Abstract: A fan of an aircraft engine is provided with a rotating fan rotor for feeding air aftward as a spiral flow and a stator vane for rectifying the spiral flow to be an axial flow. The fan stator vane is provided with a hub end portion extending radially relative to a rotating axis of the fan rotor and a tip end portion leaning toward a suction side. Leading edges of the hub end portion and the tip end portion have sweepback angles of from 27 degrees to 33 degrees relative to a radial direction defined by the rotating axis.

Abstract: A turbine blade includes an airfoil having opposite pressure and suction sidewalls joined together at opposite leading and trailing edges and extending longitudinally from root to tip. A plurality of independent cooling circuits are disposed inside the airfoil correspondingly along the pressure and suction sidewalls thereof. Each circuit includes an inlet channel extending through the dovetail. One of the circuits includes multiple longitudinal channels separated by corresponding perforate partitions each including a row of impingement holes for cascade impingement cooling the inner surface of the airfoil.

Abstract: A method facilitates assembling a rotor assembly for gas turbine engine. The method comprises providing a first rotor blade that includes an airfoil, a platform, a shank and a dovetail, coupling the first rotor blade to a rotor shaft using the dovetail, and coupling a second rotor blade to the rotor shaft such that a shank cavity is defined between the first and second blades. The method also comprises inserting a seal pin into the horizontal platform seal pin slot such that a gap defined between the first and second rotor blade platforms are substantially sealed wherein the seal pin includes a first end, a second end and a substantially cylindrical body extending therebetween and sized to frictionally engage the slot, wherein at least one of the first and second ends has a cross-sectional area that is smaller than a cross-sectional area of the body.

Abstract: A tube-type vortex reducer conducts cooling air in a compressor (1) of a gas turbine. Radial secondary air tubes (2) are arranged in a disk interspace (5) and attached to a compressor disk (3) with their radial outward end sections. The end sections of the secondary air tubes (2) are attached to a separate carrier ring (6), which is connected to a compressor disk (3).

Abstract: An axial flow fan. The axial flow fan includes an impeller, an annular structure, and a plurality of connecting elements. The impeller has a plurality of blades, arranged radially. Each blade has an outer periphery. The outer periphery has a top portion. The annular structure is attached to the top portion of the outer periphery of each blade. Each connecting element respectively connects each blade to the annular structure.

Abstract: A compressor for a gas turbine has, on the surfaces of its components, in particular of its blading, a coating for protecting the surfaces from erosion. The coating has at least two layers or a plurality of pairs of layers formed from amorphous carbon or a plasma polymer, the layers having an inherently high hardness, and the outermost layer of the coating having hydrophobic properties. Furthermore, the hardness of an inner layer of a pair of layers is higher than the hardness of an outer layer. The coating is particularly suitable for the avoidance of drop impingement erosion caused by liquid drops, erosion caused by solid particles, such as ice, and contamination caused by deposition of dust particles and constituents which are dissolved in liquids. The coating prolongs the service life of the components and increases the power of the turbine.

Abstract: An aerofoil 1 includes cooling channels 2, 3, 4, 5 with transfer passages 8 between adjacent channels 2, 3, 4, 5. In normal operation, the constriction in each cooling channel 2, 3, 4, 5 ensures direct through coolant airflow in the direction of arrowheads A. However, when a channel 4 is blocked by a blockage 9 airflow in adjacent channels 2, 5 is forced through the transfer passages 8 in order to provide airflow in the blocked channel 4 and facilitate cooling. This blocked channel airflow is in the direction of arrowheads B. Generally, the cross-section of the transfer passages 8 is determined for conformity with the outlet 7 cross-section of the channel 4 in order to achieve substantial coolant flow balance across the coolant channels 2, 3, 4, 5 of the aerofoil 1.

Abstract: A wind machine comprises a plurality of fabrics that are removeably installed on a rotatable carrier. The carrier axis of rotation may be either horizontal or vertical. The carrier has pairs of first and second arms that support opposite ends of a fabric net. Side strands of the net may be reinforced. Each net has a loop that is supported on one carrier arm and a piece of material that is supported on the second carrier arm. The fabric piece of material has holes that receive associated studs on the carrier second arm, which is turnable. By turning the carrier second arm, a tension is imparted to the fabric. The carrier second arm is lockable to maintain the tension. Multiple panels are connected to the net for pivoting between closed and open positions. The panels resist the wind when they are in the closed position.

Abstract: In an emergency cooling system (17) for a component (1) which is subject to thermal load in operation, in, e.g., a turbine, the component (1) has a wall (3) which, in operation, is acted on by heat on a first wall side (14) and is acted on by a flow of cooling fluid (11) on a second wall side (15). The wall (3) has at least one emergency cooling opening (12) which is closed off by a plug (16) and through which cooling fluid flows from the second wall side (15) to the first wall side (14) when the plug (16) is absent. The plug (16) is designed so as to melt at a predetermined temperature. The plug (16) is a body which is produced separately from the component (1), the plug (16) being inserted into the emergency cooling opening (12), in which it is connected to the component (1).

Abstract: A starter air valve assembly includes a valve body, a flow control valve, a rate control servo mechanism, and a valve actuator. The valve body defines a flow passage having at least an inlet port and an outlet port. The valve is disposed at least partially within the flow passage and is moveable between an open position and a closed position. The rate control servo mechanism is adapted to receive pressurized fluid and is configured, upon receipt thereof, to supply a controlled flow of the pressurized fluid. The valve actuator is coupled to the valve and is in fluid communication with the rate control servo to thereby receive the controlled flow of the pressurized fluid. The valve actuator is configured, upon receipt of the controlled flow of the pressurized fluid, to move the valve between the closed position and the open position at a substantially controlled rate.

Abstract: A cooled turbine shroud assembly includes a first cooling path and a second cooling path adapted to provide shroud impingement air at different pressures to enhance efficiency. The cooling air is preferably acquired from a common source of secondary air. In one aspect the assembly, a shroud support supports a shroud ring and the cooling paths are separated in part by a flexible seal.

Abstract: A rotor blade is provided having a hollow airfoil with a cavity and an attached root. The root has a leading edge conduit, at least one mid-body conduit, and a trailing edge conduit. Each conduit has a centerline. The leading edge conduit includes an inlet having a forward side, a suction side, and a pressure side that diverge from the centerline of the leading edge conduit, and an aft side. Each of the mid-body conduits includes an inlet having a suction side and a pressure side that diverge from the centerline of the mid-body conduit, and an aft side and a forward side. The trailing edge conduit includes an inlet having a suction side and a pressure side that diverge from the centerline of the trailing edge conduit. The trailing edge conduit inlet further includes a forward side and an aft side.

Abstract: A gas turbine engine rotor stack includes one or more longitudinally outwardly concave spacers. The spacers may provide a longitudinal compression force that increases with rotational speed.

Abstract: A ceiling fan blade cover for positioning over a fan blade. The cover has a covering portion and a plurality of strategically positioned adhesive strips. The covering portion is wrapped around the blade, and the adhesive strips adhere the cover to itself around the blade. A perforated strip along the cover splits the cover longitudinally to allow the cover to be easily removed from the blade.

Abstract: A wind energy machine has four rotor chambers formed by perpendicular walls. Each rotor chamber has an intake portion, a reversal portion, a parallel portion, and an exhaust portion. Air flow is reversed in each chamber for every 90 degrees of rotation, such that the intake portion becomes an exhaust and the exhaust portion becomes and inlet.

Abstract: A propeller hub assembly having a through-hub exhaust propeller hub characterized by an interior overlap zone defined by the composite interior dimensions of a selected number of conventional propeller hubs and optionally fitted with a removable exhaust ring and/or sized ventilation plugs. The hub assembly of this invention includes specially designed driver adaptors for insertion in the overlap zone of a universal propeller hub and accommodating corresponding conventional OEM factory thrust washers normally used in the conventional propeller hubs. The overlap zone design facilitates installation of the propeller hub assembly on any conventional lower unit outdrive utilizing the OEM factory thrust washers and corresponding driver adaptors. The exhaust ring and sized ventilation plugs facilitate optimum engine exhaust porting through the hub assembly for various applications, such as racing and other high performance operation.

Abstract: A steam turbine that can effectively operate with the steam at the higher temperatures, while maintaining the strength of turbine constituent components despite the high steam temperature of the steam is provided. The steam turbine includes a casing, a rotor, a plurality of turbine stages, a steam pass, a nozzle box, and a cover plate. The rotor is rotatably installed in the casing. The turbine stages are disposed in the turbine, at least one of the turbine stages including a turbine nozzle and including a moving blade that is fixed to the rotor. The steam pass includes the turbine stages. The nozzle box is placed in a space between the casing and the rotor for providing a heated steam into the steam pass. The cover plate is arranged along an outer surface of the nozzle box.

Abstract: A turbine engine shroud segment comprises a body including an outer surface from and along which a segment projection extends away from and in an axial direction. The segment projection includes circumferentially spaced apart segment support surfaces. A shroud hanger comprises a body including an inner surface from and along which a hanger projection extends in an axial direction. The hanger projection includes circumferentially spaced hanger bearing surfaces. In a circumferential turbine engine shroud assembly of shroud segments and hangers, a shroud hanger is assembled between a pair of adjacent shroud segments separated by an axial interface. The hanger projection is in juxtaposition with the interface, and respective segment support surfaces and hanger bearing surfaces are in registry.

Abstract: A gas turbine stator including at least a first injector providing a passage for a main cooling air stream into a pressurized chamber. An evacuation mechanism discharges air coming from an internal labyrinth gland of a first cavity towards a lower-pressure second cavity. A second injector evacuates the air contained in the second cavity towards a main duct. The stator further includes a third injector designed to generate an overpressure close to the internal labyrinth gland in the pressurized chamber.

Abstract: An integrated propulsion and guidance system for a vehicle includes an engine coupled to an impeller via a driveshaft to produce propulsive force. The impeller includes a hub and a plurality of blades, including at least one control blade pivotably mounted to the hub. A control system provides a control signal to a magnetic actuator to adjust the blade pitch of the control blades as the blades rotate about the hub. The change in blade pitch produces a torque on the driveshaft that can be used to control the heading of the vehicle.