Abstract: A gas turbine engine component includes opposing walls that provide an interior cooling passage. One of the walls has a turbulator with a hook that is enclosed within the walls.

Abstract: A turbine blade having labyrinth of internal channels for circulation of coolant, the novel labyrinth geometry includes; inlet arranged on axially upstream face of terminal portion leading to an upstream duct portion having first section adjacent the inlet and a second section, the second section having reduced cross section compared to first section; a first passage intersecting first section and extending through the blade body towards tip of the blade, a proximal end of leading edge passage arranged to capture incoming air flow; a main blade passage intersecting a downstream duct portion, the downstream duct portion arranged in axial alignment with the upstream duct portion but separate from upstream duct portion; and a restrictor passage intersecting with the mid-blade passage and extending towards a mid-blade duct portion, the mid-blade duct portion in axial alignment with the upstream and downstream duct portions and in fluid communication with the upstream duct portion.

Abstract: A seal assembly includes a blade outer air seal, a downstream vane, and a pressure wall, according to various embodiments. The blade outer air seal may include a radially outer surface and the downstream vane may be coupled to the blade outer air seal via a fluid sealing engagement. The pressure wall may be coupled to the blade outer air seal and may define a metering orifice. In various embodiments, the metering orifice of the pressure wall is configured to meter air flow from a first plenum upstream of the pressure wall to a second plenum downstream of the pressure wall. In various embodiments, at least a preponderance of the radially outer surface of the blade outer air seal at least partially defines the first plenum and the fluid sealing engagement at least partially defines the second plenum.

Abstract: A gas turbine engine includes a turbine section including a plurality of blade outer air seals disposed therein, the blade outer air seals each including a body including a raised material that extends beyond the outer surface of the body and the raised material includes an inlet hole formed through the raised material.

Abstract: A method to design a turbine including: estimating rates of thermal radial expansion for each of a stator and a rotor corresponding to a period of operation of the turbine; estimating a clearance between the rotor and the stator based on the rates of thermal radial expansion, and determining a mass or surface area of the stator or rotor based on the clearance.

Abstract: The main object of the invention is an angular stator sector (10) for a turbomachine compressor, comprising an outer shroud and an inner shroud (S) arranged coaxially one inside the other, and at least one vane (P) extending radially between the outer shroud and the inner shroud (S) and connected to the latter by its radial ends, characterized in that the inner shroud (S) comprises at least one brush seal (1, 2, 3) forming an obstacle to the recirculation of the downstream gases upstream of the inner shroud (S).

Abstract: A method of manufacturing a turbine shroud segment for a gas turbine engine comprises: metal injection molding (MIM) a shroud segment body with a groove defined in a first lateral side thereof and with a flow restrictor projecting integrally from an opposite second lateral side thereof. The groove is oversized relative to the flow restrictor to provide for a clearance fit between the flow restrictor and the groove of adjacent turbine shroud segments when assembled together in a ring formation. The shroud segment body with the integrated flow restrictor are then subjected to debinding and sintering operations.

Abstract: RAPPs comprise a housing, a swash plate with an inclined surface, and a rotor assembly positioned adjacent the swash plate. The swash plate and/or the inclined surface are ceramic. The rotor assembly comprises a rotor-drum having at least one cylinder bore having a piston disposed therein, wherein the piston has a ball-shaped end. A slipper is interposed between the swash plate and the rotor-drum, and includes a socket joint for accommodating the piston ball-shaped end therein. A plastic material may be disposed within the socket joint. The slipper has a ceramic interface surface in contact with the inclined surface. A stator plate is positioned in the housing, and a rotor plate is interposed between the stator plate and the rotor-drum. The stator plate has a ceramic interface surface in contact with the rotor plate. The rotor plate has a ceramic interface surface in contact with the stator plate.

Abstract: An anti-backflow device for a fan unit, which is fabricated by cutting a rectangle thin plate, includes: a plate body defining an air outlet to permit air outflow upon activation of the fan unit, and having at least two inner peripheral sides; a plurality of connection arms; and a plurality of blades. Each blade is connected a pair of the connection arms, which are in turn connected to two connecting holes formed in the inner peripheral sides of the plate body.

Abstract: Provided is a turbine including a rotor; a blade provided on the rotor and comprising a cooling flow path through which a cooling fluid flows; and a shroud surrounding an exterior of the blade, wherein the blade includes: at least one rib turbulator protruding into the cooling flow path; and at least one subsidiary protrusion protruding from an outer surface of the at least one rib turbulator.

Abstract: A cylindrical case includes a case main body made of a composite material of reinforcing fibers impregnated with a thermosetting resin, and an outward flange on the case main body. The outward flange includes: a bonding layer; a foundation layer disposed on the bonding layer; one flange constituting layer having a leg layer which is laminated from one slope surface of the foundation layer to the bonding layer and a wall layer which rises from the one slope surface; and the other flange constituting layer having a leg layer which is laminated from the other slope surface of the foundation layer to the bonding layer and a wall layer which rises from the other slope surface. The foundation layer is formed by laminating roving layers, while the flange constituting layers are formed by laminating a plurality of biaxial fabric layers including a biaxial fabric of a non-crimp structure.

Abstract: A fan unit includes a fan case, a partition member and a centrifugal fan. The fan case has an inflow port and a blowout port. The fan case includes a unit connecting portion for connecting the heat exchange unit. The partition member partitions an inside of the fan case into an upstream side space and a downstream side space. The partition member has an opening for allowing the upstream side space and the downstream side space to communicate with each other. The centrifugal fan includes an impeller including a plurality of backward curved blades. The centrifugal fan is arranged such that the impeller is located in the downstream side space and sucks air in the upstream side space through the opening. The blowout port is located on an outer side in a radial direction of the impeller in the downstream side space.

Abstract: An inlet door state control system for an auxiliary power unit (APU) includes an inlet door configured to allow air into an inlet of the APU. The system also includes an actuator configured to open the inlet door. The system also includes an APU threshold switch connected to the actuator, the APU threshold switch configured to automatically change from an open position to a closed position when a predetermined APU operating condition is met. In the system, the actuator opens the inlet door when the APU threshold switch is in the closed position.

Abstract: The present invention relates to a method (100) for intentionally mistuning a turbine blade of a turbomachine (10), by providing raised portions (31) or slots (32), the position of which is calculated on the basis of a vibration analysis of the disk (steps a) to d)).

Abstract: A heat exchanger assembly includes an outer manifold defining an outer cavity. An inner cavity is defined by an inner shell supported within the outer manifold and at least partially surrounded by the outer cavity. The inner shell includes a plurality of impingement openings for directing airflow into the inner cavity. An inner manifold is supported within the inner cavity. The inner manifold is exposed to impingement airflow through the plurality of impingement openings in the inner shell. The inner manifold includes a plurality of flow passages and at least one insulator pocket substantially aligned with the plurality of flow passages. A cooled cooling air system for a gas turbine engine and a gas turbine engine assembly are also disclosed.

Abstract: A compressor of an axial turbine engine comprising two rotors or contra-rotating drums, of which an inner rotor and an outer rotor are each provided with blade rows forming a regular alternating pattern. The inner rotor is provided with a radial annular junction fixed to the transmission shaft coming from a turbine. The outer rotor surrounds the inner rotor. The compressor also comprises a rotating bearing linked to the outer rotor and arranged axially level with the radial junction of the inner rotor so as to align the mechanical links axially. This alignment limits the effect of centrifugal force between the clearances between the blades and the walls of the rotors. A transmission with a pinion with a radial rotation axis allows the outer rotor to be driven by the inner rotor.

Abstract: A rotor of an exhaust-gas turbocharger includes a rotor hub and rotor blades disposed on the rotor hub. The rotor blades have a blade thickness distribution selected in such a way that the rotor blades have along their extent from a fluid inlet or leading edge to a fluid outlet or trailing edge at least one transition between a stiffness or rigidity-oriented blade thickness distribution and an inertia and stress-oriented blade thickness distribution over the height of the blade.

Abstract: A centrifugal pump (1) includes at least one pump stage (2) and a first housing part (3) having a suction connection (5). A second housing part (6) has a pressure connection (7). At least one intermediate housing part (10) at least in sections delimits a channel (11) leading to a pressure side of the at least one pump stage (2). The pump further includes a third housing part (20). The second housing part (6) and the at least one intermediate housing part (10) are arranged between the first and the third housing part (3, 20). The at least one intermediate housing part (10) and the second housing part (6) are configured to be arranged in at least two different positions with respect to the first and the third housing (3, 20).

Abstract: A rotor of a vacuum pump has a circular member that is driven rotatably, a cylindrical member joined to an outer circumference of the circular member, and a thread groove pump flow path formed between the cylindrical member and a stator member surrounding an outer circumference of the cylindrical member. The cylindrical member is made of a material having at least a feature of lower thermal expansivity or lower creep rate than that of a material of the circular member. A gap of a second region provided between a non-joint portion of the cylindrical member and the stator member is set to be smaller than a gap of a first region provided between a joint portion of the cylindrical member and the stator member.

Abstract: A beam for a rotorcraft rotor and particularly to a helicopter rotor. Said beam comprises a hub connection portion, a blade connection portion, a first flexure portion located between the hub connection portion and the blade connection portion and having a bending stiffness about a first axis which is orthogonal to the longitudinal axis of the blade, said bending stiffness being smaller than that of the hub connection portion and that of the blade connection portion and a shear portion located between the hub connection portion and the blade connection portion and having a shear stiffness parallel to a second axis which is orthogonal to the longitudinal axis of the blade and non-parallel to the first axis. Said shear stiffness is smaller than that of the hub connection portion and that of the blade connection portion.