Abstract: A seal in a turbine of a combustion turbine engine is described. The seal is formed within a trench cavity defined between a rotor blade and a stator blade. The stator blade includes a sidewall projection and the rotor blade includes an angel wing projection extending toward the stator blade. The side wall projection overhangs the angel wing projection. The seal include: a port disposed on an inboard surface of the stator projection; and deflecting structure disposed on the angel wing projection. The deflecting structure may be configured to receive the fluid expelled from the port and deflect the fluid toward an inlet of the trench cavity.

Abstract: An airfoil platform comprises a leading edge portion and a trailing edge portion. The trailing edge portion comprises a first region having a convex flowpath contour, a second region having an intermediate flowpath contour extending downstream from the convex flowpath contour, and a third region having a concave or linear flowpath contour extending downstream from the intermediate flowpath contour to a downstream end of the trailing edge portion of the platform.

Abstract: A connecting system for metal component and CMC components, a turbine blade retaining system and rotating component retaining system are provided. The connecting system includes a retaining pin, a metal foam bushing, a first aperture disposed in the metal component, and a second aperture disposed in the ceramic matrix composite component. The first aperture and the second aperture are configured to form a through-hole when the metal component and the ceramic matrix composite component are engaged. The retaining pin and the metal foam bushing are operably arranged within the through-hole to connect the metal component and the ceramic matrix composite component.

Abstract: A fluid cooling device for the propulsion unit of a propfan type aircraft including a compressed air intake at the air compressor of the turbomachine, an air vein capable of conveying the collected compressed air to a cooler, and a system for conveying the heat of the lubricant to the cooler is provided. The cooler includes a matrix body provided with a plurality of ducts for a cooling agent, the ducts extending along a first inner surface up to a second outer surface of the matrix body such that the collected pressurized air serving as a cooling agent can pass through the matrix body, the matrix body of the cooler forming a portion of the outer skin of the propulsion unit; and a set of fins extending from the outer surface towards the outside of the propulsion unit, and oriented mainly parallel to the air flow direction when the aircraft is in flight.

Abstract: A hydraulic pressure control apparatus for an automatic transmission may include an oil tank, a first hydraulic pump fluid-connected with the oil tank for generating a first hydraulic pressure, a second hydraulic pump fluid-connected with the first hydraulic pump for generating a second hydraulic pressure higher than the first pressure, a torque converter and a lubrication portion fluid-connected to a first low pressure supply line to receive the first hydraulic pressure, a first high pressure supply line fluid-connected to the second hydraulic pump and to a powertrain, a switching valve bifurcated from the first low pressure supply line and fluid-connected to the first hydraulic pump and both the torque converter and the lubrication portion, and a feedback line fluid-connected to the first high pressure supply line to the switching valve so as to selectively open or close the switching valve according to the second hydraulic pressure.

Abstract: Embodiments of the present disclosure include a system having a turbine blade segment having a blade and a mounting segment coupled to the blade, wherein the mounting segment has a multi-piece assembly configured to mount in a radial direction into a slot of a turbomachine rotor.

Abstract: A rotor assembly for helicopter vehicles for providing an easy way of controlling pitch, roll and lift of the aircraft by respective servo actuators. The rotor assembly has a rotor shaft, at least two rotor blades, a rotor head, and a non-rotating swash plate. The rotor assembly also includes a pitch hinge for each rotor blade connecting each rotor blade to the rotor head. The rotor assembly also includes a guide member for each rotor blade. As the rotor assembly rotates, the guide members are in substantial contact with an upper surface of the non-rotating swash plate. Forces such as magnetic and/or an aerodynamic forces are applied on the rotor blades and are sufficiently strong to create a valve effect on the pitch hinge, which in turn maintains contact between the guide members and the non-rotating swash plate.

Abstract: A fan rotor has a fan web and a plurality of circumferentially spaced-apart fan blades extending radially outwardly from an outer rim of the fan web. The outer rim is integrally connected to an inner rim through an axially facing web section. The web section has an inward concavature and extends aft of the center of gravity of the fan blades to shift the center of gravity of the hub rearwards while maintaining airfoil stress below critical levels. The rim section may have an inwardly projecting annular channel formed in a leading edge thereof and tuned to the 2M3ND mode of the fan hub.

Abstract: An example airfoil for a gas turbine engine includes a body having a first surface extending from a first edge to a second edge and a cavity disposed in the body. A first cover is at least partially disposed within the cavity. The first cover includes a first portion cooperates with a corresponding second portion. A second cover covers the first cover and forms at least a portion of the first surface with the body. The first cover is disposed between the body and the second cover. The first cover and the second cover have a different coefficient of thermal expansion than the body.

Abstract: A compressor section for use in a gas turbine engine has a plurality of compressor stages. Each compressor stage is provided with a rotor hub, and each rotor hub mounts a plurality of compressor blades. A rotor drum extends between adjacent rotor hubs. A plurality of stator stages have an outer ring and a radially inner ring. A plurality of vanes extend between the outer and inner rings. An inner surface of the inner ring is spaced by a gap from an outer surface of the rotor drum. The rotor drum is provided with a plurality of blades having a general airfoil shape to resist leakage across the gap.

Abstract: A centrifugal fan includes an impeller, a motor and a case. The impeller includes a hub and multiple blades. The hub has a center. The blades are connected to the hub and have all respective outmost edges collectively define a circle with the center and a radius R. Each blade has at least one concave cutout. Each concave cutout is equipped with a depth of greater than 0.5 millimeters and an obtuse angle of less than 170 degrees, wherein the obtuse angle is an included angle between an inner edge of the concave cutout and an outer edge of the blade. The motor is secured to the huh and drives the impeller to rotate. The case houses the impeller and the motor.

Abstract: A rotary seal for sealing a bladed rotor of a gas turbine engine to a stator thereof comprises a sealing element and a sealing element support comprising a radially outer edge portion on which the sealing element is fixed, a radially inner mounting portion adapted to be attached to a supported rotor hub, and a flexible, medial web portion extending between the radially outer edge portion and the radially inner mounting portion.

Abstract: Systems and methods for altering airflow to gas turbine engines are provided. In this regard, a representative system includes a gas turbine engine inlet having a slat, the slat being movable between a retracted position and an extended position. In the extended position, the slat increases an effective diameter of the inlet compared to the diameter of the inlet when in the retracted position.

Abstract: A hydraulic tubing support that reduces noise transmitted to an operator due to pulsation of hydraulic oil in a junction tube. The hydraulic tubing support structure includes a pair of left and right remote control valves for generating pilot pressures for the plurality of hydraulic actuators in response to an input operation performed on each operating lever, pump-side tubes and tank-side tubes respectively extending from the respective remote control valves, a junction tube for allowing communication of the tubes guided to below a floor plate through a through hole and communication of the tubes guided to below the floor plate through a through hole, and a middle reinforcement beam extending in a right-and-left direction and fixed to the lower surface of the floor plate. The junction tube is fixed to the middle reinforcement beam in a non-contact state with the floor plate.

Abstract: Provided is a piston type compressor which can enhance cooling of internal parts housed in a crank chamber, while effectively reducing an outflow of oil to the outside of a compressor by effectively performing a centrifugal separating operation due to the rotation of a shaft. The compressor includes: a first suction path which directly introduces a working fluid flowed from a suction port 30 into suction chambers 27a, 27b without via the crank chamber 7; and a second suction path which introduces the working fluid flowed from the suction port 30 into the suction chambers 27a, 27b via the crank chamber 7, and the second suction path includes: an oil separation passage 32 where a working fluid is introduced into the suction chambers 27a, 27b from the crank chamber 7 via holes formed in the shaft; and a bypass passage 33 where the working fluid is introduced into the suction chambers 27a, 27b from the crank chamber 7 through the cylinder blocks 1, 2 without via the shaft 12.

Abstract: The invention relates to a nacelle (1) for a turbojet engine (8) comprising: an air intake structure (4) able to channel a flow of air towards a fan (7) of the turbojet engine (8), comprising an air intake lip (21) upstream of the nacelle (1) and attached at its ends to an outer panel (25) and an inner panel (23); a central structure (5) intended to surround said fan (7) and to which the air intake structure (4) is attached in such a way as to ensure aerodynamic continuity, said central structure (5) comprising a secondary, or bypass, flow path outer ring section (11) intended to surround the engine and a central outer cowl (13), and a downstream section (6), the outer panel (25) comprising a moving part (25a) attached to the air intake lip (21) and extending downstream of the inner panel (23) and at least one fixed part (25b) fixed to the central structure (5) or to the downstream section (6) and intended to nest together with the moving part (25a) through their having complementary shapes.

Abstract: A metallic annular connection structure between two parts for an aircraft turbomachine, with an arbitrary half-section including two primary branches and a base forming a first U opening up in the radial direction from a longitudinal axis, and two secondary branches forming a second U with one of the two primary branches opening up in the longitudinal direction. The primary and secondary branches and the base of the first U are made in a single piece.

Abstract: An abrasive coating on a rotor shaft interacts with cantilevered vanes to form an abradable air seal in a turbine engine. The abrasive coating includes a metal bond coat, and an abrasive layer containing a plurality of abrasive CBN grit particles in a ceramic matrix.

Abstract: A strip seal for providing a seal between adjacent components, which include a first groove and a second groove angled with respect to and intersecting the first groove. The grooves of respective components are opposed to one another when the components are assembled. The strip seal includes a first strip section to span between and be received in the opposed first grooves, and a second strip section to span between and be received in the opposed second grooves. One end of the first strip section is arranged to butt against the second strip section at the intersection of the grooves. The other end of the first strip section has at least one deformable projection that can engage the end of the first groove. The projection deforms as it engages the end of the groove and urges the end of the first strip section against the second strip section.

Abstract: A wind turbine includes a component arranged in the nacelle of the wind turbine, which component requires lubricating with a liquid lubricant. An automatic liquid lubricant changing arrangement includes a source of fresh liquid lubricant, a supply line for supplying fresh liquid lubricant from the source to the component, a waste liquid lubricant collecting unit for waste liquid lubricant, and a removal line for conveying waste liquid lubricant from the component to the waste liquid lubricant collecting unit. Moreover, a control device for such a wind turbine and a method of operating such a wind turbine are provided.