Abstract: An exhaust duct for an engine includes an outer exhaust duct and a nested exhaust duct capable of having at least two configurations. The nested exhaust duct is circumferentially surrounded by the outer exhaust duct for a first length of the nested exhaust duct in a first configuration. The nested exhaust duct is circumferentially surrounded by the outer exhaust duct for a second length of the nested exhaust duct in a second configuration, which is less than the first length.

Abstract: A wind turbine system and to a method for operating said system is disclosed. The system further comprises a detection device configured for detecting body waves generated by an earthquake. In one aspect, the present disclosure is directed to a system comprising a wind turbine, in particular to an onshore erected wind turbine, a wind turbine controller for controlling the wind turbine, and at least one detection device, which is connected to the wind turbine controller for transmitting signals. The wind turbine includes at least a rotor having at least one rotor blade, wherein the rotor is rotatably mounted to rotation support means of the wind turbine, and a tower having a top end for supporting the rotation support means and a support end. The detection device is configured to detect and measure earthquake generated primary waves (P-waves). The detection device may include at least one sensor or a plurality of sensors, wherein the sender is configured to detect and/or measure earthquake generated P-waves.

Abstract: A fluid flow distributor includes a manifold body having a first chamber configured to receive the supply of coating gas. A pair of inlet nozzles protrude from an upper surface of the manifold body for insertion into a turbine blade for delivering the coating gas to the internal cavities of the turbine blade. The inlet nozzles may be tapered to facilitate insertion of the inlet nozzles into a root portion of the turbine blade. The fluid flow distributor may have a geometry that promotes laminar flow of the coating gas.

Abstract: A stator part of a turbomachine includes a platform, a blade, and a fin. The blade and the fin extend from the platform. The platform, an extrados of the blade and the fin define therebetween a gas flow channel. The channel has a section in a plane normal to an axis of the turbomachine, the section having a surface area, the surface area continuously decreasing from upstream to downstream with reference to a general gas flow direction through the turbomachine.

Abstract: A wind turbine monitoring device for monitoring a wind turbine including a lightning sensor for detecting a lightning strike on a wind turbine blade includes a lightning parameter acquisition part configured to acquire at least one lightning parameter based on an output of the lightning sensor, a lightning level determination part configured to determine a level of the lightning strike based on the at least one lightning parameter acquired by the lightning parameter acquisition part; and an inspection control part configured to judge whether it is necessary to automatically inspect the wind turbine blade by at least one inspection unit for inspecting the wind turbine blade, according the level of the lightning strike determined by the lightning level determination part.

Abstract: Rotor blade (20) to be arranged in a gas conduit (3) of a turbomachine (1), having a rotor blade airfoil (23), which radially inwardly has a chord length Si, radially outwardly has a chord length Sa, and in a radial position rx inbetween has a chord length Sx, the chord length Sx in the radial position rx being at least equal to the chord length Si radially inwardly (Si<Sx), and the chord length Sa radially outwardly corresponding at most 0.9 times the chord length Sx in the radial position rx inbetween (Sa<0.9 Sx).

Abstract: A composite blade assembly for a turbine engine. The composite blade assembly having a core, a first skin and a second skin. The core having a composite structure. The first skin having at least one composite ply. The second skin having at least one composite ply. The first skin having a first radius. The second skin having a second radius.

Abstract: A sensor system for a turbomachine having an axis is disclosed. The sensor system includes a mounting member including a body configured to be mounted to a circumferential slot defined in at least a circumferential portion of a circumferential interior surface of a casing of the turbomachine. A plurality of sensors is coupled to the mounting member and configured to measure an operational parameter of the turbomachine.

Abstract: The present disclosure relates to a spar cap (10) for a wind turbine blade (1000) comprising: a plurality of spar cap layers (20) and a first interlayer (30) arranged between the first spar cap layer (20a) and the second spar cap layer (20b) and comprising: a number of first interlayer areas (31), including a first primary interlayer area (31a), comprising a first number of interlayer sheets (33) comprising a first plurality of fibres (35); and a number of second interlayer areas (32), including a second primary interlayer area (32a), comprising a second number of interlayer sheets (34) comprising a second plurality of fibres (36), wherein the first number of interlayer sheets (33) is of a different characteristic than the second number of interlayer sheets (34).

Abstract: A system for changing the pitch of the blades of a turbomachine propeller, each blade being mounted so as to pivot about a pitch axis, the system including a control means and a connection mechanism connecting the control means to each blade of the propeller, the connection mechanism including, for each blade of the propeller: —a connecting rod having a first end connected to the control means; and —an eccentric having a first end connected to the blade in order to rotate same about its pitch axis and a second end forming a yoke connected to a second end of the connecting rod by a pivot connection; the yoke of the eccentric being oriented towards the pitch axis of the blade.

Abstract: A segmented wind turbine blade comprises a first blade segment and a second blade segment connected to the first blade segment by means of male spar part protruding from the second blade segment and received in the cavity of a female spar part of the first blade segment. The first blade segment comprises a spar cap bonded to an inner surface of a shell portion of the first blade segment. The spar cap comprises a longitudinally extending scarf connection between a first spar cap portion made from pultrusions and a second spar cap portion being bonded to an outer surface of the female spar part, wherein the longitudinally extending scarf connection is spaced from, adjoins or partially overlaps the longitudinal inner end of the female spar part in the longitudinal direction of the blade.

Abstract: An additive manufactured rotor for a seal assembly is provided. The rotor surrounds a central axis and extends along the central axis from a first axial end to an opposite second axial end. The rotor is rotatable about an axis of rotation that is co-axial with the central axis. The rotor can include an outer ring and an inner ring that is connected to the outer ring by a radial web. The outer ring has a rotor face for providing a sealing surface at the first axial end. The outer ring can define a first annular cavity and the inner ring can define a second annular cavity that is radially separated from the first annular cavity. The radial web can define a fluid channel for providing fluid communication between the first annular cavity of the outer ring and the second annular cavity of the inner ring.

Abstract: Partition damper seal configurations for segmented internal cooling hardware apparatus are disclosed. An example airfoil includes an outer wall having a first rib spaced apart from a second rib on a surface of the outer wall, and an inner wall surrounded by the outer wall, the inner wall having a third rib protruding from the inner wall towards the surface of the outer wall, an end of the third rib detachably coupled to a portion of the surface of the outer wall, the portion of the surface positioned between the first rib and the second rib, the third rib and at least one of the first rib or the second rib to at least partially seal a flow passage between the inner and outer walls.

Abstract: An integrally bladed rotor for an aircraft engine includes a hub and a circumferential array of blades extending from the hub. Each blade has an airfoil extending from a gaspath side of a platform provided at a periphery of the hub. The platform has a radial thickness T. An edge of the airfoil is disposed at an axial distance L1 from an adjacent axial edge of the platform. A projection extends radially inwardly from an interior side of the platform opposite to the gaspath side. The projection has an axial thickness t, a radial height h from the interior side of the platform, and an axial distance L2 from the adjacent axial edge of the platform. T is a radial thickness of the platform at an axial location of the projection, and 0 . 2 ? T t ? 5 ; 1 ? h t ? 10 ; and ? 0 ? L 2 L 1 ? 1 ? 0 .

Abstract: This stationary turbine blade comprises: a stationary blade main body extending in the radial direction intersecting the flow direction of steam; a hydrophilic region which is formed on the surface of the stationary blade main body and which has a higher hydrophilicity than the other parts and has the radial dimension gradually increasing toward the downstream side in the flow direction; and a collecting portion which is provided on the downstream side of the hydrophilic region and which collects a liquid film flowing along the hydrophilic region.

Abstract: A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, or Table IX. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.

Abstract: A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of TABLE I and TABLE II. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values being joined smoothly with one another to form a complete airfoil shape.

Abstract: An unducted airfoil assembly includes an airfoil having spaced-apart pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced apart leading and trailing edges. The airfoil defines a forward-most axial point and is arranged around a longitudinal axis and rotates about the longitudinal axis in a rotational direction. A tip leading edge of the airfoil is circumferentially offset in a direction opposite the rotational direction relative to a circumferential location of the forward-most axial point.

Abstract: An aircraft system is provided that includes a gas turbine engine, a gearbox and at least one compressor. The gas turbine engine includes a compressor section, a turbine section, a combustor section and a rotating structure. The combustor section is fluidly coupled with and between the compressor section and the turbine section. The rotating structure includes a compressor section rotor within the compressor section and a turbine section rotor within the turbine section. The at least one compressor includes a compressor rotor rotatably driven by the rotating structure through the gearbox. The gas turbine engine may be dedicated to powering the at least one compressor.

Abstract: An aircraft propulsion system includes a bladed rotor configured for rotation about a rotational axis. A rotor blade of the bladed rotor of rotor blades includes a blade body. The blade body has a blade span extending between and to a base end and a tip end. The blade body has a blade chord extending between and to a leading edge and a trailing edge. The blade body forms a pressure side surface and a suction side surface. The blade body forms a recess at the pressure side surface. The recess includes a recess surface portion forming a portion of the pressure side surface. The recess surface portion has a recess height. The recess height is greater than or equal to a Y-value of 0.025 for a normalized two-dimensional curve of a surface profile of the recess surface portion taken along a Y-Z plane orthogonal to the rotational axis for a recess span.