Abstract: A bushing assembly for a turbine vane includes a bushing, housing, and a flexible conductor. The bushing includes a bore for receiving a trunnion of the vane and a first conductor extending from the bushing. The first conductor is adapted to be connected to a heater element disposed on the vane. The housing is positioned over the bushing, and the bushing is rotatable relative to the housing. The housing includes a second conductor extending from the housing for connection to an electrical power source. The flexible conductor is electrically connected between the first conductor and the second conductor, such that an electric current is transmitted from the second conductor to the first conductor to provide an electric current to the heater element.

Abstract: A seal assembly for a fluid coupling includes: (a) a generally planar, substantially rigid seal retainer with opposed first and second faces, having an annular first groove formed in the first face; (b) a first resilient seal disposed in the first groove; and (c) an annular first backup ring positioned radially outboard of the first resilient seal and secured to the first resilient seal, wherein the first backup ring is substantially harder than the first resilient seal.

Abstract: A self-contained in-borehole gas monitor (IGM) apparatus (8) comprising a detector for measuring a gas variable, and a controller (54) configured to automatically periodically use the detector to measure a gas variable.

Abstract: A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. A tip baffle bifurcates the airfoil tip into two pockets, with a first pocket being laterally open at its aft end to recover leakage flow, and a second pocket being laterally closed.

Abstract: A balance weight for a rotor includes: (a) an arcuate body including a front wall and a rear wall interconnected by an end wall, the front, rear, and end walls collectively defining a generally U-shaped cross-sectional shape; and (b) a projection extending outwardly from the rear wall, the projection being adapted to engage an aperture extending through a flange of the rotor.

Abstract: A gas turbine engine bearing cage assembly includes: a first bearing cage having: an annular first bearing support ring; an annular first mounting flange; and an annular array of axially-extending first spring arms interconnecting the first bearing support ring and the first mounting flange, the first spring arms defining an outer diameter; and a second bearing cage having: an annular second bearing support ring; an annular second mounting ring, the second mounting ring defining an inner diameter greater that the outer diameter; and an annular array of axially-extending second spring arms interconnecting the second bearing support ring and the second mounting ring, the second spring arms defining spaces therebetween. The bearing cages are sized such that the first bearing cage can be received within the second bearing cage. The spaces are positioned to receive the first spring arms, permitting independent flexing motion of the first and second spring arms.

Abstract: A service tube apparatus for a gas turbine engine includes a service tube assembly having: (a) an elongated, hollow service tube; and (b) a service tube baffle surrounding the service tube which is pierced with a plurality of impingement cooling holes.

Abstract: A mixer for a gas turbine engine combustor includes: (a) a primary fuel injector with upstream and downstream ends, the primary fuel injector including: (1) a hollow central portion configured to pass a first air stream; (2) an annular fuel passage at the downstream end, configured to discharge an annular first fuel stream surrounding the first air stream; (b) an annular splitter surrounding the primary fuel injector, configured to pass a second air stream surrounding the first fuel stream; (c) an annular first housing surrounding the splitter, and having an exit positioned axially downstream of the primary fuel injector and the splitter; and (d) fuel injection ports disposed in an array outside the first housing, and disposed in communication with a fuel supply and positioned to discharge a second fuel stream into a third air stream at a position axially upstream of the exit of the first housing.

Abstract: A turbine nozzle for a gas turbine engine includes: (a) spaced-apart arcuate inner and outer bands; (b) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the interior of the vane defining at least a forward cavity and a mid-cavity positioned aft of the forward cavity; (c) a hollow impingement insert received inside the mid-cavity, the impingement insert having walls which are pierced with at least one impingement cooling hole; (d) a passage in the turbine vane at a radially outer end of the forward cavity adapted to be coupled to a source of cooling air; and (e) a passage in the inner band in fluid communication with a radially inner end of the forward cavity and a radially inner end of the impingement insert.

Abstract: A preform includes an airfoil stub and a dovetail hub. The hub first undergoes electrochemical discharge machining to form a rough dovetail. The airfoil stub undergoes electrochemical machining to form an airfoil. The rough dovetail then undergoes electrochemical discharge machining to form a rough tang. The rough tang is finish machined to form a dovetail extending from the airfoil in a unitary rotor blade.

Abstract: Methods for processing a signal of interest in an electrical power system are provided, as well as systems and computer program products for carrying out the methods. The methods include obtaining a representative window of data points from the signal of interest; obtaining a window of interest containing data points from the signal of interest; and comparing a phase drift compensated window to the representative window, wherein the compensated window is calculated in accordance with the window of interest and a phase drift that is present in the window of interest relative to the representative window.

Abstract: A method for regulating gas turbine engine fluid flow may include the steps of providing a flow tube having an open valve, a first bend and a second bend, flowing fluid through the flow tube, actuating a piston so that the piston moves in the axial direction, and closing the valve due to the axial movement of the piston.

Abstract: A baffle seal for a thrust reverser of a gas turbine engine includes a seal body of a resilient material. The seal body has a relatively flat central portion with opposed front and back sides. A raised sealing rim extends at least partially around the central portion. An outer periphery of the sealing rim extends beyond an outer periphery of the central portion so as to define an exposed sealing surface.

Abstract: A fairing for a structural strut in a gas turbine engine includes: (a) an inner band; (b) an outer band; (c) a hollow, airfoil-shaped vane extending between the inner and outer bands; (d) wherein the fairing is split along a generally transverse plane passing through the inner band, outer band and vane, so as to define a nose piece and a tail piece; and (e) complementary structures carried by the nose piece and the tail piece adapted to secure the nose piece and the tail piece to each other.

Abstract: A turbine shroud includes a shroud hanger having an arcuate panel from which three inner hooks extend inwardly, and from which two outer hooks extend outwardly therefrom. The two outer hooks effect a statically determinate configuration of the shroud.

Abstract: An electronic date calculator includes an electronic processor, input keys operably connected to the processor, at least one date function key corresponding with a selected date unit and operably connected to the processor, and a display operably connected to the processor. The processor is programmed to drive the display to show a present date. In response solely to entry of a multiplier from the input keys and a date unit from the date function key, the processor adds a product of the selected date unit and the multiplier to the present date to generate a resulting date, and drives the first display to show the resulting date.

Abstract: A method for operating a train includes: (a) using a processor carried by the train, creating a trip profile which is computed at so as to substantially optimize an operating parameter of the train which depends on multiple operating variables; (b) operating the train along a route at speeds determined by the trip profile; (c) identifying a target location ahead of the train which cannot be cleared in a desired time if the train operates in accordance with the trip profile; and (d) operating the train at a clearing speed substantially faster than determined by the trip profile until the target location is cleared. A computer program product is provided for carrying out the method.

Abstract: A turbine nozzle includes: a hollow, airfoil-shaped turbine vane; and an arcuate first band disposed at a first end of the turbine vane, the first band having a flowpath face adjacent the turbine vane, and an opposed back face. The back face includes at least one open pocket, the at least one pocket defined in part by a bottom wall recessed from the back face, opposed ends of the bottom wall merging with the back face. The bottom wall is substantially free of interior corners.

Abstract: A valve assembly may include a body having an axis and a flow tube attached to the body for flowing a fluid therethrough, the flow tube having a first bend and a second bend. The valve assembly may further include a valve attached to the flow tube having an axle that is perpendicular to the axis, and a piston attached to the body and the axle and parallel to the axis.