Abstract: An airfoil defining a span extending between a root and a tip. The airfoil includes a retaining member extending at least partially between a leading edge and a trailing edge defining a frangible line extending at least partially along a chord at a point along the span of the retaining member. The airfoil further includes a frangible airfoil portion extending between the tip and the frangible line. The frangible airfoil portion includes a first plurality of composite plies, at least one composite ply of the first plurality of composite plies wraps around the retaining member. The airfoil includes a residual airfoil portion extending from the frangible line to the root including a second plurality of composite plies, at least one composite ply of the second plurality of composite plies wraps around the retaining member. Further, the residual airfoil portion meets the frangible airfoil portion at the frangible line.

Abstract: A fan module includes a housing, a bearing, a rotating shaft, and a fan wheel. The housing includes a bottom covering plate, a top covering plate, and a side wall connected between the bottom covering plate and the top covering plate and surrounding to form a housing space. The bearing is disposed on the bottom covering plate and includes a supporting pillar. The supporting pillar extends from the bottom covering plate toward the top covering plate. The rotating shaft has a first through hole therein. The rotating shaft is rotatably sleeved onto the supporting pillar by the first through hole. The fan wheel is connected to an outer edge of the rotating shaft.

Abstract: Disclosed are provided indoor unit of an air conditioner. A present invention is to provide an indoor unit of an air conditioner having an improved structure for preventing vibrations and noise of a blade due to vibrations of a motor when the blade rotates, and a blade unit applied to the indoor unit. The indoor unit of the air conditioner includes a main body including an outlet, and a blade unit configured to adjust a direction in which air discharged from the outlet is discharged, wherein the blade unit comprises, a blade coupled with the main body to be rotatable in the outlet, a motor including a rotation transfer member, and configured to generate a rotatory force that is transferred to the blade; and a buffer member made of a material having a restoring force, coupled with the blade at one end, and surrounding a part of the rotation transfer member.

Abstract: A method for constructing a cold box module and resulting apparatus is provided. The method can include providing a cold box module having framing and an upper and lower module sections, introducing an upper column section longitudinally into the upper module section while the upper module section is substantially horizontal; introducing a lower column section longitudinally into the lower module section while the lower module section is substantially horizontal; releasably attaching the lower column section to the lower module section using shipping saddle spacers and support saddles; and attaching a skirt attachment to the lower column section and the lower module section, wherein the skirt attachment is configured to limit longitudinal movement of the lower column section when the lower module section is in a horizontal position during transport.

Abstract: A coupling is disclosed for connecting a propeller to a motor in an aircraft such as a rotary wing aircraft and the like. The coupling comprises a propeller hub having an inner propeller hub bore defining an axial keyway. A rotatable shaft has an internal shaft bore connected for rotation with the motor. A radial key is slidably located in a radial aperture extending through the rotatable shaft. An actuator is slidably mounted within the internal shaft bore of the rotatable shaft. The radial key is received with the axial keyway for securing the propeller hub to the rotatable shaft. A depression of the actuator retracting the radial key relative to an outer surface of the rotatable shaft for permitting the propeller hub bore to be introduced onto the rotatable shaft.

Abstract: A turbine that includes an inner shroud segment having a cooling configuration in which interior channels are configured to receive and direct a coolant. The cooling configuration may include a pair of counterflowing crossflow channels in which a first crossflow channel extends side-by-side with a neighboring second crossflow channel; and a feed and outlet channel configuration comprising neighboring feed and outlet channels. The feed channel may connect at a first connection to an upstream end of the first crossflow channel and the outlet channel may connect at a second connection to a downstream end of the second crossflow channel. The feed channel may extend in an inner radial direction from an inlet to the first connection. The outlet channel may extend in an outer radial direction from the second connection to an outlet. The feed channel may include a section that undercuts the outlet channel.

Abstract: A ceramic matrix composite (CMC) component including a subcomponent, such as a band flowpath, a load bearing wall and a wall support, each comprised of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix. The CMC component further including at least one mechanical joint joining the subcomponent, the load bearing wall and the wall support to form the CMC component. The reinforcing fibers of the load bearing wall are oriented substantially normal to the reinforcing fibers of the subcomponent and the wall support. Methods are also provided for joining the subcomponent, the load bearing wall and the wall support to form a mechanical joint.

Abstract: A method for installation of a cryogenic distillation apparatus is provided. The method can include the steps of: providing an upper module section having an upper column section disposed within and secured to the upper module section, wherein the upper module comprises a roof; providing a lower module section having a lower column section disposed within and secured to the lower module section; erecting the lower module section from a horizontal position to a vertical position at an installation site; lifting the upper module section from a horizontal position and attaching the upper module section, while in a vertical position, to a top portion of the lower module section; lowering the upper column section, independent of the upper module section, toward the lower column section; and welding the upper column section and the lower column section together.

Abstract: A method for assembling an airfoil includes pressing a blade body together with at least one of a blade sheath and a blade cover between a plunger and a die base to join the blade body to the blade sheath and/or the blade cover. The method can include transferring heat from the plunger and/or the die base to at least one of the blade body, the blade sheath and the blade cover to cure an adhesive.

Abstract: A damper seat for a ring damper that redirects axial loads and is disposed within a gas turbine engine with at least one disk rotatable about a rotational axis and having a disk neutral axis extending radially from the rotational axis.

Abstract: The invention relates to a method of forming a roller bearing cage comprising: forming a planar strip of material, having a length corresponding to a circumferential dimension of a roller bearing cage; forming openings in the planar strip, corresponding to positions at which rollers are to be located; forming a plurality of tangs, alongside and part of each side of the length of the planar strip, each tang having a first tang edge of a first length adjoining the strip and a second edge of a second length opposite the first tang edge; and bending each side of the length of the strip such that the plurality of tangs is positioned at an angle with respect to the planar strip, wherein the fold is through an angle of greater than 90° and less than or equal to 180° relative to the plane of the planar strip.

Abstract: A rotor blade comprises a mount and a blade that extends from the mount along a radial axis. The leading edge includes an indent segment. The leading edge has a leading edge radial length measured along the radial axis. The indent segment has an indent radial length measured along the radial axis. The indent segment has an indent depth. A first ratio of the indent radial length to the leading edge radial length is at most 0.5. A second ratio of the indent depth to the indent radial length is at least 0.05.

Abstract: According to one example, an assembly for a repair of a compressor casing of a gas turbine engine is disclosed. The assembly can comprise: an arcuate track configured to be mounted to the casing, wherein when mounted to the casing the track is configured to be spaced in a substantially concentric arrangement from an inner surface of the casing; a carrier coupled to the track and movable therealong; and a machining device mounted to the carrier, the carrier configured to adjust at least an axial position of the machining device relative to the track for machining the inner surface of the casing.

Abstract: The present invention relates to a centrifugal fan comprising a fan housing with a radial outlet opening arranged in a radial peripheral wall thereof, a rotor arranged rotatably in the fan housing and provided close to an axial rotation axis thereof with a rotor inflow opening, wherein the fan housing is provided close to the rotation axis of the rotor with an axial inlet opening, and a tube part which extends in the fan housing from the radial outlet opening arranged in the radial peripheral wall and inward along the radial peripheral wall. The invention further relates to a heating device comprising a burner with a fuel mixture infeed opening, a centrifugal fan according to the invention, and wherein a fluid connection is provided between the fuel mixture infeed opening of the burner and the outlet opening of the centrifugal fan.

Abstract: A containment structure for surrounding a rotatable machine includes a double-walled inner shell having a forward end, an aft end, and a substantially cylindrical body extending therebetween. The inner shell includes an inner wall at least partially surrounding a bladed portion of the bladed rotor, and an outer portion that branches radially outward from the inner wall. The containment structure also includes a substantially cylindrical back sheet coupled to the outer portion and disposed radially outward of the inner wall.

Abstract: An airfoil for a turbine engine having an engine component including an air supply circuit coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the air supply circuit to an outer surface of the engine component through the passages.

Abstract: The present disclosure provides a core structure comprising a trailing edge section including a plurality of rib-forming apertures (126) defined by a plurality of radially-extending channel elements (130) and axially-extending passage elements (128) and a radially outer low flow framing channel element (134) located adjacent to a radially outer edge (124). The core structure may be used for casting a gas turbine engine airfoil (11). The radially outer framing channel element (134) comprises a plurality of notches (14) extending radially inwardly from the radially outer edge (124). A distal portion (144a) of the notches (140) overlaps in an axial direction with the rib-forming apertures (126) of a first axially-aligned outer row (138a). A radial height of at least one of a first and a second axially-extending passage element (148a, 148b, 150) is greater than a prevalent radial height of other axially-extending passage elements (128) in the core structure.

Abstract: A blade track system includes an outer ring coupled with a blade track, and an inner ring positioned concentrically between the outer ring and the blade track. The outer ring designed to radially expand, at a first predetermined rate, in response to acceleration of a gas turbine engine. The segments of the blade track radially outwardly expanded away from a hub of the gas turbine engine by the radial expansion of the outer ring. The inner ring designed to radially contract inwardly toward the hub of the gas turbine engine at a second predetermined rate in response to deceleration of the gas turbine. The first predetermined rate being greater than the second predetermined rate, and radial contraction of the outer ring and the segments of the blade track constrained to the predetermined rate of contraction of the inner ring.

Abstract: A blade outer airseal comprising a body having: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; a trailing end; a metallic substrate; and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer comprising a metallic matrix and a filler. The filler forms at least 20% by volume of the abradable layer with agglomerates or aggregates of oxide particles, the oxide particles having a D50 size ?200 nm.

Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool. The LP spool and the HP spool are independently rotatable about an axis. The LP pressure spool has an LP compressor and an LP turbine. The HP spool has an HP turbine and an HP compressor. The LP compressor is axially positioned between the HP compressor and an accessory gear box (AGB). The AGB is drivingly connected to the HP spool through the center of the LP compressor.