Abstract: Bituminous paving mixtures containing lubricating agents or additives may be prepared at hot mix temperatures and cooled, paved and compacted at temperatures 10-55 Celsius degrees lower than the hot mix temperatures. The increased temperature range between the hot mix temperatures and the paving and compacting temperatures is facilitated by the improved compacting properties of the paving mixture when it includes the lubricating agents or additives.

Abstract: A composite material and method of making the same are disclosed. An example method for fabricating a composite material forms a core layer between opposing outer layers. The core layer includes a mixture of at least one metallic powder and at least one expanding agent. The example method removes moisture and gasses from the core layer by applying a first vacuum pressure to at least the core layer. The example method compresses the core layer to bond the core layer to the outer layers while a second vacuum pressure is applied to at least one of the outer layers. The resulting composite material has a compacted core layer that is substantially free from moisture and imbedded gasses. Additionally, the outer layers are substantially free from perforations enabling the escape of gas and moisture during foaming of the core layer. The composite material may be reshaped to form semi-finished products which, in turn, may be heated to foam the core material to form finished products.

Abstract: This optical assembly comprises a securing support (40), an optical focusing element (44) and a reflecting mirror (42) which is suitable for reflecting an incident light beam (F1) towards the optical focusing element (44) in order to focus it onto an illumination plane (P). The reflecting mirror (42) is movable relative to the securing support (40). The optical focusing element (44) is movable relative to the securing support (40). The assembly includes elements for connecting the focusing element (44) to the mirror (42) for synchronised displacement of the two of them. The assembly is useful in devices for illuminating operating fields.

Abstract: The invention relates to recirculation flow combustors having a generally curved recirculation chamber and unobstructed flow along the periphery of the boundary layer of the vortex flow in this chamber, and methods of operating such combustors. Such combustors further have a border interface area of low turbulence between the vortex flow and the main flow in the combustor, in which chemical reactions take place which are highly advantageous to the combustion process, and which promote a thermal nozzle effect within the combustor. A combustor of this type may be used for burning lean and super-lean fuel and air mixtures for use in gas turbine engines, jet and rocket engines and thermal plants such as boilers, heat exchanges plants, chemical reactors, and the like. The apparatus and methods of the invention may also be operated under conditions that favor fuel reformation rather than combustion, where such a reaction is desired.

Abstract: The invention relates to recirculation flow combustors having a generally curved recirculation chamber and unobstructed flow along the periphery of the boundary layer of the vortex flow in this chamber, and methods of operating such combustors. Such combustors further have a border interface area of low turbulence between the vortex flow and the main flow in the combustor, in which chemical reactions take place which are highly advantageous to the combustion process, and which promote a thermal nozzle effect within the combustor. A combustor of this type may be used for burning lean and super-lean fuel and air mixtures for use in gas turbine engines, jet and rocket engines and thermal plants such as boilers, heat exchanges plants, chemical reactors, and the like. The apparatus and methods of the invention may also be operated under conditions that favor fuel reformation rather than combustion, where such a reaction is desired.

Abstract: This optical assembly comprises a securing support (40), an optical focusing element (44) and a reflecting mirror (42) which is suitable for reflecting an incident light beam (F1) towards the optical focusing element (44) in order to focus it onto an illumination plane (P). The reflecting mirror (42) is movable relative to the securing support (40). The optical focusing element (44) is movable relative to the securing support (40). The assembly includes elements for connecting the focusing element (44) to the mirror (42) for synchronised displacement of the two of them. The assembly is useful in devices for illuminating operating fields.

Abstract: A table comprising a base (2), a vertical pillar (4), a horizontal platform (5) provided with a seat (9) and mounted on the pillar, and elements for moving the platform relative to the pillar, the elements comprise, a first rail (12), secured to the pillar, a second rail (13) parallel to the lower rail, integral with the seat and mobile in translation therewith relative to the first rail, and a carriage (15) mounted freely sliding on the first fixed rail from one end thereof to the other, the second rail being mounted sliding relative to the carriage and thereon; on each rail (12, 13) a shoe is mounted sliding, said shoe being mechanically integral with the carriage (15).

Abstract: The assembly of two parts, one of which is fixed and the other of which is removable, includes automatic locking and unlocking elements for securing the removable part to the fixed part. The unlocking elements are mounted on the removable part and are integrated inside it. The removable part has a male end adapted to be received in a complementary female end of the fixed part, snap-fastening against a resilient stop latch inside said female end. The male end is secured to a longitudinal spindle extending inside the removable part and terminated by a handle for manual actuation, thus enabling the male end to be turned in order to unlock the assembly of the two parts. The male end is returned automatically to its locking position by a return spring.

Abstract: A gas turbine engine rotor has a body and blades, which are attached to the rotor by a root portion, for receiving a hot fluid flow and a compressed fluid from a compressor. Each blade has a base portion, an external airfoil surface, a blade flow portion of the airfoil, and a passage system communicating with the compressor and with the blade flow portion to create a thermal insulating boundary between the heated fluid and the external airfoil surface. The rotor has a substantially planar platform member, extending substantially transversally to the body of the blade and having an upstream portion protruding in the direction toward the combustion zone. The platform member has at least a pair of openings on either side of the airfoil, the openings being positioned in series along the blade flow portion. One opening of the pair defines an inclined passage in the platform member, and the other opening is separated by a partition from the first opening.

Abstract: The lighting device for lighting a lighted field comprises a light source having first and second lighting modules. The lighting modules are adapted to light lighted domains of the lighted field. The lighted domains form an overlap zone, and each lighting module defines an overlap volume. The device includes detector means adapted to detect a zone of reduced lighting in the overlap zone, and control means adapted to increase the light flux from said second lighting module when the detector means detect a zone of reduced lighting. The invention is applicable to lighting devices used in operating theaters.

Abstract: A gas turbine engine rotor has a body and blades, which are attached to the rotor by a root portion, for receiving a hot fluid flow and a compressed fluid from a compressor. Each blade has a base portion, an external airfoil surface, a blade flow portion of the airfoil, and a passage system communicating with the compressor and with the blade flow portion to create a thermal insulating boundary between the heated fluid and the external airfoil surface. The rotor has a substantially planar platform member, extending substantially transversally to the body of the blade and having an upstream portion protruding in the direction toward the combustion zone. The platform member has at least a pair of openings on either side of the airfoil, the openings being positioned in series along the blade flow portion. One opening of the pair defines an inclined passage in the platform member, and the other opening is separated by a partition from the first opening.

Abstract: A bearing lubrication system for a turbomachine having a lubrication chamber which defines a lubrication space surrounding the bearings has lubricant feeding devices for supplying lubricant to the lubrication space, a lubricant removing device for removing lubricant from the lubrication space, and a buffer case surrounding the lubrication chamber, that is located in the fluid space of the turbomachine, and defines a buffer space communicating with the atmosphere. Shaft contact seals are provided between the buffer case and the fluid space, and shaft seals are provided between the buffer space and the lubrication space.

Abstract: The structure is suspended from the ceiling of a room in a hospital or a clinic and includes a substantially vertical arm adapted to support medical equipment such as a cart above the floor. For this purpose, the structure has a support column for supporting the medical equipment, the column being connected to the vertical arm, and an intermediate support on which said medical equipment is loaded and which is hinged to the column and forms an external cover therefor. The structure also has means for adjusting the position of the intermediate support relative to the column so as to correct departures of the on-board equipment from the horizontal.

Abstract: A gas turbine engine a turbine, a compressor turbine mounted downstream the turbine for rotation in a direction opposite to the rotation direction of the turbine that is mounted downstream the compressor. Exhaust fluid from the compressor turbine is cooled in a heat exchanger with a compressed fluid downstream the compressor and is then cooled with air in separate heat exchanger before being admitted to the compressor. A part of the compressed fluid heated in the heat exchanger is fed to cool the turbine blades, and the rest of the fluid is fed to a heated fluid source for the turbine. To control the gas turbine engine, a part of fluid is boosted by a booster compressor and is discharged from the engine. The booster compressor is driven by an expanding turbine that rotated under the effect of combustion air that is expanded in the expanding turbine and flows through the expanding turbine under the action of reduced pressure in the heated fluid source.

Abstract: A method of operating a gas turbine engine comprising a power turbine mounted downstream a compressor, and a compressor turbine mounted downstream the power turbine for rotation in a direction opposite to the rotation direction of the power turbine. Exhaust fluid from the compressor turbine is cooled in a heat exchanger with a compressed fluid downstream the compressor and is then cooled with air in separate heat exchanger before being admitted to the compressor. A part of the compressed fluid heated in the heat exchanger is fed to cool the turbine blades, and the rest of the fluid is fed to a heated fluid source for the turbine. To control the gas turbine engine, a part of fluid is boosted by a booster compressor and is discharged from the engine. The booster compressor is driven by an expanding turbine that rotated under the effect of combustion air that is expanded in the expanding turbine and flows through the expanding turbine under the action of reduced pressure in the heated fluid source.

Abstract: A gas turbine engine comprising a compressor, a power turbine, a counter-rotating compressor turbine for powering the compressor and a heat exchanger interconnected among them, uses a mixer to mix waste fluid heated by the heat exchanger with combustion air and feed the mixture to a combustor.

Abstract: A gas turbine engine has a device for admitting a rotating fluid flow from an annular space of the casing to the inlet portion of a combustor to form a rotating fluid flow in the inlet portion of the combustor. The rotating fluid flow is formed in the annular space of the casing by supplying a fluid from a compressor to the blades of the turbine rotor disk.

Abstract: The control system comprises a microphone (7) linked to a receiver block (9) and delivering audio signals to a discriminating block (11) comparing the voice profile of the speaker with a particular authorized speaker profile recorded in a personal chip card (20) of the speaker. The authorized audio signals are then processed in a voice recognition device and an electronic control unit so as to selectively activate one of the actuators (3) of the operating table in response to a specific voice command uttered into the microphone and effected by an effector (16) actuated by the speaker.

Abstract: A method of operation of a gas turbine engine having a turbine blade flow portion located between a blade inlet edge and outlet edge, and having a compressor to supply a compressed fluid flow comprising a substantial portion of the compressor fluid output along the outside surface of the blade flow portion, thus providing a thermal insulating boundary layer for the turbine blades over which flows heated fluid from the combustor. Heated fluid formed in the combustor flows without further cooling directly to the turbine blades, thereby reducing losses associated with cooling.