Abstract: A compound differentially threaded element engages two or more longitudinally severed segments of a mating threaded element to provide differential linear motion. Different thread types may include pitch, thread starts, handedness or thread-form. Combinations of differential threads may be selected to enable fine or coarse linear motion without correspondingly fine or coarse thread pitches.

Abstract: A method of operating a multistage gas compressor system including providing a plurality of compressor stages connected in series, receiving a gas flow having contaminants within a gas passage, and supplying solvent to the gas passage at or upstream of a compressor in a compressor stage of the plurality of compressor stages to entrap or dissolve the contaminants in the gas flow. The method includes resisting disabling fouling of the compressor in the compressor stage from any contaminants entrapped or dissolved in the solvent, for example, by controlling a discharge temperature of the compressor, and/or using a type of compressor that is not susceptible to being disabled by fouling in at least the first stage. The discharge temperature can be controlled by providing the compressor with a pressure ratio selected to provide a desired discharge temperature.

Abstract: This scanning array scans an area around the array for nearby objects, collision obstructions, and terrain topography. The scanning array can scan for sounds emitted by objects in the vicinity of the scanning array, passive energy receipt sources, or it can also send out an energy beam and scan for reflections from objects within the energy beam. The energy beam can be optical, laser, radar or other energy emitting sources. The scanning array of the invention can be used for helicopter detection and avoidance of collision risk and can be used for other scanning purposes. Scanning of an entire hemisphere or greater is accomplished by manipulating the scanner platform through the coordination of either linear actuators or gimbals so as to produce nutation without rotation. This motion allows transceivers to be directly coupled to transmitting and sensing modules without the losses associated with slip rings and other coupling devices.

Abstract: A method of operating a multistage gas compressor system including providing a plurality of compressor stages connected in series, receiving a gas flow having contaminants within a gas passage, and supplying solvent to the gas passage at or upstream of a compressor in a compressor stage of the plurality of compressor stages to entrap or dissolve the contaminants in the gas flow. The method includes resisting disabling fouling of the compressor in the compressor stage from any contaminants entrapped or dissolved in the solvent, for example, by controlling a discharge temperature of the compressor, and/or using a type of compressor that is not susceptible to being disabled by fouling in at least the first stage. The discharge temperature can be controlled by providing the compressor with a pressure ratio selected to provide a desired discharge temperature.

Abstract: An apparatus for deploying a propeller assembly from a folded configuration to a deployed, operational configuration, the apparatus comprising a propeller assembly hub which in conjunction with a propeller hub nut maintains an aerodynamically efficient shape after the propeller assembly is deployed, the propeller hub nut which is diametrically large enough to allow assembly of a drive shaft and a drive shaft bevel gear and includes a cavity to accept a spring detent, a propeller blade which protrudes from a journal located in the surface of the propeller assembly hub where when in its folded configuration, the propeller blade is in the same parallel axial direction as the drive shaft and when deployed is nutated to a radially outwardly extending operative position in response to rotating of a propeller blade bevel gear, the drive shaft rotated about its axis where one end engages a prime mover and a second distal end engages the hub nut, drive shaft bevel gear fixed to the drive shaft near the distal end whic

Abstract: An airborne vehicle having a deployable airfoil with an elevon wherein the deployment of the airfoil and the control of the elevon are both powered by a single servo mechanism. A shear pin prevents relative movement between the elevon and the airfoil until the airfoil is in the deployed position. A stop mechanism locks the airfoil in the deployed position, whereafter operation of the drive mechanism fractures the shear pin, thereby allowing the elevon to be controlled by the drive mechanism.

Abstract: A roller screw assembly includes a threaded rod, a nut having internal, non-helical grooves and a plurality of externally grooved elongated rollers seated circumferentially about the rod and captured in place by the nut. The grooves in the nut and rollers are selected to have the same spacing as the pitch of the rod threads and with a corresponding profile so as to allow intermeshing engagement between the nut, rollers and rod. The inner surface of the nut is formed such that a cross-section normal to the axis of the rod illustrates at least one lobed area which is of sufficient extent to allow a roller in that area to translate axially with respect to the rod. The number of lobes is dependent on the number of threads or parallel helices formed on the rod. Rotation of the nut with respect to the rod enables axial translation of the nut with respect to the rod by recirculation of the grooved rollers at the lobed region.

Abstract: An optical apparatus for selectively directing a line of sight between a residence location and locations within a substantially hemispherical field of regard. The apparatus includes a stator which supports a first stage for rotation about a first axis of rotation. A second stage is supported by the first stage for at least partial rotation about a second axis of rotation. The first stage and the second stage include respective mirrors which direct the line of sight between the residence location and the locations in the field of regard. The first stage and the second stage are each operatively rotated by one or more foundation-based drive motors or the like. A drive train arrangement is preferably utilized to transfer motive power from the stationary drive motor to the second stage.

Abstract: An optical apparatus for selectively directing a line of sight between a residence location and locations within a substantially hemispherical field of regard. The apparatus includes a stator which supports a first stage for rotation about a first axis of rotation. A second stage is supported by the first stage for at least partial rotation about a second axis of rotation. The first stage and the second stage include respective mirrors which direct the line of sight between the residence location and the locations in the field of regard. The first stage and the second stage are each operatively rotated by one or more foundation-based drive motors or the like. A drive train arrangement is preferably utilized to transfer motive power from the stationary drive motor to the second stage.

Abstract: A multipiece combustor has a portion thereof being made of a plurality of ceramic segments. Each of the plurality of ceramic segments have an outer surface and an inner surface. Each of the plurality of ceramic segments have a generally cylindrical configuration and including a plurality of joints. The joints define joint portions, a first portion defining a surface being skewed to the outer surface and the inner surface. The joint portions have a second portion defining a surface being skewed to the outer surface and the inner surface. The joint portions further include a shoulder formed intermediate the first portion and the second portion. The joints provide a sealing interlocking joint between corresponding ones of the plurality of ceramic segments.

Abstract: An airfoil and nozzle assembly including an outer shroud having a plurality of vane members attached to an inner surface and having a cantilevered end. The assembly further includes a inner shroud being formed by a plurality of segments. Each of the segments having a first end and a second end and having a recess positioned in each of the ends. The cantilevered end of the vane member being positioned in the recess. The airfoil and nozzle assembly being made from a material having a lower rate of thermal expansion than that of the components to which the airfoil and nozzle assembly is attached.

Abstract: An axial flow turbine's nozzle/nozzle support structure having a cantilevered nozzle outer structure including an outer shroud and airfoil vanes extending radially inwardly therefrom, an inner shroud radially adjacent the inner end of the airfoil vanes and cooperatively disposed relative to the outer shroud to provide an annular fluid flow path, an inner and an outer support ring respectively arranged radially inside the inner shroud and axially adjacent a portion of the outer shroud, and pins extending through such portion and into the outer support ring. The inner support ring or inner shroud has a groove therein bounded by end walls for receiving and being axially abuttable with a locating projection from the adjacent airfoil vane, inner shroud, or inner support ring.

Abstract: A turbine nozzle and shroud assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine nozzle vane assembly. The turbine nozzle vane assembly includes a plurality of segmented vane defining a first vane segment and a second vane segment. Each of the first and second vane segments having a vertical portion. Each of the first vane segments and the second vane segments being positioned in functional relationship one to another within a recess formed within an outer shroud and an inner shroud. The turbine nozzle and shroud assembly provides an economical, reliable and effective ceramic component having a preestablished rate of thermal expansion being less than the preestablished rate of thermal expansion of the other component.

Abstract: An axial flow turbine's nozzle/nozzle support structure having a cantilevered nozzle outer structure including an outer shroud and airfoil vanes extending radially inwardly therefrom, an inner shroud radially adjacent the inner end of the airfoil vanes and cooperatively disposed relative to the outer shroud to provide an annular fluid flow path, an inner and an outer support ring respectively arranged radially inside the inner shroud and axially adjacent a portion of the outer shroud, and pins extending through such portion and into the outer support ring. The inner support ring or inner shroud has a groove therein bounded by end walls for receiving and being axially abuttable with a locating projection from the adjacent airfoil vane, inner shroud, or inner support ring.

Abstract: A nozzle guide vane assembly has ceramic components therein having a conventional thread thereon including a preestablished pitch and having a preestablished rate of thermal expansion. The nozzle guide vane assembly has a metallic components therein having a preestablished rate of thermal expansion being greater that the rate of thermal expansion of the ceramic components is positioned in a gas turbine engine. The metallic component, a nut, has a thread therein including a plurality of crests being spaced on a pitch equal to that of the ceramic component and has a pair of contacting surfaces extending from the plurality of crests. A notch spirally extends intermediate adjacent ones of the plurality of crests and has a preestablished depth which is at least twice the size of the conventional pitch. Furthermore, the pair of contacting surfaces are in contact with only a portion of the threaded surface of the ceramic components.

Abstract: A gas turbine engine's nozzle structure includes a nozzle support ring, a plurality of shroud segments, and a plurality of airfoil vanes. The plurality of shroud segments are distributed around the nozzle support ring. Each airfoil vane is connected to a corresponding shroud segment so that the airfoil vanes are also distributed around the nozzle support ring. Each shroud segment has a hook engaging the nozzle support ring so that the shroud segments and corresponding airfoil vanes are supported by the nozzle support ring. The nozzle support ring, the shroud segments, and the airfoil vanes may be ceramic.

Abstract: A nozzle guide vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The nozzle guide vane assembly includes an outer shroud having a mounting leg with an opening defined therein, a tip shoe ring having a mounting member with an opening defined therein, a nozzle support ring having a plurality of holes therein and a pin positioned in the corresponding opening in the outer shroud, opening in the tip shoe ring and the hole in the nozzle support ring. A rolling joint is provided between metallic components of the gas turbine engine and the nozzle guide vane assembly. The nozzle guide vane assembly is positioned radially about a central axis of the gas turbine engine and axially aligned with a combustor of the gas turbine engine.

Abstract: A nozzle guide vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The nozzle guide vane assembly includes a pair of legs extending radially outwardly from an outer shroud and a pair of mounting legs extending radially inwardly from an inner shroud. Each of the pair of legs and mounting legs have a pair of holes therein. A plurality of members attached to the gas turbine engine have a plurality of bores therein which axially align with corresponding ones of the pair of holes in the legs. A plurality of pins are positioned within the corresponding holes and bores radially positioning the nozzle guide vane assembly about a central axis of the gas turbine engine.

Abstract: A combustor assembly having a preestablished rate of thermal expansion is mounted within a gas turbine engine housing having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the combustor assembly. The combustor assembly is constructed of a inlet end portion, a outlet end portion and a plurality of combustor ring segments positioned between the end portions. A mounting assembly is positioned between the combustor assembly and the gas turbine engine housing to allow for the difference in the rate of thermal expansion while maintaining axially compressive force on the combustor assembly to maintain contact between the separate components.

Abstract: The present invention provides a ceramic nozzle guide assembly with an apparatus for mounting it to a metal nozzle case that includes an intermediate ceramic mounting ring. The mounting ring includes a plurality of projections that are received within a plurality of receptacles formed in the nozzle case. The projections of the mounting ring are secured within the receptacles by a ceramic retainer that allows contact between the two components only along arcuate surfaces thus eliminating sliding contact between the components.