Abstract: A rotatable child safety seat can include a seat shell for receiving a child therein. a rotating pedestal, and a seat base. The pedestal and seat shell can rotate with respect to the seat base. The pedestal can include a locking pin and the seat base can include a multitude of pin receiving apertures that allow a user to rotate the seat shell and pedestal in either a clockwise or counter-clockwise direction at a number of different angles or positions. The child safety seat can also include two separate seat belt/LATCH tether pathways. One seat belt/LATCH tether pathway can be provided on the seat back of the seal shell and can be used when the child safety seat is in a forward-facing configuration and the other seat belt/LATCH tether pathway can be provided in the seat base and used when in a rearward-facing configuration.

Abstract: A pipe coupon extraction tool includes a rod defining a first end, a second end, and a central axis; and a spring bar defining a first end and a second end, the spring bar rotatably secured to the rod, a surface of the spring bar configured to be angled with respect to the central axis when the pipe coupon extraction tool is engaged with a pipe coupon.

Abstract: A cut warning system can include a valve sleeve defining a cavity, the valve sleeve defining a bottom sealing surface within the cavity; a pipeline extending through the cavity; a drilling machine including a shell cutter, the shell cutter defining a bottom edge, the drilling machine configured to axially advance the shell cutter from a pre-engagement position towards the bottom sealing surface, the pipeline positioned between the shell cutter and the bottom sealing surface in the pre-engagement position; and a signaling element positioned within the cavity, the signaling element configured to produce a signal when the shell cutter reaches a post-engagement position, the bottom edge being axially positioned between the pipeline and the bottom sealing surface.

Abstract: Systems, methods, and software are included herein to manage domain name system (DNS) requests to DNS servers. In one implementation, a computing device joins a local network and identifies a connection to a first DNS server associated with the local network. The computing device further implements first DNS rules based on the connection to the first server and monitors when a second DNS server is available using the local network. When the second DNS server becomes available, the computing device implements second DNS rules in place of the first DNS rules, wherein the second DNS rules direct DNS requests to the second DNS server in place of the first DNS server.

Abstract: By surface roughening of CMC component via a pico-laser treatment a good adhering of a plasma sprayed coating is achieved.

Abstract: A gas turbine engine seal assembly (160) including: a rigid seal (58) cooperatively configured with a structure (14, 42) of a gas turbine engine to define a leakage path (102, 130) including a flow-controlling section (106, 134); and a compliant seal (162, 164) positioned in the leakage path.

Abstract: A sealing band arrangement for a gas turbine including first and second adjoining rotor disks each including a disk arm having a slot. The sealing band arrangement includes at least one first seal strip segment located within the slots, wherein the seal strip segment includes first and second ends. The sealing band arrangement also includes a tab section that extends from the first end in order to form an underlap seal with an adjacent second seal strip segment. The underlap seal enables a thickness of the first and second ends to be substantially equivalent to a thickness of the first seal strip segment in order to improve wear life of the seal strip segment. The sealing band arrangement further includes at least one wide portion formed in the first seal strip segment wherein the wide portion is wider than a remaining portion of the first seal strip segment.

Abstract: A turbine is provided comprising a plurality of stages, each stage comprising a rotatable disk and blades carried thereby, at least one pair of adjacent rotatable disks defining an annular gap therebetween and having respective opposing sealing band receiving slots aligned with the annular gap A sealing band is located in the opposing receiving slots to seal the annular gap Disk engagement structure is defined in the pair of adjacent rotatable disks. A clip member is coupled to the sealing band and engaged with the pair of adjacent rotatable disks through the disk engagement structure The clip member may have an aperture extending only partially through the clip member for alignment with a hole in the sealing band for engagement with a tool To improve weld geometry, the clip member may have angled surfaces and notched areas, and the sealing band may have chamfered edges.

Abstract: A gas turbine engine seal assembly (160) including: a rigid seal (58) cooperatively configured with a structure (14, 42) of a gas turbine engine to define a leakage path (102, 130) including a flow-controlling section (106, 134); and a compliant seal (162, 164) positioned in the leakage path.

Abstract: A self-powered sensing and transmitting circuit (50) including a power element (44) and a sensing element (46) that is powered by the power element for generating a sensor signal responsive to a local operating environment The circuit also includes a transmitting element (48) powered by the power element for transmitting an output signal responsive to the sensor signal to a receiving location (33, 55) remote from the circuit The power element, sensing element and transmitting element of the circuit are arranged in a generally planar and non-integrated circuit configuration formed on a substrate (57) component exposed to operating temperatures at or exceeding 650° C.

Abstract: A turbine including a plurality of stages, each stage including a rotatable disk and blades carried thereby. An annular gap defined between a pair of adjacent rotatable disks. A sealing band is located in opposing sealing band receiving slots formed in the adjacent disks to seal the annular gap, the sealing band including band engagement structure. A disk engagement structure is defined in the pair of adjacent rotatable disks. The disk engagement structure extends axially into the pair of adjacent rotatable disks and circumferentially aligns with the band engagement structure. A clip member is positioned in engagement with the sealing band through the band engagement structure and in engagement with the pair of adjacent rotatable disks through the disk engagement structure. The clip member restricts movement of the sealing band in only a circumferential direction of the slots.

Abstract: A method and apparatus for improved turbine bellyband rotor seal machining, installation and life are disclosed. A fixture is provided which can be temporarily attached to the turbine disks in a position straddling the gap between the disks, without destacking the turbine rotor. The fixture accepts power tools including a drill and a mill, and positions the power tools to drill and grind a rectangular slot into the disks, where the slot has the exact size and shape needed to receive an anti-rotation block which is integral to the replacement bellyband. Measuring tools are also provided which enable precise location of each of the four slots which must be machined in the disks. The resulting slots have a uniform size and shape, and are equally spaced around the circumference of the disk, thereby facilitating installation of the service bellyband from four identical segments.

Abstract: A sealing band arrangement for a gas turbine including first and second adjoining rotor disks each including a disk arm having a slot. The sealing band arrangement includes at least one first seal strip segment located within the slots, wherein the seal strip segment includes first and second ends. The sealing band arrangement also includes a tab section that extends from the first end in order to form an underlap seal with an adjacent second seal strip segment. The underlap seal enables a thickness of the first and second ends to be substantially equivalent to a thickness of the first seal strip segment in order to improve wear life of the seal strip segment. The sealing band arrangement further includes at least one wide portion formed in the first seal strip segment wherein the wide portion is wider than a remaining portion of the first seal strip segment.

Abstract: A method and apparatus for improved turbine bellyband rotor seal machining, installation and life are disclosed. A fixture is provided which can be temporarily attached to the turbine disks in a position straddling the gap between the disks, without destacking the turbine rotor. The fixture accepts power tools including a drill and a mill, and positions the power tools to drill and grind a rectangular slot into the disks, where the slot has the exact size and shape needed to receive an anti-rotation block which is integral to the replacement bellyband. Measuring tools are also provided which enable precise location of each of the four slots which must be machined in the disks. The resulting slots have a uniform size and shape, and are equally spaced around the circumference of the disk, thereby facilitating installation of the service bellyband from four identical segments.

Abstract: An inductance-stable ultra high temperature circuit coupling transformer (50) used to transmit and receive alternating current power and/or data signals (29?, 33?). Primary (30?) and secondary (34?) windings are formed on nanostructured laminated (31?) primary and secondary steel cores (32?) having a Curie temperature exceeding an ultra high operating temperature. The operating range can extend from ambient to 250° C. or to in excess of 550° C. or up to 700° C. with a change in inductance of less than 10% in various embodiments.

Abstract: A self-powered sensing and transmitting circuit (50) including a power element (44) and a sensing element (46) that is powered by the power element for generating a sensor signal responsive to a local operating environment The circuit also includes a transmitting element (48) powered by the power element for transmitting an output signal responsive to the sensor signal to a receiving location (33, 55) remote from the circuit The power element, sensing element and transmitting element of the circuit are arranged in a generally planar and non-integrated circuit configuration formed on a substrate (57) component exposed to operating temperatures at or exceeding 650° C.

Abstract: A turbine is provided comprising a plurality of stages, each stage comprising a rotatable disk and blades carried thereby, at least one pair of adjacent rotatable disks defining an annular gap therebetween and having respective opposing sealing band receiving slots aligned with the annular gap A sealing band is located in the opposing receiving slots to seal the annular gap Disk engagement structure is defined in the pair of adjacent rotatable disks. A clip member is coupled to the sealing band and engaged with the pair of adjacent rotatable disks through the disk engagement structure The clip member may have an aperture extending only partially through the clip member for alignment with a hole in the sealing band for engagement with a tool To improve weld geometry, the clip member may have angled surfaces and notched areas, and the sealing band may have chamfered edges.

Abstract: A telemetry system for use in a combustion turbine engine (10) having a compressor (12), a combustor and a turbine (16) that includes a sensor (306) in connection with a turbine blade (301) or vane (22). A telemetry transmitter circuit (312) may be affixed to the turbine blade with an electrical connecting material (307) for routing electronic data signals from the sensor (306) to the telemetry transmitter circuit, the electronic data signals indicative of a condition of the turbine blade. A resonant energy transfer system for powering the telemetry transmitter circuit may include a rotating data antenna (314) affixed to the turbine blade or on a same substrate as that of the circuit. A stationary data antenna (320) may be affixed to a stationary component such as a stator (323) proximate and in spaced relation to the rotating data antenna for receiving electronic data signals from the rotating data antenna.

Abstract: A voltage regulator circuitry (50) adapted to operate in a high-temperature environment of a turbine engine is provided. The voltage regulator may include a constant current source (52) including a first semiconductor switch (54) and a first resistor (56) connected between a gate terminal (G) and a source terminal (S) of the first semiconductor switch. A second resistor (58) is connected to the gate terminal of the first semiconductor switch (54) and to an electrical ground (64). The constant current source is coupled to generate a voltage reference across the second resistor 58. A source follower output stage 66 may include a second semiconductor switch (68) and a third resistor (58) connected between the electrical ground and a source terminal of the second semiconductor switch. The generated voltage reference is applied to a gating terminal of the second semiconductor switch (58).

Abstract: A turbine including a plurality of stages, each stage including a rotatable disk and blades carried thereby. An annular gap defined between a pair of adjacent rotatable disks. A sealing band is located in opposing sealing band receiving slots formed in the adjacent disks to seal the annular gap, the sealing band including band engagement structure. A disk engagement structure is defined in the pair of adjacent rotatable disks. The disk engagement structure extends axially into the pair of adjacent rotatable disks and circumferentially aligns with the band engagement structure. A clip member is positioned in engagement with the sealing band through the band engagement structure and in engagement with the pair of adjacent rotatable disks through the disk engagement structure. The clip member restricts movement of the sealing band in only a circumferential direction of the slots.