Abstract: A compressor shroud for an aircraft turbine engine, the shroud being arranged between two bladed rotary wheels and radially in line with a deflector, the shroud including a sealing device including one or more sealing elements, including a downstream end sealing element on which, projecting downstream, an air entraining and diverting structure is provided, designed to axially divert the discharge air issuing from the end sealing element.

Abstract: A demand-based load balancing function may be provided by one or more drive controllers that takes advantage of the affinity laws to linearize the control of the variable of interest (e.g., flow, pressure, etc.). Each drive controller may be set up by the user simply inputting a few values into the drive controller. Based on the inputs, the drive controllers may interpolate control points using an assumed linear relationship between the variable to be controlled (e.g., pressure) and the current driven to the pump. Feedback data from the system may be used to continually update the drive controllers so as to potentially allow them to better balance power usage to each pump.

Abstract: A platform for a bladed wheel having a small hub-tip ratio, suitable for being fabricated out of composite material from a three-dimensionally woven fiber preform, the platform including a bottom wall, a top wall defining an air flow passage, and two side walls extending transversely between the bottom wall and the top wall, wherein the side walls extend longitudinally beyond the upstream end of the bottom wall. The platform further includes a fastener tab that is folded from the upstream end of the bottom wall.

Abstract: A turbine blade, including: an airfoil and a platform, which has an upper face on which the airfoil is arranged; and at least one lateral face, the lateral face including a slot for insertion of a sealing strip. The transition between the upper face of the platform and the at least one lateral face includes a stepped portion and a beveled portion is provided.

Abstract: A carrier segment of a carrier section for circumscribing an array of circumferentially spaced turbine blades of a gas turbine engine, the blades being disposed radially inwardly of a turbine casing, the carrier segment including a carrier wall disposed radially inwardly of the casing and radially outwardly of the turbine blades, and the carrier wall including one or more portions facing the casing, wherein at least one of the one or more portions of the carrier wall is provided with one or more impingement apertures therein for passage therethrough of air of a predetermined temperature, heating air, from a feed source into impingement onto the turbine casing. The application of heating air onto the casing during transient stages of enhanced engine power, e.g. during step climbs, results in better matching of radial expansion of the casing relative to the turbine blades, thereby enabling improved blade tip clearance control.

Abstract: An exemplary variable vane actuation system for a gas turbine engine includes a vane arm attachable to a vane stem and configured to rotate the vane stem about a radially extending axis. The vane arm includes a claw feature to be press-fit onto the vane stem.

Abstract: An internal hot gas bypass device coupled with inlet guide vane for centrifugal compressor includes an inlet guide vane assembly, a driving motor assembly and a gas bypass valve assembly. The inlet guide vane assembly further includes a master vane, a plurality of slave vanes, a vane-front fixing ring, a vane-rear fixing ring, a vane-driving ring, a connecting pipe and a vane-opening indicating disk. The driving motor assembly further includes a motor, a driving unit and a motor fixing base. The gas bypass valve assembly further includes a valve, an external fixing-and-guiding ring, an internal fixing-and-guiding ring, a driven element, a spring, a sealing ring, a valve stud and a valve base. The driving motor assembly is connected with the driving unit and the master vane of the inlet guide vane assembly via a connecting rod, and is further connected with the slave vanes of the gas bypass valve assembly.

Abstract: The present disclosure relates generally to a system for handling a gas turbine engine fan case. The system includes a composite fan containment case including a case outer surface, a case inner surface, and at least one main case aperture extending from the case outer surface through the case inner surface, and at least one shear puck, the at least one shear puck including a shear puck protrusion; wherein the shear puck protrusion of each of the at least one shear pucks is disposed within a respective one of each of the at least one main case apertures.

Abstract: A rotor stage (100) of a gas turbine engine (10) comprises a platform (120) from which rotor blades extend. The platform is provided with a circumferentially extending damper ring (200), the damper ring having an engagement surface (210) that engages with a platform engagement surface (110) of the platform (120). In use, the damper engagement surface (210) and the platform engagement surface (110) move relative to each other in a radial direction, in response to diametral mode excitation. This causes friction between the two surfaces, thereby dissipating energy and damping the excitation. The rotor stage (100) is arranged such that the engagement load between the damper engagement surface (210) and the platform engagement surface (110) is a function of the rotational speed of the rotor stage (100).

Abstract: An actuation arrangement for effecting actuation of a variable stator vane pivotally mounted on a tubular casing. The actuation arrangement includes: an actuator connector connected to the variable stator vane via an actuating lever; an anchor fixedly mounted relative to the circumference of the tubular casing; an actuator; and a belt extending from the actuator to the fixed pulley. The actuation arrangement further includes a movable pulley movable relative to the tubular casing and connected to the actuator connector. The belt has a loop portion provided between the proximal and distal ends which loops around the movable pulley, the loop portion for transferring forces generated in the belt by the actuator to the movable pulley to effect movement of the movable pulley and actuator connector towards the anchor to effect actuation of the variable stator vane via the actuating lever.

Abstract: A turbine nozzle includes an arcuate inner band having opposed flowpath and back sides, and an aft flange extending outward from the back side; an arcuate outer band having opposed flowpath and back sides; an airfoil-shaped turbine vane extending between the flowpath sides of the inner and outer bands, wherein the inner and outer bands and the vane comprise a ceramic low-ductility material; and a metallic collar surrounding the aft flange.

Abstract: A heat shield for a mid-turbine frame has a conical body, including at least one axial retention feature, at least one circumferential retention feature, and at least one radial retention feature.

Abstract: A modular panel for covering a portion of a structure and directing air impacting against the structure into a common path to harness wind energy includes a rear side that is adapted for mounting with the structure and a front side having a plurality of apertures therethrough. At least one central conduit leads from an inlet port on a first edge of the modular panel to an outlet port on a second edge of the modular panel. A plurality of branch conduits are each fixed between one of the plurality of apertures and the at least one central conduit. At least one of the modular panels affixed to the structure further preferably includes a wind turbine within the panel and along the central conduit. The wind turbine is adapted for receiving air from the central conduit and each branch conduit for spinning the wind turbine to produce electricity.

Abstract: A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.

Abstract: A centrifugal compressor assembly for use in a turbine engine is provided. The assembly includes an impeller that includes a plurality of rotor blades. The assembly also includes a stationary assembly circumscribing the impeller such that a clearance is defined therebetween. The stationary assembly includes at least one articulating seal member positioned adjacent the plurality of rotor blades, and a biasing mechanism configured to cause the at least one articulating seal member to selectively translate relative to the plurality of rotor blades based on an operating condition of the turbine engine.

Abstract: The present application relates to an axial turbomachine housing designed to channel a primary annular flow in the low-pressure compressor of the said turbomachine. The housing comprises a first shell and a second shell designed to be contiguous and coaxial. The first shell comprises a flange and a centering surface substantially cylindrical. The second shell comprises a flange and radial centering member designed to mate with the centering surface. The flange of the first shell includes cut-outs distributed along its circumference, and the centering member extends axially from the flange of the second shell through the said cut-outs to the centering surface where the two flanges are in contact.

Abstract: A component of a turbine is disclosed. The component includes an carrier segment having a rail, an frame segment including a hanger having a flange supported on the rail of the carrier segment, and an inner surface having a section of a track for a turbine blade defined therein. The component also includes a retainer segment secured to the carrier segment such that the hanger is secured between the retainer segment and the carrier segment.

Abstract: Vertical axis wind turbines are provided having foil design and geometry that facilitates lift, torque and laminar flow along a 360 degree radial. Contemplated foils are non-planar, and have a chord length that is at least three times greater than a distance between a trailing end of a leading foil, and a leading end of a trailing foil. Additionally or alternatively, the foils are located away from a turbine axis at a distance that is about 2.9-3.5 times greater than a chord length of the foils. In some embodiments, the foils are circumferentially distributed via one or more laminar stall vanes.

Abstract: The present disclosure relates to combustor configurations, panels and components for a gas turbine engine. In one embodiment, a combustor for a gas turbine engine includes a support structure including a plurality of openings and a plurality of panels mounted to the structure. The plurality of panels define a combustion cavity of the combustor. Each panel includes a first wall configured to receive cooling air and a second wall configured to provide air flow for the cavity. The first and second walls form a cavity and include one or more elements for controlling the cooling effectiveness of each panel. Another embodiment is directed to a combustor panel including one or more elements for controlling cooling effectiveness. Another embodiment is directed to a support structure for a combustor of a gas turbine engine. Another embodiment is directed to configurations of panels including single walled portions or single walled panels.

Abstract: A multistage centrifugal pump includes a foot part (1) and a head part (7), between which several pump stages are arranged. Each of the pump stages includes an impeller (4) and a housing (5) surrounding the impeller (4). The housings (5) are arranged over one another. The housings (5) together with an outer casing (9) form an annular channel (8). The housings (5) together with an outer casing (9) are clamped via clamping bolts (11) which are fastened on the head part (7) and the foot part (1). The clamping bolts (11) are arranged within the annular channel (8).