Abstract: An annular cover for a lubrication chamber of a rotary bearing of a turbomachine. The cover includes a wall that is generally circular and flared with an orifice that is designed to receive a transmission shaft opposite an assembly surface for the cover, and at least one duct communicating with the inside of the wall and extending along the wall as far as the assembly surface. The duct is formed in the thickness of the body of the wall which is made from the same material, and which includes a composite material with a thermoplastic matrix and carbon fibers.

Abstract: The present invention relates to a blade row group arrangeable in a main flow path of a fluid-flow machine and including N adjacent member blade rows firmly arranged relative to one another in both the meridional direction and the circumferential direction, with the number N of the member blade rows being greater than/equal to 2 and (i) designating the running index with values between 1 and N, with a front member blade row (i) as well as a rear member blade row (i+1) being provided, and with the blade row group having two main flow path boundaries. It is provided that there is a gap between one blade end of at least one blade of at least one of the member blade rows and at least one of the two main flow path boundaries.

Abstract: A gas turbine includes a compressor, a combustor, and a turbine. The turbine includes a honeycomb seal disposed so as to be secured to a casing side in a clearance between the casing and turbine blades rotating around a rotating shaft and a seal fin that is provided on an end face of each of the turbine blades facing the honeycomb seal. The seal fin extends in a direction perpendicular to the rotating shaft. The honeycomb seal is formed by a plurality of corrugated sheet metals overlapped with each other at walls of nodes thereof and the walls of the nodes are blazed with each other. Each of the corrugated sheet metals has trapezoids formed in alternating fashion. A longer direction of each wall of the nodes of the honeycomb seal is angled with respect to the rotational direction of the turbine blades.

Abstract: A spar cap for a rotor blade of a wind turbine is disclosed. The rotor blade includes a blade root and a blade tip, leading and trailing edges, pressure and suction sides, and at least one spar cap configured on an internal surface of either or both the pressure or suction sides. The spar cap includes one or more layers of a first material and a second conductive material contacting at least one of the layers of the first material. Further, the conductive material is different than the first material. Thus, the conductive material is configured with the first material so as to create an equipotential spar cap.

Abstract: A fan is provided, including a driving member, a fan bracket, a main fan and a main cover. The fan bracket is assembled with the driving member. The main fan is disposed on a first connecting portion of the fan bracket. The main cover is disposed on a second connecting portion of the fan bracket. An airflow space is formed between the main fan and the main cover. The main cover is formed with a first wind-guiding cover. Thereby, when the driving member drives the main fan to rotate, air can be inhaled through the first wind-guiding cover into the airflow space, and air will be exhaled toward a periphery of the airflow space by using a guidance of the first wind-guiding cover.

Abstract: A blade row group arrangeable in a main flow path of a fluid-flow machine includes N adjacent member blade rows firmly arranged relative to each other in both a meridional direction (m) and a circumferential direction (u). A relative secondary passage length (v?) and a relative secondary passage width (w?) each increase at least in one part of the area between the mean meridional flow line (SLM) and at least one of the main flow path boundaries (HB) towards the main flow path boundary (HB).

Abstract: An exemplary gas turbine includes a rotor unit, a tie-bolt, a cooling air pipe, and a clamping member. The rotor unit includes rotor blades and rotor disks. The rotor blades are arranged on outer circumferential surfaces of the rotor blades. The tie-bolt extends along the central axis of the rotor unit through the rotor disks and fastens the rotor disks. The cooling air pipe has the tie-bolt arranged therethrough and forms a ring-shaped cooling air flow path in an internal space thereof with the tie-bolt through which a cooling air is passed. The clamping member is arranged in the ring-shaped cooling air flow path so as to support the tie-bolt with respect to the cooling air pipe.

Abstract: A turbine engine in which an air flow circulates from upstream to downstream, or for an aircraft, including a rotary shaft extending axially and a de-oiling tube mounted to be rigidly connected to and on the inside of the shaft by an upstream fixing mechanism including: a first inner dog clutch extending on an inside from the shaft, a second dog clutch extending on an outside from the de-oiling tube, which is longitudinally aligned with the first dog clutch and positioned downstream of the first dog clutch, and an anti-rotation longitudinal locking latch extending between the rotary shaft and the de-oiling tube to prohibit rotation of the second dog clutch of the de-oiling tube relative to the first dog clutch of the rotary shaft.

Abstract: An exhaust-gas turbocharger (1) with a bearing housing (2), a shaft (3) mounted in the bearing housing (2), a compressor wheel (5) arranged on the shaft (3) and a turbine wheel (4) arranged on the shaft (3), a housing component (7) which surrounds the compressor wheel (5) or the turbine wheel (4), and a sealing ring (14) between the bearing housing (2) and the housing component (7), wherein the sealing ring (14) is, in order to impart its sealing action, compressed in a direction perpendicular to the shaft (3).

Abstract: A blade device for a mixing propeller has a rocking shaft and a plurality of blade units. The blade unit is made of a flexible material and is installed on the rocking shaft via a fixing groove. The blade unit includes a horizontal propelling flexible blade and a vertical uplifting flexible blade. The fixing groove has a horizontal section and a vertical section. One end of the horizontal propelling flexible blade is inserted in the vertical section of the fixing groove while the other end of which is kept free so that it can swing back and forth. One end of the vertical uplifting flexible blade is inserted in the horizontal section of the fixing groove while the other end of which is kept free so that it can swing back and forth.

Abstract: A gas turbine engine (30) comprising a rear cowl (38) defining an exhaust aperture (40) and a motive system. The rear cowl (38) comprises at least one panel (42) and the motive system is operable to selectively move the panel (42) between deployed and stowed configurations by rotation of the panel (42) about an axis substantially parallel to the main rotational axis of the engine (30). This alters the area of the exhaust aperture (40).

Abstract: To provide a turbo compressor rotatable at high speed that is capable of being downsized, and of being suppressed in performance deterioration at low speed rotation. A turbo compressor includes a housing, a rotating shaft, a motor, a compressor mechanism, and a support section. The support section includes at least three rollers on the rotating shaft, roller shaft portions on the rollers, and a roller bearing portion for supporting the roller shaft portions. The rollers and the rotating shaft respectively have a drive transmission portion for drive transmission from the rotating shaft to each of the rollers, and the drive transmission portion of the rollers has a diameter larger than a diameter of the drive transmission portion of the rotating shaft.

Abstract: A blade cascade for a turbomachine, having a number of blades (11, . . . 14; 21, . . . 25; 31, . . . 37) which include a monocrystalline material, each blade having a crystal orientation value (|?|), which is dependent on a crystal orientation of the monocrystalline material of the blade; the crystal orientation values of first blades (11, . . . 14) being less than a first limiting value and the crystal orientation values of second blades (21, . . . 25; 31, . . . 37) being at least equal to the first limiting value; and the blade cascade having at least one first sector (1), which includes at least three successive first blades (14, 12, 11, 13), and having at least one second sector (2+3; 2?+3?; 2?+3?), which includes at least three successive second blades (22, 21, 23, 24, 25; 31, 34, 36, 37, 33, 32, 35).

Abstract: A rotor drive for a tail rotor of a helicopter is provided. The system includes a stator and a rotor mounted to the stator with a rotatable central carrier. Rotor blades are radially attached to the rotatable central carrier and each of the rotor blades is pivotable about their respective radial central axis for variation of blade pitch. At least one permanent magnet is provided on each rotor blade. A plurality of electromagnets is provided on the stator close enough to allow inductive interaction between the plurality of electromagnets and the at least one permanent magnet on each rotor blade. The permanent magnets are offset from the radial central axis in a direction perpendicular to the rotation plane for individual pitch control of the rotor blades by individual control of electric supply to the electromagnets.

Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: A marine propeller has an outer hub having a central axis and a blade having a blade root attached to the outer hub and extending radially outward from the outer hub toward a blade tip. The blade has a leading edge and a trailing edge. The propeller has a diameter between about 15 inches and about 17 inches and a pitch between about 14 inches and about 24 inches. The blade has a progressive rake angle such that a first local rake angle at the blade root is less than a second local rake angle at the blade tip. A combination of the diameter, pitch, and progressive rake angle provides a marine vessel to which the marine propeller is coupled with minimum drag while the marine vessel is operating at less than a maximum vessel speed. A method of designing a propeller is also disclosed.

Abstract: A steam turbine stationary blade is configured to be a stationary blade structure having a hollow structure. The steam turbine stationary blade is provided with a slit disposed on a stationary blade surface. The pressure of a stationary blade hollow is reduced to suction a liquid film through the slit for removing the liquid film formed on the stationary blade surface. An opening portion of the slit is covered with a sheet in a meshed pattern formed of a fine mesh thereby reducing an accompanied steam amount so as to effectively remove the liquid film.

Abstract: A drive pod of a watercraft such as a boat may be designed to break off the hull of the boat in the event of an underwater collision involving the drive pod. A shaft assembly that transmits power from the engine in the hull to blades or a jet in the drive pod is designed to break at a precise point so that seals in the hull and seals in the drive pod are protected from damage. The shaft assembly may include an axial blind hole with an undercut at a bottom of the blind hole. A pin may be inserted to reinforce the shaft above the undercut.

Abstract: A centrifugal fan includes a fan frame and a fan impeller received in the fan frame. The fan frame has at least one air inlet and at least one air outlet respectively formed on two sides of the fan frame. The fan impeller has a hub, an extension section outward extending from the hub and multiple blades disposed on the extension section. Each blade has a front end and a rear end. The rear ends of the blades are annularly arranged to together define a virtual geometrical configuration. A flow guide space is defined between the virtual geometrical configuration and the hub. A chord length is defined between the front and rear ends of the blade. The flow guide space has a width larger than or equal to the chord length so as to thin the centrifugal fan and enhance the performance thereof.

Abstract: A turbomachine aerofoil blade has an aerofoil body portion and a dovetail root fixing at the base of the aerofoil body portion which slides, in use, into a correspondingly shaped slot of a rotor of the turbomachine. The dovetail root fixing has a neck portion, and support flanks engage with matching angled surfaces of the slot under centrifugal loading of the aerofoil blade to support the aerofoil blade on the rotor. The neck portion is shaped such that a rotational adjustment of the aerofoil blade relative to its angular position when supported under centrifugal loading is needed to provide adequate clearance at the neck portion to allow the dovetail root fixing to slide into the slot. On centrifugal loading the engagement of the support flanks with the matching angled surfaces of the slot forces a reversal of the rotational adjustment and reduces the clearance at the neck portion.