Abstract: A silencer duct that may be part of, for example, a turbomachine inlet and may include a duct body, and a silencer element extending axially through the duct body. A first portion of a coupler may extend axially from a first side of the duct body. A second portion of a coupler may extend axially from a second side of the duct body. At least one of the first portion of the coupler and the second portion of the coupler are configured to couple to at least one of an adjacent silencer duct and an inlet.

Abstract: The present application concerns a test engine hood for a turbine engine, such as a double flow turbine. The test hood allows replacement of a flight engine hood during tests on a test bench on the ground where the temperature conditions could damage the flight hood. The test hood includes a tubular wall of carbon-fiber epoxy composite, and metal flanges upstream and downstream. To provide thermal protection, the test hood includes a layer of silicone with a majority of polysiloxane. The layer covers the entire inner surface of the wall to create a barrier. The present application also concerns a method for testing a turbine engine on a test bench, where the turbine engine is fitted with a test casing. The present application also concerns a use of silicone for thermal insulation of the inside of the test hood of the turbine engine on a test bench on the ground.

Abstract: A rotor stage of a gas turbine engine includes a platform from which rotor blades extend. The platform is provided with a circumferentially extending damper ring, the damper ring having an engagement surface that engages with the platform. The damper ring provides damping through slip between the engagement surface and the platform. The damper ring has a hoop stress that results in a load being provided to the platform from the engagement surface. The load can be optimized in order to provide improved damping.

Abstract: The impeller includes a blade formed either entirely or partially from fiber reinforced plastic, a boss member that supports the blade, a plate that presses a root portion of the blade against the boss member; and a fastening portion that fastens the boss member to the plate, wherein the root portion of the blade has an undercut shape, the boss member has an excavated portion, the excavated portion is shaped identically to all or a part of the undercut shape or shaped such that a gap is formed between the excavated shape and all or a part of the undercut shape, and the root portion of the blade is fastened by a fastening force via the boss portion and the plate in a condition where a clearance is provided between the boss member and the plate.

Abstract: The invention concerns a method of operating a wind power installation in which the rotor is brought to a halt and fixed, comprising the steps: braking the rotor, positioning the rotor at a stopped position, and fixing the rotor in the stopped position. According to the invention it is provided that an end position is predetermined, the rotor is braked in regulated fashion to a stopped position associated with the end position, and for positioning for the predetermined end position the rotor is braked in an automated procedure until stopped at the stopped position, and for fixing in the stopped position a mechanical fixing device is applied, in particular automatically.

Abstract: A turbocharger (10) including variable turbine geometry has a turbine wheel (24) with a turbine axis of rotation (R1) that extends in an axial direction. The turbocharger (10) also has a plurality of guide vanes (34) that is selectively movable between a range of angular positions. Each one of the guide vanes (34) is supported for pivotal movement about a guide vane axis of rotation (R2) and each guide vane axis of rotation (R2) is non-parallel to the turbine axis of rotation (R1).

Abstract: Systems and methods for reducing friction during gas turbine engine assembly may comprise, a rear hub which may comprise a conical web, a horizontal arm coupled to the conical web, and/or a hub kickstand coupled to the conical web. The conical web, horizontal arm, and/or hub kickstand may converge at a pivot point. The hub kickstand may be removably coupled to the tie shaft.

Abstract: A gas turbine engine component has an airfoil extending radially inwardly of an outer platform to an inner platform. A central passage is formed within the airfoil and has an inlet end for receiving cooling air. An outlet end in the inner platform delivers cooling air to a downstream use. The airfoil has a suction wall and a pressure wall, and extends in an axial direction from a leading edge to a trailing edge. A suction skin core is between the central passage and the suction wall. A pressure skin core is between the central passage and the pressure wall.

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil body defining a cavity, and a baffle including a baffle body including sidewalls and defining an internal passage for conveying coolant. The baffle body is situated in the cavity such that a majority of external surfaces of the sidewalls abut the cavity.

Abstract: An adapter structure for a ventilating fan, including an adapter having an air inlet; an air guide structure having an air inlet, and a mounting structure for mounting the air guide structure within the adapter. The mounting structure includes a first portion provided at an outer side of a flange of the air inlet of the air guide structure and a second portion provided at an inner side of the adapter so that the mounting structure is positioned between the air inlet of the air guide structure and the air inlet of the adapter. With the adapter structure for a ventilating fan according to the present invention, the airflow amount is prevented from being reduced, and noise is reduced.

Abstract: A wind energy generation turbine is built to take advantage of high winds in mountain passes and other areas of extreme wind velocity. A windmill section is raised high by support structures. Electricity generators are kept in the base of the windmill to reduce elevated weight. A nozzle or shroud channels wind into a narrow raceway to take advantage of the Venturi effect. Windmill blade tips housed within a circular raceway are strengthened by blade tip connectors and blade spar struts against high wind forces. Windmill blade angle and windmill wind facing are dynamically altered by computerized motors for maximum efficiency. Windmill blade angle and/or generator load maintain ratio of windmill blade tip speed to wind speed for efficiency. Turbine speed translation gears are able to decouple windmill from 60 Hz cycle or use water pumps and gravity to store energy at peak generation times.

Abstract: A ventilation fan comprises a fan, a cover module and a filter. The fan includes an inlet and an outlet. The cover module is disposed at the inlet and includes a main body and a cover. The main body includes an opening and fixing portions. The opening is disposed corresponding to the inlet. The periphery of the opening is configured with two opposite slideways. The fixing portions are disposed on the main body. The cover and the main body are disposed separately to form a gap and the cover includes connecting portions correspondingly connected to the fixing portions. The filter detachably slides on the slideways to be disposed at the opening. The size of the cover is larger than that of the opening. The air flows to the filter and inlet through the gap and flows out of the outlet through the fan.

Abstract: A rotor-stator assembly for a gas turbine engine, the assembly including a rotor having a layer of ceramic material forming an abrasive coating deposited on its tip, the layer being constituted mainly by zirconia and possessing a void ratio less than or equal to 15%, and a stator arranged around the rotor and provided facing the tip of the rotor with a layer of ceramic material forming an abradable coating, the layer being constituted mainly by zirconia possessing a void ratio lying in the range 20% to 50% with pores having size less than or equal to 50 ?m.

Abstract: A propeller blade mounting system includes a mounting system (4) on rolling bearings between a propeller hub (3) and a propeller blade (2), wherein: at least one bearing outer ring (9) is connected in rotationally fixed manner to the propeller blade (2); at least one bearing inner ring (15, 16, 17) is mounted on the propeller hub (3); a sleeve-shaped central section (13) connected to the propeller blade (2) is disposed radially inside the bearing inner ring (15, 16, 17); and a lubricant chamber (18) is formed between the bearing outer ring (9) and the central section (13) in the radial direction, relative to the rotational axis (R) of the propeller hub (3), and is closed towards the exterior.

Abstract: The invention relates to a wind energy plant with a nacelle, a generator located in the nacelle, a tower and a yaw bearing to adjust the nacelle orientation into the wind, such that the yaw bearing is located under the nacelle in a vertical yaw displacement and the nacelle is supported on the yaw bearing above a vertical shaft section of the same length as the yaw displacement.

Abstract: A device for protecting against oil leaks towards the rotors of a turbomachine turbine includes an upstream cavity in which an oil/air mixture can circulate, the upstream cavity being delimited downstream by a journal of the turbine rotor and on the outside by a sealing flange of the journal extending axially in an upstream direction, a downstream cavity opening towards the discs of the turbine and communicating with the upstream cavity via a plurality of ventilation holes provided in the journal, and an upstream annular deflector fixed to the sealing flange of the journal and extending radially inwards towards the ventilation holes The upstream deflector has oil passage ports provided at the end of same secured to the sealing flange of the journal.

Abstract: A nacelle of a turbine engine includes an external cowling, an internal cowling, and a heat exchanger associated with at least one circulation duct for a fluid. In particular, the circulation duct forms a recirculation loop through the heat exchanger, and the recirculation loop includes at least one circulation area extending at least partially along the external cowling in contact with a wall of the external cowling so as to allow exchange of heat by conduction with the air outside the nacelle.

Abstract: A rotor system lock for a gas turbine engine is described which blocks movement of rotating wheel assemblies relative to static vane assemblies in a gas turbine engine in order to block unintended rotation (or windmilling) of the gas turbine engine when it is exposed to high winds while at rest or to ram air during pre-launch flight and thereby avoid damage to components of the engine.