whereby a relative movement between the tower and the damper mass may cause an impact with between the tower mass and the shock absorbing structure dependent on the magnitude of the amplitude of the tower oscillation. A main technical progress is that the damper does not need detailed tuning to the towers natural frequency. As long as the damper mass is sufficient, it may be used for damping a range of tower sizes and heights.

A method and associated system for processing waste gases, liquids and solids, produced by human activity, to separate (i) liquids suitable for processing to produce potable water, (ii) solids and liquids suitable for construction of walls suitable for enclosing a habitat volume and for radiation shielding, and (iii) other fluids and solids that are not suitable for processing. A forward osmosis process and a reverse osmosis process are sequentially combined to reduce fouling and to permit accumulation of different processable substances. The invention may be used for long term life support of human activity.

The invention relates to an aircraft turboprop engine (310) comprising at least a low-pressure body (12) and a high-pressure body (14), possibly also an intermediate-pressure body, at least one of said bodies comprising a compressor, the low-pressure body driving a propeller by means of a first gearbox (16), the turboprop engine also comprising means for supplying air to an air-conditioning circuit of an aircraft cabin, characterised in that said supply means comprise at least one compressor (60) of which the rotor (61) is coupled to the low-pressure body, said load compressor (60) including an air inlet (62) connected to means (72) for bleeding air from the compressor of the turboprop engine when all of the aforementioned bodies comprise only a single compressor, or from the compressor of the low-pressure body or the compressor of the intermediate-pressure body of the turboprop engine when all of the bodies comprise at least two compressors.

An electromechanical connection includes a first conductor disposed in a first non-conductive array and a second conductor disposed in a second non-conductive array capable of mating with the first non-conductive array. The second conductor is capable of mating with the first conductor when the first non-conductive array and the second non-conductive array are mated. A processor associated with the first non-conductive array determines if an electrical connection is formed between the first conductor and the second conductor. The processor can assign a function to the electrical connection.

An apparatus and method for balancing the emission current of neutralizers in ion thruster arrays is disclosed that allows a single power processing unit (PPU) to be used to drive the array. A typical embodiment includes at least one voltage-regulated power supply, each voltage-regulated power supply for driving a common element in each of the plurality of ion thrusters, the common element in each of the plurality of ion thrusters being coupled together at a common point, and a current balance circuit for providing a substantially balanced current to each neutralizer cathode of the plurality of ion thrusters by providing a voltage to the neutralizer cathodes relative to the common point.

A self rotating deployed film solar batteries array is composed of film solar batteries, electrical cables, a center axle and connecting lines: many long strip shaped film solar batteries radiate to form a circle or a polygon-array, when linking two adjacent film solar batteries with connecting lines, each film solar battery links to a center axle with electrical cables; film batteries deployed and maintained in an array shape by self rotating centrifugal force in space; film batteries are coiling outside the surface of a center axle before their deployment. The unite weight of thin film battery is only 1 / 30 of traditional solar cell paddle. The film solar batteries array can be used in various satellite, space station and solar power rocket. It will greatly reduce the launching cost, enhance the power for spacecrafts and double the length of service life.

The present invention relates to wind turbine towers and in particular to such towers having a damper for use when erecting the tower and prior to installing a nacelle on the top of the tower. The invention also relates to a method for damping wind turbine towers. One aspect of the invention involves a wind turbine tower (2) with an upper tower structure (24) and a damper (5) comprising, —a liquidless damper housing (7,8) fixed to the upper structure, —a cylindrical interior surface of the damper housing, and—a damper mass having a horizontal extent which is less than a horizontal extent of the cylindrical interior surface of the damper housing, and—at least one shock absorbing structure, where the damper mass is arranged to, when the tower oscillates, essentially stay in a standstill location, whereby a relative movement between the tower and the damper mass may cause an impact with between the tower mass and the shock absorbing structure dependent on the magnitude of the amplitude of the tower oscillation. A main technical progress is that the damper does not need detailed tuning to the towers natural frequency. As long as the damper mass is sufficient, it may be used for damping a range of tower sizes and heights.

The theft-protected screw part in the form of a nut or a screw has a free end region and a ring-shaped depression formed at the end region for the engagement of a wrench for rotation the screw part. Viewed from radially outside to radially inside, the depression is delimited by an outer edge, a bottom and an inner edge. The outer edge forms outer abutment surfaces and the inner edge forms inner abutment surfaces for the wrench. The screw part is composed of a main part and an insert. The main part has a protrusion, which is located within the inner edge. The insert is designed in a ring shape, has a hole for accommodating the protrusion and forms the inner abutment surfaces.

The present invention relates to a method for reducing the rotational speed, in a gas turbine engine, of a turbine comprising a rotor (6) driving a shaft (8) and able to rotate inside a stator (7) in the event of breakage of said shaft. This method is one which consists in measuring (11) the temperature at a point on a surface of the stator (10A) which surface lies downstream of the rotor (6), in transmitting the measurement signal to a control means (100) that controls the slowing of the rotor, said control means being designed to control the slowing of the rotor when the temperature reaches a threshold.The invention also relates to the device.

The invention relates to an aircraft engine attachment pylon, comprising a box formed by the assembly of a first spar (18), a second spar (20) and two lateral panels (22), the pylon also comprising an aft engine attachment (8) fitted with an aft attachment body (54), and also provided with two lateral fittings (26) associated with the two lateral panels (22) to which they are fixed and from which they project laterally outside the caisson, each fitting (26) forming a plane attachment interface (36) with the attachment body (54) through which bolts pass (56).According to the invention, each interface (36) is in the shape of a straight segment inclined at 45° from the vertical direction (Z) as seen in section on any transverse plane of the pylon passing through it.

An active body (1) includes flares (2, 6, 7) arranged adjacent, above, or behind each other, wherein at least one hydrophobic separating layer (3, 5) is integrated between the flares, or flare disks (2, 6, 7), thereby preventing the flares (2, 6, 7) from attaching or sticking. In one embodiment, the hydrophobic separating layer (3) is applied to at least one side of the flares (2), preferably as a powder preferably consisting of microspheres, or the like. In another embodiment, a separating disk is disposed between the flares (6, 7) as the separating layer (5), which in addition is anti-cohesive and anti-adhesive.

A vehicle having a structural bed configured to serve as a structural load-bearing member is provided. The structural bed extends rearward from a cab structure of the vehicle and includes a core layer. First and second outer layers flank the core layer and span substantially the entirety of the core layer. The first and second outer layers are composed of a material that has a higher strength than the core layer. The thickness of the core layer may be at least approximately 10 times greater than each of the thicknesses of the first and second outer layers, respectively. The composite structural bed may be integrated with mass-efficient structures to produce an efficient load-bearing structure for a vehicle.

Spinning rotor (1) for an open end rotor spinning machine comprising a rotor shaft (2), a rotor cup (3), which has an opening (4), an inner chamber (5), a rotor groove (6), a conically widening slide wall (7) extending from the opening (4) to the rotor groove (6) and a rotor base (9) arranged opposing the opening (4) and designed with a bore (8), through which the rotor shaft (2) extends at least partially. The rotor shaft (2) is connected by means of a connection element (10) to the rotor cup (3) and the rotor shaft (2) and rotor cup (3) comprise a common rotational axis (13). The rotor shaft (2) and the rotor cup (3) have connection means (11, 12), which are at least partially surrounded by the connection element (10) configured as a cast part, so a positive connection of the rotor shaft (2) to the rotor cup (3) can be achieved.

A device for detecting breakage of a gas turbine engine shaft and for reducing the rotational speed of the turbine includes a rotor of a turbine or of a first stage turbine driving the shaft. The rotor has a turbine disk with a rim. A stator that the rotor rotates inside or a nozzle guide vanes assembly of the first turbine stage is provided. A temperature sensor is positioned on the stator or on the nozzle guide vanes assembly, immediately downstream of the rim. The sensor is located to sense temperature on a portion of the stator that contacts the rotor, or on a portion of the nozzle guide vanes assembly that contacts the first stage rotor, in the event of shaft breakage. An engine fuel control member connects to the sensor and can interrupt fuel supply to the engine, when the sensor emits a signal above a predetermined threshold.

A method of manufacturing a tube-plate structure of metal-matrix composite material in which a single mold is used having a first fiber preform of shape comparable to that of the tube, a second fiber preform of shape comparable to that of the plate, and a third fiber preform surrounding the first fiber preform where it is adjacent to the second fiber preform all placed therein. Thereafter, a metal or a metal alloy is injected into the mold along the axis of the tube via the face of the second preform that is remote from the first preform. This provides a monolithic structure that presents a high degree of thermo-mechanical stability.

A rear part of an aircraft including a support structure for supporting engines, extending through the fuselage, through a first opening and a second opening. A connection structure connects the support structure to the fuselage, including a first connection mechanism connecting the support structure to a first casing forming the first opening and a second connection mechanism connecting the support structure to a second casing forming the second opening. The connection structure also includes at least one effort recovery connecting rod, the first end of which is mounted on the support structure and the opposite end is mounted on the fuselage, at a distance from the first and second openings.

An electrical power supply system and method for an aircraft. The system includes an electrical network including primary generators powering the electrical distribution channels, and an homopolar generator making it possible to create an artificial neutral.

The frame according to the invention comprises two uprights and two crossbeams, each of which is provided with a catching member adapted to receive a corresponding end of at least one heddle, while there are also provided damping means, fast with at least one corresponding catching member, which are placed opposite surfaces for direct abutment of this catching member against a corresponding heddle. The or each catching member is formed by at least one beat metal sheet, which ensures fixation of the damping means by cooperation of shapes and / or by adhesion.

The theft-protected screw part in the form of a nut or a screw has a free end region and a ring-shaped depression formed at the end region for the engagement of a wrench for rotation the screw part. Viewed from radially outside to radially inside, the depression is delimited by an outer edge, a bottom and an inner edge. The outer edge forms outer abutment surfaces and the inner edge forms inner abutment surfaces for the wrench. The screw part is composed of a main part and an insert. The main part has a protrusion, which is located within the inner edge. The insert is designed in a ring shape, has a hole for accommodating the protrusion and forms the inner abutment surfaces.