Abstract: A ram air turbine actuator release device to release a ram air turbine actuator includes a lock bolt releasably engaged to the ram air turbine actuator, a toggle including a toggle roller to engage the lock bolt, and a toggle pivot to couple the toggle to the ram air turbine actuator, a toggle actuator, including an actuation source, and a stroke amplifier, including a piston coupled to the actuation source, a first hydraulic chamber having a first diameter in fluid communication with the piston, a second hydraulic chamber having a second diameter in fluid communication with the first hydraulic chamber, and a plunger in fluid communication with the second chamber, wherein a diameter ratio between the first hydraulic chamber and the second hydraulic chamber amplifies a displacement of the actuation source to displace the plunger to rotate the toggle to disengage the toggle roller from the lock bolt.

Abstract: The disclosure aims to provide a ventilator module with improved efficiency. The ventilator module employs the dual structure of fans includes a swirler fan and a suction fan, in which the swirler fan is disposed at the front side and the suction fan is disposed at the rear side of the swirler fan so that a swirl formed by the drive of the swirler fan forms a donut-like low pressure zone around an inlet, and a tornado is formed by rotating the donut-like low pressure zone by the drive of the suction fan thereby cause the air below swirler fan to ascend at high velocity so as to be suctioned and discharged.

Abstract: Disclosed is a pump having a pump rotor rotatably supported about an axis of rotation in a pump stator. In this respect, the pump rotor is designed and is arranged above a rotor shaft in a shaft bearing such that a lubricating film of a lubricating fluid formed from the pump fluid can be formed in a lubricating ring gap between the rotor shaft and the shaft bearing. In accordance with the invention, a separation device is provided at the rotor shaft by which a predefinable quantity of the ingredient can be separated from the pump fluid by means of a centrifugal force in the operating state for providing the lubricating fluid.

Abstract: A sump pressurization system comprising an off-board source of pressurized air is provided to supplement pressurized air to a bearing sump arrangement when the operating conditions of the gas turbine engine are such that the on-board pressurized air source, e.g. the compressor of the gas generator, are such that the air pressure generated thereby is insufficient to pressurize a sump pressurization cavity. A gas turbine engine comprising such a sump pressurization system is also provided, as is a corresponding method for operating a gas turbine engine to facilitate reducing leakage of lubrication oil.

Abstract: A compressor in a turbocharger for an internal combustion engine includes a compressor wheel that includes a central hub having a centerline, a root portion and an end portion. A plurality of blades is formed around the central hub. The plurality of blades includes a group of full-blades extending from the root portion of the central hub up to a maximum distance from the root portion along the centerline, a group of partial-blades extending to an area along the centerline that is between 40% and 55% of the maximum distance along the centerline, and a group of half-blades extending to an area along the centerline that is between 55% and 70% of the maximum distance. The plurality of blades is organized in repeating sets of blades arranged around the compressor wheel, each repeating set including at least one full-blade, at least one half-blade and at least one partial-blade.

Abstract: The present disclosure provides a fir tree coupling for gas turbine engine parts comprising a load beam having a longitudinal axis, a base, a first side, and a second side, a rail extending from the base of the load beam between the first side and the second side, a tooth running parallel to the longitudinal axis disposed on the first side of the load beam. The rail may comprise at least one of, a convex sidewall having a convex curvature, a concave sidewall having a concave curvature, or a vertical sidewall extending perpendicular to the base. The rail may comprise a sidewall comprising a sidewall step wherein the sidewall has a step cut into a portion of the rail. The rail may comprise a tapered sidewall wherein the tapered sidewall extends at an angle to the base.

Abstract: An blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially inward from the main support member toward the blade outer air seal. The support tab configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the main support member.

Abstract: A rotor for a thermal turbomachine, in particular a gas turbine, is designed to conduct a medium, such as compressor air, in the interior of the gas turbine. In order to conduct the medium in the interior with low flow losses and at the same time to specify a rotor that can be produced comparatively simply and economically, a separately produced blade wheel is arranged between the mutually adjacent hub regions of the two rotor discs. The first side of said blade wheel lies against the hub region of the second rotor disc and the second side opposite the first side has a number of ribs, which extend from radially outside to radially inside.

Abstract: The invention relates to a turbomachine rotor including a disk and at least one blade wherein the root comprises a bulb accommodated into a groove associated with the disk, wherein the bulb includes a slot that opens up radially inwards at its lower face, and in that the rotor includes a retaining part extending partly into the groove projecting radially outwards from the bottom face of the groove, of which a radially outer end of the retaining part fits into the slot of the bulb and bears radially inwards on the inner wall of the slot of the bulb.

Abstract: There is provided a turbine including a rotor wheel including a plurality of dovetail grooves and at least one insertion groove, the dovetail grooves and the insertion groove arranged in a circumferential direction of the rotor wheel; a plurality of first buckets, each of the first buckets including a vane, a platform provided at a first end portion of the vane, and a dovetail provided at the platform and having a shape corresponding to a corresponding dovetail groove; at least one second bucket including a vane, a platform provided at a first end portion of the vane, and at least one protrusion portion provided at the platform and configured to be inserted into a corresponding insertion groove of the insertion groove; and a fixing member configured to be inserted through the protrusion portion and the rotor wheel and configured to restrict radial movement of the second bucket.

Abstract: The invention relates to a metering pump (1) made of plastic, with two rotors (10) coupled to one another via gears (11) and drivable in opposite directions, which are seated in a pump housing (5) equipped with suction ports (6) and outlet ports (7), wherein each rotor (10) has a rotor shaft (12), the rotor shaft ends (15) of which are seated in the walls (8, 4) of the pump housing (5). Each rotor (10) has two rotor blade walls (13) arranged diametrically on the rotor shaft (12), a partially cylindrical rotor blade shoe (14) being formed at each of the peripheral ends of said rotor blade walls, wherein the rotor blade shoes (14) on the one hand contact the cylindrical inside wall regions of the pump housing (5) and on the other contact the rotor blade shafts (13) of the adjacent rotor (10) in a sliding and sealing manner.

Abstract: The pump includes a first rotatable member including a radially inward facing groove having an edge. The first rotatable member configured to receive a plurality of flows of fluid over the edge. The first rotatable member configured to rotate at a first angular velocity. The pump also includes a second rotatable member including a collector configured to rotate at a second angular velocity. The second rotatable member also includes a plurality of scoop tubes extending radially outwardly from the collector. Each scoop tube of the plurality of scoop tubes includes a first end coupled in flow communication to the collector and a second end including an inlet opening extending into the groove. The second end curved such that the inlet opening is open in a direction of rotation of the second rotatable member. The inlet opening configured to scoop a fluid collected in the groove.

Abstract: An assembly adapted for use in a gas turbine engine is disclosed herein. The assembly includes a first component including metallic materials and a second component including ceramic matrix composite materials. A portion of the second component is configured to engage a portion of the first component directly so that the second component is supported in a predetermined position.

Abstract: A fan and an electronic device are provided. An opening is provided on a sidewall of a housing of the fan, a baffle is arranged at the opening and to cover a part of the opening. When an impeller of the fan rotates in a first direction, a first end of the baffle is fixed and a second end of the baffle moves towards the inside of the housing, or in the case that the impeller rotates in the first direction, the baffle protrudes towards the inside of the housing to form a protrusion. In the case that the impeller rotates in a second direction, the second end of the baffle moves towards the outside of the housing, or in the case that the impeller rotates in the second direction, the baffle protrudes towards the outside of the housing to form a protrusion.

Abstract: A shrouded turbine airfoil (10) with a leakage flow conditioner (12) configured to direct leakage flow to be aligned with main hot gas flow is disclosed. The leakage flow conditioner (12) may be positioned on a radially outer surface (18) of an outer shroud base (20) of the outer shroud (22) on a tip (24) of an airfoil (10). The leakage flow conditioner (12) may include a radially outer surface (28) that is positioned further radially inward than the radially outer surface (18) of the outer shroud base (20) creating a radially outward extending wall surface (30) that serves to redirect leakage flow. In at least one embodiment, the radially outward extending wall surface (30) may be aligned with a pressure side (38) of the shrouded turbine airfoil (10) to increase the efficiency of a turbine engine by redirecting leakage flow to be aligned with main hot gas flow to reduce aerodynamic loss upon re-introduction to the main gas flow.

Abstract: The invention proposes a casing (30) of an aircraft turbine (16), intended to support a set of ring sectors (28) which partly delimits a channel for the passage of a gas stream through the turbine (16), where the casing (30) includes means for dynamic adjustment of the radial position of the ring sectors (28) by controlled injection of an air stream on to portions (36) of an annular wall (34) of the casing (30), where the casing (30) includes an upstream radial tab (38) which connects an upstream end of each ring sector (28), in the flow direction of the gas stream, to the casing (30), and a downstream radial tab (40) which connects a downstream end of each ring sector (28) to the casing (30), where both upstream and downstream radial tabs (38, 40) are made from a single piece with the casing (30), characterized in that each radial tab (38, 40) is made as two portions (42, 44) from different materials.

Abstract: An aeroengine has an inlet system with a forward end with respect to a flight direction. The inlet system includes a main inlet duct for selectively directing a first air flow from a forward main intake opening of the main inlet duct to a compressor rotor, the forward main intake opening being defined at the forward end of the inlet system and a secondary inlet duct for directing a second air flow from a secondary intake opening of the secondary inlet duct to the compressor rotor only when the main inlet duct is closed. A control apparatus is provided for selecting the first and second air flow to enter into the compressor rotor.

Abstract: A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.

Abstract: Systems and methods are provided for sidestream mixing. The system may include a first junction formed from a plurality of conduits. The plurality of conduits may include a first conduit fluidly coupled to a compressor, the first conduit forming a first conduit diameter and configured to flow therethrough a first process fluid stream of a plurality of process fluid streams. The plurality of conduits may also include a second conduit fluidly coupled to the first conduit and the compressor, and configured to flow therethrough a second process fluid stream of the plurality of process fluid streams. The first junction may be disposed a first distance at least three times the first conduit diameter upstream of the compressor, such that the first process fluid stream and the second process fluid stream are mixed and form a first combined process fluid stream prior to being fed into and pressurized in the compressor.

Abstract: A method of mixing airflow within an inner diameter (ID) mixing chamber of a turbine exhaust case (TEC) includes directing pressurized airflow into the ID mixing chamber. Cooling airflow is directed radially inward via a tube and is then expelled into the ID mixing chamber in a circumferential direction for mixing with the pressurized airflow.