Abstract: Noise reduction conduit for non rotary components of aircraft engines, subjected to a characteristic range of temperatures of a gas turbine engine, constituted by an annular structure composed of an aerodynamic wet wall (10a, 10b), perforated and resistant mechanically and thermally; of a dry wall (12a, 12b), not resistant and of light weight; and of some intermediate elements to which both walls are mechanically attached and that define a jump or difference of temperature between the wet and dry walls; between which wet (10a, 10b) and dry walls (12a, 12b) there are partitions that define cavities (16a, 16b) isolated with regard to each other.

Abstract: Remote activation mechanism for equipment hold down and release, composed of a fixed base (1); a disk with capacity to rotate (2); a ring (3) subdivided in independent segments; a helical torsion spring (4) mounted around the segmented, being in one end joined to the fixed base (1) and the other end to the disk (2); a retainer (5) to attach the hardware, that passes through the fixed base (1) and has means to be blocked by the segmented ring (3); a disk blocking system; and a disk liberation system (2). The disk (2) can potentially rotate from a position in which the helical torsion spring (4) is loaded hugging radially the segmented ring (3), up to a position in which the helical torsion spring (4) is unloaded, allowing the ring segments move radially away to release the retainer (5). The disk blocking system can be based on rollers or balls (12) with possibility of being inserted partially in disk grooves or in crown grooves.

Abstract: Remote activation mechanism for equipment regulated deployment or release, that includes a cylindrical housing (1), connected by means of a rod (10) with the external equipment to be deployed including the acting mechanism, and has adhered a fusible material band in its internal surface (11). Inside the housing a cylindrical frame (2) connected with the fixed part of the equipment is disposed. That frame is provided with means to perform the local and progressive fusion of the fusible material band. Additionally a cylindrical sealing piece (3) is disposed in between the fusible material band (11) and the frame (2).

Abstract: Axisymmetric nozzles of variable geometry and orientation of flow intended for gas turbine engines, especially for aircraft. The nozzle comprises control means for adjusting the throat area and vectoring the thrust, which means are formed by three rings concentric to the longitudinal axis of the engine, an inner ring, an intermediate ring, and an outer ring, and by a plurality of linear actuators. The outer ring includes two ring segments interarticulated to each other and swingable independently or in unison to vector the thrust of the aircraft, said swinging and corresponding thrust vectoring being limited to a single plane corresponding to the pitch of the aircraft.

Abstract: An apparatus and procedure is described for the characterization of sprays composed by spherical particles, by means of a laser source (1) generating a collimated laser beam (2) that is passed through the spray to be characterized. The laser beam is made to coincide with the x-axis of a cartesian coordinate system (3) contained in a measurement plane perpendicular to the spray axis. A scattering collection means (5) is disposed to obtain the 90.degree. scattering activity produced by the spray material in a small probe volume formed at the intersection of the laser beam and the object volume of the scattering collection means. Additional collection means (14) are included to obtain the attenuation of the laser beam passing trough the measurement plane. The optical systems (5 and 14) are coupled to photodetectors (10 and 18) and signal processing units (10' and 18') able to generate electrical signals proportional to the received light intensities.

Abstract: Improvements in orientable axisymmetric nozzles of variable geometry which are intended for gas turbine engines, which nozzles comprise a convergent zone (2) followed by a divergent zone (3), both formed by main petals (4-5) and secondary petals (33-34), and they add to the known functions (simultaneous axisymmetric variation, according to a preestablished law, of the throat area A8 and of the outlet area A9; variation of all the geometry of the outlet area A9 independently of the throat area A8; and, axisymmetric orientation of the flow) a fourth function of varying only a part of the geometry of the outlet area A9 independently of the throat area A8.

Abstract: A divergent master petal for orientable nozzles of variable geometry intended for gas turbine engines, which is connected by means of articulations to the convergent master petal (4) and to a bar (12) which connects the master petal to the control mechanism. The inner surface (5c) of the divergent master petal (5), which is in contact with the flow of gases, is of variable shape between a substantially straight cross section coinciding with or close to the upstream transverse edge and a convexly curved cross section coinciding with or next to its downstream end transverse edge, with the convexity directed towards the inside of the engine.

Abstract: A divergent slave petal for sealing in variable geometry exhaust nozzles for gas turbine propulsion units includes a base plate for bearing axial forces but having minimum capacity for transmitting torsional forces and a plurality of discrete transverse elements for transmitting transverse and shear forces but not those torsion forces acting about the longitudinal axis of the petal. The base plate and discrete transverse elements are linked by guide elements running along the longitudinal edges of the base plate and by intermediate discrete transverse element fasteners.

Abstract: Orientable axisymmetric nozzle of variable geometry for gas turbine engines which comprises convergent (2) and divergent (3) sections formed by master petals (4, 5) and slave petals (33, 34) duly connected together, each divergent master petal (5) being connected to an outer annular control part (6) by a biarticulated bar (15). This bar is connected by one end to the part (6) by a cylindrical articulation (16) while by its opposite end it is connected to the divergent master petal (5) via intermediate bars (26, 27).

Abstract: A thrust vectoring variable geometry exhaust nozzle for gas turbines, which includes a convergent section (2) followed, in the direction of the flow, by a divergent section (3), both formed by master (4 and 5) and slave petals (41 and 42), whose convergent section (2) defines a throat (15) having a variable area. The divergent section (3) has variable geometry in order to orientate the thrust, and includes a governing and external radial support system for regulating the throat area (15), and a governing system for regulating the vectoring of the thrust. Both system are formed by a single governing system consisting of three annular pieces (6,7 and 8), concentric among themselves and with the axis of the turbine, and by a plurality of linear actuators (9). The master petals (5) of the divergent section (3) are transversely subdivided into at least two segments (5a, 5b).

Abstract: A tracking solar radiation structure which includes a main support column and a plurality of secondary structures mounted on the main column with a series of reflecting surfaces on the secondary structures. The bearing column extends in an inclined plane and is rotatable about its axis. The secondary reflector structures are articulatedly connected to the bearing column and adapted to swing with respect to the bearing column around the axis of articulation. The bearing column is supported at its lower end on an appropriate base and at a section above its mid-point by a substantially flat structure perpendicular to the axis of rotation of the bearing column.

Abstract: Apparatus for reflecting light including a head carrying a reflecting panel and mounted for rotation on a column, said head including a mechanism for rotating said panel about a horizontal axis between a first range of positions for following the sun and an inverted position, said mechanism including an articulated quadrilateral controlled by a linear actuator.

Abstract: A transport vessel especially used in connection with the transportation of liquid gases, e.g., natural gas, includes means for isolating storage tanks from the hull of the vessel to minimize the deformations to the tank from the hull. In this way, the thickness and hence weight of the tanks may be significantly reduced.

Abstract: A marine platform supports industrial installations. The platform comprises a barge and a lower keel on which the barge rests. The keel is positioned on the ocean floor. Intermediate friction elements are situated between the contact surfaces of the barge and the keel. Elastic elements are interconnected to the barge and the keel. These elastic elements oppose displacements between the barge and the keel. The displacements are controlled because the friction resulting from the intermediate friction elements impedes movements between the barge and the keel. These movements may be caused by external forces acting on the barge, such as waves, currents, and winds, or may be caused by the effects of acceleration on the keel induced by an earthquake of small magnitude. The intermediate friction elements have means for permitting displacements between the barge and the keel in the case of an earthquake of great magnitude.