Abstract: A controlled extrication module for the injured composed of a body with several means of immobilization of an injured person and supplied with devices for handling, maneuvering and transporting. The module is composed of a rigid plaque that provides a rear part with a medium zone coinciding with a person's back, a lower zone coinciding with a sacrococcygeal zone, and an upper zone coinciding with neck and head. The upper zone has a rounded edge which coincides with a cranial base and a border enabling attachment to an upper end of a seat. The upper zone also has two cavities for placing cervical collar straps which delimit a central help and semi-rigid fins connected to additional straps which attach at their ends. Both sides of the medium zone have upper and lower projections and an intermediate space supplying a side border. The border is placed on a side edge of the seat. The module also has a harness made up of upper and lower strips.

Abstract: A component for use in a gas turbine engine is provided. The component has an airfoil portion with a plurality of internal cooling passages and a non-linear trailing edge. The component further has a non-linear array of teardrop shaped assemblies which form a plurality of injection slots for injecting a coolant fluid into a fluid passing over the airfoil portion. The teardrop shaped assemblies are designed to maximize thermal performance of the component by reducing a relative diffusion angle between the injected coolant flow and the streamline direction of the fluid passing over the airfoil portion.

Abstract: A system for cooling a combustion chamber of an engine, such as a rocket engine, is provided. The system has a plurality of coolant tubes or passages surrounding the combustion chamber, a torroidal coolant-collection manifold for receiving coolant from the coolant tubes or passages and for discharging the coolant through a discharge port, and a plurality of turning vanes within the torroidal manifold for reducing pressure loss and improving pressure uniformity associated with the torroidal coolant-collection manifold.

Abstract: A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a plurality of microcircuits having at least one passageway on an exposed internal wall of the first half of the airfoil portion. The method further comprises forming a second half of the airfoil portion of said turbine engine component, and forming at least one additional cooling microcircuit having at least one passageway on an exposed internal wall of the second half of the airfoil portion. Thereafter, the first half is placed in an abutting relationship with the second half after the cooling microcircuits have been formed and inspected. The first half and the second half are joined together to form the airfoil portion.

Abstract: A rocket engine chamber has a back structure and a heat exchanger structure located radially inwardly of the back structure. The heat exchanger structure has a plurality of integrally formed cooling passageways with adjacent ones of the passageways having a common sidewall structure. Each passageway has a top section which forms the wall that contacts the hot gases. The top section is formed by a wall structure having an inner and outer surface formed by an arc of a circle and a substantially constant wall thickness.

Abstract: The present invention relates to a metallic coating to be deposited on gas turbine engine components. The metallic coating comprises up to 18 wt % cobalt, 3.0 to 18 wt % chromium, 5.0 to 15 wt % aluminum, 0.1 to 1.0 wt % yttrium, up to 0.6 wt % hafnium, up to 0.3 wt % silicon, 3.0 to 10 wt % tantalum, up to 9.0 wt % tungsten, 1.0 to 6.0 wt % rhenium, up to 10 wt % molybdenum, and the balance nickel.

Abstract: An improved engine construction, such as a rocket engine construction is provided. The engine construction comprises a combustion chamber, a smooth wall nozzle, and a transition zone between the chamber and the smooth wall nozzle. The transition zone has a coolant system which includes a manifold formed from a non-copper material through which a coolant flows. In a high heat transfer embodiment, the transition zone includes an additional manifold formed from a copper based material.

Abstract: A packaged block of envelopes comprises a series of envelopes, retaining plates disposed on either side of said series of envelopes, and a peripheral holding binder. In the vicinities of each of two of its corners, each of the envelopes has at least one thickness compensation wedge having a thickness substantially equal to the thickness of its closure flap, so that the envelopes are of total thickness that is identical at all four of their corners.

Abstract: There is provided a method for producing a metal/ceramic bonding circuit board, which can form a fine pattern even if a circuit forming metal plate is thick and which can shorten the time required to carry out etching, when a molten metal is caused to contact to a ceramic substrate to be cooled and solidified to bond the circuit forming metal plate to the ceramic substrate to etch the circuit forming metal plate to form a metal circuit plate having a desired circuit pattern. A molten metal is caused to contact both sides of a ceramic substrate 10 to be cooled and solidified. Thus, a circuit forming metal plate 12 having a shape similar to a desired circuit pattern is bonded to one side of the ceramic substrate 10, and a metal base plate 14 is bonded to the other side thereof.

Abstract: A bristle arrangement for use in a brush seal, comprising: a plurality of bristles arranged in a length; and a joint along the length securing the bristles together. The fixture for making the bristle arrangement, comprises: a base having a surface with an arrangement of guides thereon, the guides adapted to orient the tufts on the surface; and a cover having a surface for receiving the tufts. The cover removably mounts to the base to sandwich the tufts between the cover and the base. Making a brush seal with multiple stages comprises the steps of: providing plates and bristle arrangements; creating a stack of plates and bristle arrangements; and joining the stack.

Abstract: A method comprising a search phase to find shared information in a peer-to-peer network by terminals each being configured as client and as server to share information with other terminals in the peer-to-peer network, the search phase being triggered on a server in a peer-to-peer network, connected to a data transmission network, after a request sent by a user terminal connected to the server but not to the peer-to-peer network, this phase comprising a step in which a list of shared information is created and transmitted to the terminal in response to the request, a step in which shared information is selected from this list on the terminal, and a phase in which the selected information is downloaded to the terminal not connected to the peer-to-peer network, after a download request has been sent from the terminal.

Abstract: In accordance with a first aspect of the present invention, an aircraft having a scramjet engine is provided. The scramjet engine includes a flowpath which varies in three dimensions. In accordance with a second aspect of the present invention, a method for launching an aircraft having a scramjet engine with a nozzle section and a solid rocket booster positioned within the nozzle section is provided. The method includes the steps of igniting the solid rocket booster to accelerate the aircraft to a speed at which the scramjet engine can operate, clearing the nozzle section by ejecting the solid rocket booster from the nozzle section upon exhaustion of the solid rocket booster; and injecting fuel into a flow of air passing through the scramjet engine and igniting the fuel and the air to provide thrust to the aircraft.

Abstract: The invention detects gas turbine bleed valve position discordances. The invention derives a modified exhaust gas temperature derivative as the predictive criteria in conjunction with a control logic to determine bleed valve position discordances that may indicate a mechanical failure in a valve, or in the control means for a valve.

Abstract: A spallation resistant metallic article comprising a metallic substrate, at least one ceramic thermal barrier coating comprising a zirconia base and at least one other element selected from the group consisting of La, Ce, Pr, Nd, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, Sc, In, Y, Mo and C, rare earth oxides, scandium, and indium, and a ceramic bond coat located on at least a portion of the substrate and between the metallic substrate and the at least one ceramic thermal barrier coating wherein the ceramic bond coat is composed of yttria stabilized zirconia (YSZ).

Abstract: A method for forming a component for use in a gas turbine engine, such as a turbine vane construction is provided. The method broadly comprises the steps of: forming a first aerodynamic structure having a first platform with a leading edge and a trailing edge, and an edge with an airfoil suction side structure; forming a second aerodynamic structure having a second platform with a leading edge and a trailing edge, and an first edge with an airfoil pressure side structure; and joining the two structures together so that the airfoil suction side structure mates with the airfoil pressure side structure to form an airfoil.

Abstract: An acoustic resonator for use in an engine is provided. The acoustic resonator includes a cavity having a volume, an aperture, and a passage connecting the aperture and the cavity. The aperture has a profiled surface for delaying separation of fluid entering the passage and for reducing losses caused by fluid separation.

Abstract: An arrangement for reducing soybean losses in soybean headers, includes a plurality of retainers which may be engaged to a tray edge and each retainer comprises a plate having a substantially planar central portion ending at a lower end which is curved downwardly forming a rounded flange from which a portion providing two grooves is projected, and arranged at a slightly offset angle with respect to the central portion and the upper end of which is folded upwardly at an angle of approximately 45° from the central portion.

Abstract: Close to its front inner corner, each side plate is provided with an extension extending transversely inwards under the central plate and carrying a pivot member adapted to co-operate with a coaxial complementary pivot member fixed under the central plate, and in that each side plate is mounted to pivot about an axis that is common to the two pivot members, which axis is substantially perpendicular to the top surface of the central plate and arranged such that, in the pivoted position, each side plate is stowed substantially under the central plate. The system further advantageously comprising a device for causing each side plate to pivot relative to the central plate while the central plate is pivoting.

Abstract: The present invention relates to an apparatus for coating one or more workpieces such as components to be used in jet engines or industrial turbines. The apparatus comprises a device for simultaneously manipulating a workpiece about multiple axes while holding a center of the workpiece at a fixed position with respect to a source of coating material. The device for manipulating the workpiece preferably comprises a modular fixture while allows the workpiece to be simultaneously rotated about a first axis, rotated about a second axis at an angle to the first axis, and titled through a range of motion such as from +45 degrees to ?45 degrees with respect to the first axis.

Abstract: A turbine engine component such as a turbine blade includes an airfoil portion formed by a suction side wall and a pressure side wall, and a cooling microcircuit incorporated in at least one of the suction side wall and the pressure side wall. The cooling microcircuit comprises a channel through which a cooling fluid flows, at least one exit hole for distributing cooling fluid over a surface of the turbine blade, and internal features within the channel for accelerating the flow of cooling fluid prior to the cooling fluid flowing through the at least one exit hole.