Abstract: A bearing housing includes an inner housing portion centered on a central axis and an outer housing portion centered on the central axis. The inner housing portion has a first end and a second end positioned axially away from the first end. The outer housing portion has a first end and a second end positioned axially away from the first end. A disk portion connects the second end of the outer housing portion to the second end of the inner housing portion The outer housing portion includes a radially outer surface having a diameter Doh1, a radially inner surface having a diameter Doh2, and a shoulder on the first end of the outer housing portion and having a radially outer surface with a diameter Ds. Diameter Ds is smaller than the diameter Doh1 and larger than the diameter Doh2.

Abstract: A lay shaft assembly for a speed reduction gearbox in a geared turbofan gas turbine engine, the lay shaft assembly having an output gear formed on a lay shaft as a single piece, and an input welded gear formed as a separate piece that is welded to the shaft in close proximity to the output gear. The output gear is machined and precision-ground prior to welding the input welded gear to the lay shaft so that the two gears can be located in close proximity. The input welded gear is precision-ground after the gear has been welded to the shaft.

Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Abstract: A component for a gas turbine engine includes a trailing edge tip corner that at least partially defines a trailing edge cavity and a multiple of corner features within the trailing edge cavity, the multiple of corner features splayed along the trailing edge tip corner.

Abstract: A wind turbine blade includes a first blade segment and a second blade segment extending in opposite directions from a chord-wise joint. The first blade segment includes a beam structure extending lengthways that structurally connects with the second blade segment at a receiving section, wherein the beam structure forms a portion of an internal support structure and includes a shear web connected with a suction side spar cap and a pressure side spar cap. The present technology also includes a joint rod located at a first end of the beam structure for connecting with the receiving section of the second blade segment to form a coupling joint about a joint axis. The coupling joint is coupled to an adjustable elastic support. The receiving section may further include a torque coupling positioned offset from the joint axis, such that a bending motion of the beam structure automatically induces a twist motion. A method of assembling the wind turbine blade is additionally disclosed.

Abstract: A mechanism for folding a rotor blade that is rotatably coupled to a blade cuff about a blade-fold axis between an extended position and a folded position. The mechanism includes a swash plate configured to translate relative to a mast, a pitch link rotatably coupled to the swash plate, a pitch horn rotatably coupled to the pitch link, a crank coupled to the pitch horn, and a link rotatably coupled to the crank and rotatably coupled to the rotor blade. The pitch horn and the crank being configured to commonly rotate relative to the blade cuff about a crank axis in response to translation of the swash plate, wherein the crank axis passes through the blade cuff.

Abstract: Provided is a spar cap for a wind turbine blade, including a main body, which includes an electrically conductive portion, and at least one metal conductor, wherein the metal conductor includes a terminal portion and at least one connection portion, wherein the connection portion of the metal conductor is wrapped by a first end of an electrically conductive and stripe-shaped carbon fibre mat, which abuts with a second end at least partly on the electrically conductive portion of the main body.

Abstract: A rotary machine includes: a stationary body having a stationary-side peripheral surface; a rotating body having a rotating-side peripheral surface facing the stationary side-peripheral surface. One surface which is one of the stationary-side peripheral surface and the rotating-side peripheral surface has an upstream-side peripheral surface, a downstream-side peripheral surface, and a rearward step surface. The other surface has an upstream-side seal fin forming a minute gap between the upstream-side seal fin and the upstream-side peripheral surface; a downstream-side seal fin forming a minute gap between the downstream-side seal fin and the downstream-side peripheral surface. The rearward step surface has a guide surface extending downstream Da2 while directed toward the other surface and connected to the upstream-side peripheral surface.

Abstract: A rotary machine includes a first flange in which a first hole portion is formed, a second flange disposed to face the first flange via an abutting surface and having a second hole portion formed therein, and a stud bolt inserted into a first hole portion and a second hole portion and fastened to a female screw of the second hole portion, wherein the thickness of the second flange is larger than the thickness of the first flange.

Abstract: A ring-shaped thermomechanical part for a turbine engine, comprising at least one coating including a polymeric matrix and fillers in non-deflagrating carbon exclusively comprising the chemical element C. A turbine engine comprising such a part.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that extends from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction. The airfoil section defines a pressure side and a suction side separated in a thickness direction, and the airfoil section includes a metallic sheath that defines an internal cavity receiving a composite core. The root section defines at least one bore dimensioned to receive a retention pin. At least one damping element is received in the internal cavity and that selectively causes the airfoil section to stiffen.

Abstract: An annulus filler for mounting to a rotor disc in a gas turbine engine includes a body portion having a top wall arranged to bridge the gap between two adjacent blades extending from the rotor disc and to define an air flow surface for air passing between the blades; and a separately formed rear interface portion, fixed to the body portion adjacent to a down-flow end of the top wall. The rear interface portion forms a lip projecting below the top wall.

Abstract: In a rotary machine that includes rotating body including a rotating-body main body and a pair of rotor shaft ends fixed to the both outer sides in the shaft direction of the rotating-body main body; a casing accommodating the rotating-body main body and being penetrated by the rotor shaft ends; a bearing rotatably supporting the rotor shaft ends and having a bearing face being provided with lubricant fluid from a lubricant line; and the support part supporting the casing, the support part is cooled through heat exchanging between the lubricant fluid the support part.

Abstract: An article for high temperature service is presented. The article includes a substrate and a plurality of coatings disposed on the substrate. At least one coating in the plurality of coatings includes an oxide of nominal composition AxB1-yDyOz, wherein A includes a rare-earth element, B includes tantalum or niobium, D includes zirconium or hafnium, 2?x?3, 0<y<1, and 6?z?7.

Abstract: A compressor rotor includes a first outer cavity formed in a rotor main body and into which air on a high-pressure side of blades is to be introduced, a first inner cavity formed in the rotor main body on an inner side in a radial direction of the first outer cavity; and a first communication passage which connects the first outer cavity and the first inner cavity to each other in the radial direction of the first outer cavity. Along an entire length of the first communication passage from the first outer cavity to the first inner cavity, the first communication passage is inclined toward a forward side of a rotation direction of the rotor main body.

Abstract: Disclosed are: a blower fan capable of reducing noise and power consumption; and an air conditioner having the same. The present device comprises: a hub connected to a driving member so as to receive rotating power; and a plurality of wings radially arranged along the circumference of the hub, wherein the plurality of wings can comprise: uneven parts formed at trailing edges, which are the rear edge portions of each wing, with respect to the rotational direction thereof; and tail wing parts formed on the outer sides of the uneven parts so as to have convex parts protruding farther than the uneven parts.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a support mountable to an engine static structure. The support has a main body extending axially between leading and trailing edge portions and circumferentially between opposed mate faces, and the main body includes a pair of opposed retention hooks extending inwardly from the leading and trailing edge portions to bound an elongated groove extending circumferentially between the opposed mate faces. A seal has a sealing portion that extends from an engagement portion. The sealing portion has a sealing face that extends circumferentially between first and second mate faces. An overwrap has one or more plies that follow a perimeter of the engagement portion to define an interface between the retention hooks and the engagement portion. A method of sealing is also disclosed.

Abstract: A gas turbine engine includes a fan drive turbine driving a fan rotor through a main gear reduction. A primary lubricant system supplies lubricant to the main gear reduction. An auxiliary oil pump supplies oil to the main gear reduction. An auxiliary pump epicyclic gear train drives the auxiliary pump when the fan rotor is rotating in either direction. The main gear reduction is separate from the auxiliary pump epicyclic gear train.

Abstract: A variable vane actuation system of a gas turbine engine is provided. The variable vane actuation system including: a variable vane; a vane stem operably associated with the variable vane, wherein the variable vane is configured to rotate with the vane stem; a vane arm having vane stem end and a vane pin end opposite the vane stem end, the vane arm being operably connected to the vane stem at the vane stem end; and a rotational variable differential transformer operably connected to the vane stem, the rotational variable differential transformer configured to detect an amount of rotation of the vane stem.

Abstract: A passive flow modulation device according to an embodiment includes: a pressure sensitive main valve controlling a flow of a cooling fluid from a first area to a second area through an orifice; and a temperature sensitive pilot valve coupled to the pressure sensitive main valve, the temperature sensitive pilot valve configured to open at a predetermined temperature in the first area, causing a pressurization of the pressure sensitive main valve, wherein the pressurization of the pressure sensitive main valve actuates the pressure sensitive main valve to an open position, allowing the cooling fluid to flow from the first area to the second area through the orifice.