Abstract: A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.

Abstract: An airfoil cooling structure, an airfoil having the airfoil cooling structure, and a turbine blade/vane element including the airfoil are disclosed. The airfoil cooling structure includes a cooling path formed inside the airfoil and having a first surface and a second surface opposite to the first surface, and an additive manufactured (AM) feature disposed in the cooling path, manufactured by additive manufacturing, and including a plurality of column parts intersecting with each other so as to abut against the first surface and the second surface.

Abstract: The present invention concerns an adjustment mechanism (200) for variable adjustment of an inlet cross-section (321) of a compressor inlet (322). The adjustment mechanism comprises a plurality of rotatably mounted baffle elements (210) which are arranged in a circumferential direction (26) and are adjustable between a first position and a second position. At least one baffle element (210) of the plurality of baffle elements (210) comprises an eddy-reducing feature (220).

Abstract: A marine vessel propeller to convert engine rotational power into propulsive thrust is of a built-up propeller (BUP) type having a circular array of propeller blades, wherein each propeller blade is a single piece including a blade part and a base part. The base part has a generally circular inner surface with a number of radially extending cylindrical indents provided with planar end wall and fastening holes arranged through the base part at a location of the indents. A cylindrical insert is provided with a hole parallel to a longitudinal axis of the insert and arranged to fit into the indent, such that the propeller blades are attachable to a propeller shaft using exemplary fastening bolts through the fastening holes and inserts. A propeller blade and method for installing a marine vessel propeller are also disclosed.

Abstract: A fan case assembly adapted for use with a gas turbine engine includes a fan track liner and an annular case. The fan track liner extends circumferentially at least partway about a central axis of the gas turbine engine. The annular case is configured to support the fan track liner at a radial position relative to the central axis. The fan case assembly further includes an air recirculation duct configured to redirect air around the fan track liner.

Abstract: A wind turbine blade comprising a blade shell that extends in a spanwise direction from a root end of the blade to a tip end of the blade, the blade shell defining an internal blade volume within which at least one blade feature is located, the blade being provided with an RF position-identification means configured for detection by an RF detection means external to the blade to enable determination of a reference position for the blade and/or the blade feature. Aspects of the invention also relate to a method of detecting a reference position for a wind turbine blade.

Abstract: Systems and methods for a turbo blanket. Specifically, embodiments are related to a flexible turbo blanket with an alloy layer, insulation layer, and mesh screen layer.

Abstract: A replaceable rotor blade tip clearance measurement device for a gas turbine engine, includes a threaded section along an axis and an integral abradable tip with an internal lattice geometry that extends from the threaded section along the axis.

Abstract: An arrangement reduces oscillation (vibration) of an oscillatory structure. The arrangement has a structure having at least one mode in at least one direction; and an oscillation-reducing device (vibration-reducing device). The oscillation-reducing devices has a housing formed by or provided on the structure, a cavity, and a body configured for making impact contacts with the housing and disposed in the cavity in such a manner that the body is configured to make impact contacts with the housing at least temporarily for as long as the structure is excited in the at least one mode in the at least on direction.

Abstract: In one exemplary embodiment of the present disclosure an airfoil is provided. The airfoil defines a spanwise direction, a root end, and a tip end. The airfoil includes: a body defining a pressure side and a suction side and extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a spar enclosed in the body of the airfoil extending along the spanwise direction, the spar comprising a plurality of spar segments arranged in an overlapping configuration along the spanwise direction.

Abstract: The invention relates to a turbomachine rotary-fan blade having a predetermined breaking zone, which extends from the upstream edge along a given length and from the blade-tip edge over a given height. According to the invention, the body is made of a composite material comprising a fibre reinforcement obtained by three-dimensional weaving of warp and weft strands, and a resin matrix in which the fibre reinforcement is embedded, and has, in or in the vicinity of the zone, a discontinuity of at least some of the strands, configured such that the zone partially detaches when there is tangential friction in the thickness direction against the blade-tip edge, the height being less than 3% of the aerodynamic stream height of the blade.

Abstract: Dual function links for gas turbine engine mounts are disclosed. An example apparatus for mounting a casing of a gas turbine engine to a pylon, the apparatus includes a first pin and a linkage including a first linkage portion including the first pin, a second linkage portion, the second linkage portion forming a first load path between the gas turbine engine and the pylon, the second linkage portion arranged with respect to the first linkage portion such that a gap prevents the first linkage portion from forming a second load path between the gas turbine engine and the pylon.

Abstract: A bearing assembly installed within a turbocharger housing between a turbine wheel and a compressor impeller mounted for rotation together on a turbocharger shaft may include a journal bearing disposed on a corresponding portion of the turbocharger shaft, a thrust bearing having a thrust bearing surface, and a bearing carrier. The bearing carrier may include a carrier body, a carrier body bore extending axially through the carrier body and receiving the journal bearing therein, and a thrust bearing seat on the exterior of the carrier body facing the turbine wheel. The thrust bearing seat may have a complimentary shape to the thrust bearing surface of the thrust bearing, the thrust bearing disposed between the carrier body and the turbine wheel and engaging the thrust bearing seat. The bearing assembly may further include an anti-thrust bearing surface facing the compressor impeller, and an anti-thrust bearing mounted to the anti-thrust bearing surface.

Abstract: Provided is a seal arranged about a tower aperture of a wind turbine nacelle, which seal includes an annular channel shaped to contain a liquid, and an annular lip extending downwards into the annular channel, which annular channel and annular lip are mounted at opposite sides of a gap between the nacelle and a wind turbine tower; and further including a volume of liquid in the annular channel, which liquid volume is sufficient to immerse the annular lip about its lower circumference to prevent a passage of air between nacelle interior and nacelle exterior. A seal maintenance arrangement including such a seal and a device for replenishing the liquid in the annular channel is also provided.

Abstract: An assembly for a gas turbine engine according to an aspect of the present disclosure includes a metallic damper including a first contact surface and a gas turbine engine component. The gas turbine engine component includes a main body extending in a first direction between a gaspath surface and a second contact surface. The first and second contact surfaces oppose each other along an interface extending in a second direction. The first and second contact surfaces are dimensioned to contact each other along the interface in a hot assembly state. The main body is established by a composite including fibers in a matrix material. At least some of the fibers are arranged to establish a plurality of cooling passages aligned with the interface relative to the second direction. A method of damping for a gas turbine engine is also disclosed.

Abstract: A heat shield assembly adapted for use with gas turbine engines, airframes, and aircraft includes a carrier and a heat-shield tile. The carrier is adapted to couple to the gas turbine engine, airframe, or aircraft. The heat-shield tile includes material different than the carrier and is arranged to cover the carrier to protect the carrier from high-temperature gases surrounding the heat shield assembly.

Abstract: A ceramic matrix composite blade includes a central core surrounded by an outer profile, the central core comprising layers of unidirectional layup having two dimension and three dimension fiber weaves; the outer profile comprises a biased weave layup that radiates toward a leading edge and a trailing edge of the blade; wherein the biased weave layup includes fibers that extend proximate an attachment region of the blade radially and axially along an airfoil portion of the blade toward the leading edge and trailing edge.

Abstract: A device for self-balancing a rotating part, such as a propeller, along a given axis is disclosed. The propeller 102 coupled to, a drive shaft with freedom for linear movement along longitudinal axis L-L; at least one pair of levers 614/616, comprising a first lever 614-1/616-1 and a second lever 614-2/616-2, that are pivotally mounted on mounting plate 606 at two diametrically opposite points 618; and at least one pair of weights 622 fixed at external ends of the levers 614/616. inner ends of levers 614/616 are operatively coupled to the propeller 102 such that when propeller 102 undergoes a linear movement in any direction along the longitudinal, axis L-L due to unbalance, inner ends of levers are, moved to cause the weights 622 to move to provide a balancing force to neutralize the unbalance in the propeller. An embodiment with only one pair of levers is also disclosed.

Abstract: A turbocharger includes: a mixed flow turbine including a turbine wheel; a turbine housing configured to house the turbine wheel, including a gas passage extending toward a leading edge of a blade of the turbine wheel; and nozzle vanes arranged in the gas passage in the circumferential direction of the turbine wheel, mutually adjacent two of the nozzle vanes forming a throat therebetween. Each nozzle vane is twisted with respect to a trailing edge of the nozzle vane as a twist center such that a width of the throat becomes narrower on the shroud side than on the hub side.

Abstract: The invention relates to a blade of a fan of a turbomachine, comprising a structure made from composite material, including a fibrous reinforcement obtained by means of the three-dimensional weaving of strands and a matrix in which the fibrous reinforcement is embedded,—the fibrous reinforcement comprising a first portion forming the leading edge and a second portion forming all or part of the trailing edge,—the strands of the fibrous reinforcement comprising first strands having a predetermined elongation at break and second strands having an elongation at break higher than that of the first strands, the first portion comprising all or some of the first strands while the second portion comprises all or some of the second strands.