Abstract: The invention relates to a turbine engine comprising an air compression stage comprising at least one movable compressor wheel, an air inlet duct coupled to said air compression stage, a first sealing device, which is arranged between a front portion of the movable compressor wheel and the air inlet duct and comprising at least one seal, a channel for conveying the air compressed by the movable wheel and a second sealing device, which is arranged between a rear portion of the movable compressor wheel and the conveying channel and is configured to receive an airflow coming from the conveying channel, the turbine engine being remarkable in that the second sealing device is configured to allow some of the air passing therethrough to be bled and in that the bleed air is conveyed to the seal of the first sealing device so as to keep it under pressure.

Abstract: In order to reduce the risks of movable nacelle cowlings opening, the invention provides a nacelle for an aircraft engine assembly comprising a fixed nacelle structure as well as at least one jointed movable cowling on the fixed structure, the cowling being jointed at its front end on the fixed structure so that, upon closing the movable cowling, a rear end of this cowling moves towards the rear and radially towards the inside.

Abstract: An exemplary carbon seal assembly generally may include a stator fixable to a static component, such as a mechanical housing of a gas turbine engine, and a rotor fixable to a rotating component, such as a shaft of the gas turbine engine, where the rotating component is rotatable relative to the static component. The carbon seal assembly may also include a carbon ring and a spring attached thereto positioned between the stator and the rotor, where the spring may be configured to move the carbon ring fore and aft between the stator and the rotor. The carbon seal assembly may further include a diaphragm operatively attached to stator and to the carbon ring and spring combination.

Abstract: An assembly for a gas turbine engine includes a minidisk that includes an axial extension extending from a disc. The axial extension includes an inner diameter surface and a recess arranged radially opposite the inner diameter surface. The recess provides a radially outwardly extending flange and a bumper extending radially inward from and proud of the inner diameter surface. A method of working on a gas turbine engine section includes inserting a tool into a cavity beneath a seal assembly, and engaging a flange of a minidisk with the tool to manipulate first and second rotors with respect to one another.

Abstract: The present invention relates to an assembly comprising a duct, preferably a turbine duct, and at least one segment formed of at least two rigid shells, each shell comprising at least one fixing orifice for fixing to the duct and at least one fixing element at least one boss per shell which boss is fixed to the duct and against which boss the shell rests, such that at least one orifice and one boss face one another, and that the fixing element passes through the orifice facing the boss and is fixed to the boss.

Abstract: A wind turbine rotor blade has a blade root, a lightning protection conductor for dissipating a lightning current toward the blade root, a suction side, a pressure side, a lightning receptor arranged on the suction side, a lightning receptor arranged on the pressure side, and an integrally formed lightning receptor base, which is arranged in the wind turbine rotor blade and on which the two lightning receptors and the lightning protection conductor are fastened, wherein the lightning receptor base includes two fastening rings, which each have an internal thread, into which one of the two lightning receptors is screwed, and an outer diameter and an outer side, wherein the outer sides of the fastening rings are arranged with a spacing of less than one outer diameter from one another.

Abstract: A system and method are provided for controlling turbine blade tip-to-static structure clearance in a gas turbine engine installed on an aircraft. Mode control data are processed to determine that a fuel-saving mode is enabled, and aircraft data are processed to determine that the aircraft gas turbine engine is generating a substantially constant thrust. The turbine blade tip-to-static structure clearance in the aircraft gas turbine engine is minimized upon determining that both the aircraft gas turbine engine is generating a substantially constant thrust and the fuel-saving mode is enabled. The turbine blade tip-to-static structure clearance in the aircraft gas turbine engine is then selectively increased to a predetermined clearance, and a change in aircraft gas turbine engine thrust is prevented until the predetermined clearance is achieved.

Abstract: A heat sink that can be positioned around a rotating shaft includes a cylindrical body with a first end and a second end, a bore running through the body with a first opening at the first end of the body and a second opening at the second end of the body, fins extending radially outward from the body and running from the first end to the second end of the body, and channels defined between the fins and running from the first end to the second end of the body.

Abstract: A vacuum pump has an exhaust portion in which rotating blade portions and stationary blade portions are laminated in multiple stages. Each of the plurality of stator blades in one stage of the stationary blade portion is three-dimensionally connected to the stationary blade portion main body by an inner circumferential side support portion on the inner circumferential end side, and three-dimensionally connected to the stationary blade portion main body by an outer circumferential side support portion on the outer circumferential end side, and a cutout is provided in ag circumferential front end of the outer circumferential side support portion.

Abstract: A method for monitoring the operation of a wind energy plant having at least one blade angle adjustable rotor blade. Rotor blade vibrations are registered during operation by at least one measuring device, and at least one current natural frequency is established from the registered vibrations. At least one environmental parameter and/or at least one operational parameter, which influence the natural frequency of the rotor blade, is or are additionally registered. At least one natural frequency expected value dependent on the additionally registered parameter(s) and at least one confidence interval are calculated for the at least one established current natural frequency of the rotor blade, and whether the established current natural frequency lies within, or outside of, the confidence interval around the natural frequency expected value is monitored. Also disclosed is an operational control apparatus of a wind energy plant and a corresponding wind energy plant.

Abstract: A gas turbine engine system comprises a rotor wheel, a plurality of blades, a lockwire and a locking key. The rotor wheel comprises a plurality of axial grooves extending through a periphery of the rotor wheel, and a plurality of posts formed between adjacent slots, each post having a circumferential slot. The blades are mounted in the axial grooves of the rotor wheel, each blade having a circumferential slot circumferentially aligned with the circumferential slots of the posts. The lockwire extends across the plurality of axial grooves of the rotor wheel within each of the circumferential slots of the posts and the blades from a first end to a second end to inhibit axial displacement of the blades within the grooves. The locking key is disposed between the first and second ends of the lockwire and provides support to at least one of the ends of the lockwire to prevent radially inward displacement.

Abstract: A plurality of guide vanes (34) in a variable turbine geometry turbocharger (10) regulates a flow of exhaust gas. The guide vanes (34) are selectively adjustable between an open position to allow the flow of exhaust gas to drive a turbine wheel (24) and a closed position to block the flow of exhaust gas. A first flow feature (58) is disposed on first (44) and second (46) edges of the guide vanes (34) to disturb the flow of exhaust gas to prevent leakage of exhaust gas around the first (44) and second (46) edges. A second flow feature (64) is disposed on front (60) and rear (62) surfaces of the guide vanes (34) to channel the flow of exhaust gas between adjacent guide vanes (34) when the guide vanes (34) are in the open position to prevent swirling and/or cross flow of the exhaust gas.

Abstract: A ceiling fan system wherein the motor of the ceiling fan is housed between the ceiling and the roof of an enclosure within which the ceiling fan is to be used, thereby disposing the motor out of view of occupants within the enclosure where the ceiling fan is being used.

Abstract: A device for deicing a separator nose of an aviation turbine engine, and including a separator nose for positioning downstream from a fan of the engine to separate annular channels for passing a primary stream and a secondary stream coming from the engine, and a casing fastened to the separator nose so as to extend it downstream, the casing having an inner shroud defining the outside of the primary stream flow passage, and including at least one air duct incorporated in the inner shroud so as to be formed integrally therewith, the air duct opening out downstream to an air feed and opening out upstream into the inside of the separator nose.

Abstract: An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas flow and a cooling surface facing a cooling fluid flow. A film hole extends through the substrate to an outlet on the hot surface. A flow conditioning structure is provided upstream of the outlet.

Abstract: A system for directing the flow of a fluid and controlling the rate of flow of the fluid. The system comprises a channel for directing the flow of the fluid; at least a pair of articulating vanes positioned within the channel for controlling the flow rate of the fluid within the channel; and a linkage between the vanes coupling the articulation of each of the vanes to the other of the vanes, wherein each vane imparts a force on the linkage when the relative angle of attack is greater than zero, wherein the force imparted on the linkage by one of the vanes is at least partially cancelled by the force imparted on the linkage by the other of the vanes during the articulation of the vanes.

Abstract: A thermally driven spring valve for turbine gas path parts is disclosed herein. A thermally driven spring valve includes a bimetallic sheet comprising a base, a first finger portion extending from the base and a second finger portion extending from the base, the first finger portion having a first curvature vector and the second finger portion have a second curvature vector, wherein an exterior surface extends from the base through the first finger portion and the second finger portion and an interior surface extends from the base through the first finger portion and the second finger portion, wherein the exterior surface of the first finger portion is disposed proximate the interior surface of the base wherein the exterior surface of the second finger portion is disposed proximate the interior surface of the base. A thermally driven spring valve may include perforations through a finger portion.

Abstract: A fan design method and fan structure is described, enabling independent control of the volume of airflow and the amount of noise produced. The noise produced is a close approximation to a pleasing red noise spectrum, and is generated solely by the interaction of the rotating fan blades with a petal assembly or a fan enclosure in several embodiments. A petal assembly may be positioned at varying spacings behind the rotating fan blades to control the level of noise production with minimal effect on the volume of airflow. Various aspects of the fan blade configuration, such as the blade pitch, camber, span, chord, etc., may be manipulated to control the ratio of airflow volume to the amount of noise produced.

Abstract: A compressor includes a rotor platform; a rotor blade; and a casing having an inner surface surrounding the tip and spaced radially outwardly from the tip to define a gap. A secondary air flow system includes a bleed inlet configured to remove secondary air flow from the primary air flow; an injection opening disposed in the inner surface of the casing upstream of the bleed inlet; an accessory conduit; and a plenum fluidly coupled to the bleed inlet, the injection opening, and the accessory conduit. The bleed inlet and plenum at least partially define a secondary air flow path such that a first portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the injection opening and a second portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the accessory conduit.

Abstract: A component for a turbocharger can include a shaft made of a first material where the shaft includes a turbine wheel end and a shaft axis; a turbine wheel made of a second material where the turbine wheel includes a shaft end and a turbine wheel axis; a weld joint formed by solidification of at least a portion of a weld pool that includes the first material and the second material, where the weld joint joins the turbine wheel end of the shaft and the shaft end of the turbine wheel and where the weld joint includes an inner radial border and an outer radial border; a reservoir disposed radially inwardly of the inner radial border of the weld joint; and a solidified portion of the weld pool disposed in the reservoir. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.