Abstract: A propeller includes a bushing that rotates together with the propeller shaft, and a propeller damper disposed around the bushing, and an inner cylinder that surrounds the bushing via the propeller damper. The bushing includes a first cylindrical portion surrounding the propeller shaft, and a first protrusion protruding outward from the first cylindrical portion and integral with the first cylindrical portion. The inner cylinder includes a second cylindrical portion surrounding the bushing via the propeller damper and a second protrusion protruding inward from the second cylindrical portion. The inner cylinder is rotatable with respect to the bushing between a noncontact position and a contact position.

Abstract: A sealing system for a rotatable element defining an axis of rotation includes a rotor blade including a shank and an angel wing extending axially from the shank. The sealing system also includes a stator vane positioned axially adjacent the rotor blade. The stator vane includes a platform extending in an axial direction over the angel wing such that a clearance gap is defined therebetween. The sealing system also includes a sealing mechanism including a portion of the platform and a portion of the angel wing. The sealing mechanism includes at least one obliquely oriented surface such that the clearance gap defines a converging nozzle.

Abstract: The described embodiments relate to improving efficiency of a low-profile cooling fan. In one embodiment, an impeller of the cooling fan includes a shroud which covers a central portion of the impeller, thereby allowing a central inlet portion of the blades to have an increased fan blade height when compared to a cooling fan constrained by minimum part tolerances between the fan blades and a portion of the fan housing. In some embodiments, the impeller includes splitter blades that can improve performance of the low-profile cooling fan.

Abstract: A centrifugal fan impeller includes a front endring, a rear endring, and a plurality of blades coupled between the front and the rear endrings. At least one blade of the plurality of blades includes a blade span extending between the front endring and the rear endring, a leading edge, and a trailing edge. The at least one blade further includes a first elliptical cross-sectional profile extending between the leading and the trailing edges.

Abstract: A flexbeam unit for a multi-blade rotor of a rotary wing aircraft, the flexbeam unit comprising a plurality of flexbeam elements that define a predetermined number of torsion elements and a ring-shaped connection zone for attachment to a rotor hub associated with a rotor shaft of the multi-blade rotor, each flexbeam element passing the ring-shaped connection zone in a tangential manner and uninterruptedly connecting a first torsion element to a second torsion element of the predetermined number of torsion elements, wherein each flexbeam element overlaps at least one in the circumferential direction of the ring-shaped connection zone immediately following flexbeam element and is overlapped by at least one in the circumferential direction of the ring-shaped connection zone immediately preceding flexbeam element.

Abstract: A retaining ring for a turbomachine disk and coverplate assembly includes a ring body defining a coverplate interface side and an opposed disk lip interface side. A flow feature is defined by the ring body on the coverplate interface side to allow airflow between the turbomachine disk coverplate and the ring body such that a pocket defined between the coverplate and the turbomachine disk is in fluid communication with a conditioning flow pathway through the retaining ring.

Abstract: A wind turbine system to provide electrical power in areas not connected to the electrical power grid. The wind turbine system includes a frame and a rotatable shaft supported by the frame. A ring and idler gear assembly is coupled to the rotatable shaft. An upper rotor assembly is coupled to the rotatable shaft. The upper rotor assembly is configured to rotate in a first direction and thereby to rotate the rotatable shaft in a first direction. A lower rotor assembly is coupled to the ring and idler gear assembly. The lower rotor assembly is configured to rotate in a second direction which is opposite of the first direction and thereby to rotate the rotatable shaft in the first direction via the ring and idler gear assembly.

Abstract: The invention relates to a process for producing an insulation element (12), which can be arranged radially above at least one guide vane (14) in a housing (10) of a thermal gas turbine. The insulation element (12) is produced from a solid body (24) provided with a metallic shell (26), the solid body (24) consisting at least partially of a ceramic material. The invention also relates to an insulation element (12), which can be arranged radially above at least one guide vane (14) in a housing (10) of a thermal gas turbine, and to an aero engine having a housing (10), in which at least one insulation element (12) is arranged radially above at least one guide vane (14).

Abstract: Wastewater pump comprising a reversible motor (110) driving a rotor (160) equipped with blades (170). The rotor (160) is a disc (165) bearing pivoting blades (170) each mounted on a radial spindle (167) borne by the rotor. Each blade (170) is composed of a plate (171) bearing an articulation node (175) engaged on the spindle and a cutter (172) on the back of the plate forming a prop supporting the plate in the active position when the rotor (160) is rotating in the forward direction (D), and the cutter (172) projecting in the peripheral direction when the rotor (160) turns in the reverse direction (R), the plate (171) being applied against the disc (165). A fixed ring surrounds the disc and bears at least one cutter (135).

Abstract: Turbine engine (1), in particular for an aircraft, comprising at least one axial shaft (2) rotatably mounted in a casing (3) of the turbine engine (1), the turbine engine (1) comprising an annular reference part (10) comprising short (11) and long (12) longitudinal reference teeth, first means for detecting the passage of the short (11) and long (12) reference teeth so as to measure the speed of the shaft (2) of the turbine engine (1) about its axis (X), an annular measurement part (20) comprising longitudinal measurement teeth (21); and second means for detecting the passage of the long reference teeth (12) and the measurement teeth (21) so as to measure the torque of the shaft (2, 102) of the turbine engine (1).

Abstract: A component for releasing a flow of material into an environment subject to periodic fluctuations in pressure, which has: a first surface that includes an inlet; a second surface that includes an outlet; a duct formed in the component and extending from the inlet to the outlet so, when the component is in use, a flow of material received at the inlet can flow along the duct to be released at the outlet into an environment subject to periodic fluctuations in pressure. The duct includes a constriction at which it decreases in cross-sectional area as it progresses from the inlet to the outlet. This can help reduce the variation in flow rate of material released at the outlet caused by the periodic fluctuations in pressure, and may help to avoid/reduce ingestion, when the component is in use. Preferably, the component is configured to form part of a gas turbine engine.

Abstract: An air hot part of a gas turbine engine, the hot part having an isogrid formed on a cool surface opposite to a hot surface, where an impingement plate bonded over multiple impingement cooling surfaces of the airfoil, where the impingement plate forms a series of double or triple impingement cooling for separate surfaces of the airfoil. The impingement plate can be shaped and sized to fit over an airfoil surface that requires multiple impingement cooling.

Abstract: An aft hub sealing assembly for a gas turbine engine is disclosed. The aft hub sealing assembly includes an aft hub, a bearing cap, an aft baffle, a first seal, and a second seal. The aft hub includes a body portion and a disk portion aft surface. The bearing cap includes a bearing cap inner portion spaced apart from the body portion. The aft baffle is located adjacent the disk portion. The aft baffle includes a baffle forward surface following a contour of the disk portion aft surface. The first seal is between the bearing cap inner portion and the body portion. The second seal is between the bearing cap inner portion and the body portion.

Abstract: A structural assembly for a fluid-flow machine includes a main flow path boundary a row of relatively rotating blades with a gap existing between the blade ends and the main flow path boundary. A secondary flow duct is connected to the main flow path via two openings. A structural assembly has at least one support component and at least one insertion component. A structure extending in the circumferential direction and receiving or holding at least one insertion component along the circumference is provided in the support component. Each insertion component forms with at least some of its faces at least part of the main flow path boundary. Each secondary flow duct is jointly limited along at least part of its course by faces of at least two components of the structural assembly.

Abstract: A slim fan structure includes a fan frame, a top cover closed to a top of the fan frame to define a receiving space in the fan frame, a stator assembly mounted in the receiving space, and a hub fitted around the stator assembly. The fan frame has opposite first and third sides forming an air inlet and an air outlet, respectively, and opposite second and fourth sides having a first and a second side wall formed thereon, respectively. The first side wall includes a protruded portion laterally extended toward the air inlet, and the second side wall includes a stop portion located adjacent to the air outlet. With the air inlet and the air outlet formed on two lateral sides of the fan frame, the slim fan structure has an effectively reduced overall thickness and does not produce noise during operation to largely upgrade the operational performance thereof.

Abstract: An air cooled turbine airfoil with an impingement plate bonded over multiple impingement cooling surfaces of the airfoil, where the impingement plate forms a series of double or triple impingement cooling for separate surfaces of the airfoil. The impingement plate can be shaped and sized to fit over an airfoil surface that requires multiple impingement cooling.

Abstract: A support assembly and method for supporting an internal assembly in a casing of a turbomachine are provided. The support assembly may include a support member that may be slidably disposed in a recess formed in the internal assembly and configured to engage an inner surface of the casing. A biasing member may be disposed in a pocket extending radially inward from the recess. The biasing member may at least partially extend into the recess and may be configured to apply a biasing force to the support member disposed therein.