Abstract: An externally supported foil with reversible camber and variable chord length is described that allows a thin foil of efficient deformed shape to generate lift equally on opposite angles of attack to a fluid flow. The foil is supported at the leading and trailing edges to ribs that are in turn connected to spanwise spars forming an external structure attachable to a body. The foil is held by leading edge hinge(s) and trailing edge elastic membrane(s) along the span or at the ribs. Membrane pretension keeps the foil taut while generating no lift when parallel to a flow. When rotated by an external mechanism to generate an angle of attack, the membrane stretches due to the differential pressures generated on the foil surface; thereby, passively increasing the chord length and camber. Rib cutouts dictate the deformed aerodynamic or hydrodynamic foil shape that then generates lift.

Abstract: There is provided a hydraulic pump startup control device in a hydraulic system, which avoids an overloaded state at startup to enable low-temperature, fast startup and maintaining of the temperature with low-cost means in order to improve low-temperature startability. A bypass path 19 is placed in parallel with a hydraulic main line from a hydraulic tank, and the downstream of the bypass path is made merged with the hydraulic main line. A bypass valve 3 that opens or closes the bypass path is provided in the bypass path, and a pressure sensor is provided in the inlet of a hydraulic unit in the hydraulic main line. Further, a control device 10 to which a pressure detection value in the hydraulic main line is input from the pressure sensor to open the bypass valve based on the pressure detection value upon startup of the hydraulic unit.

Abstract: Bolted together first and second flanges include bolts disposed through first bolt holes in the first flange. The bolts extend at least partially through second holes in the second flange. Bolt include bolt heads, threads, and shanks therebetween. Crushable spacers disposed around the shanks of a first plurality of the bolts and contacting and axially extending between the bolt heads and the first flange. Bushings disposed around a second plurality of the bolts and contacting and axially extending between the bolt heads and the second flange. A shank outer diameter may be smaller than a thread diameter and heat shrink tubing may be disposed around the bolt shanks of at least some of the spacers. First bolt holes may extend into an open annular slot on first flange and second holes may extend partially through a forward extending annular rail of second flange with rail received within slot.

Abstract: A balanced rotor of a turbine engine, having a rotor disc with a circumferential slot and a row of rotor blades mounted in the slot and a balance weight having a land which extends beneath the root of a blade and having a mass-adjustment protrusion extending from the land in a radial direction relative to the axis of the rotor component and which lies wholly between the blade root and an adjacent blade root.

Abstract: A turbocharger, comprising: at least one of a turbine housing, a bearing housing and a turbine wheel, wherein the turbine wheel is rotatably mounted about an axis and includes a guide apparatus with a plurality of guide vanes rotatably mounted in pivot bearings on a guide vane support, wherein the guide vanes influence the flow in a flow channel of the turbine housing; and a spring element, which moveably loads the guide apparatus in an axial direction against a wall of the turbine housing, and wherein the disc springs seal a displacement chamber provided with a displacement mechanism of the guide apparatus against the flow channel.

Abstract: The disclosed turbine engine includes a fan nacelle surrounding a fan and including an inlet arranged upstream from the fan. The inlet includes an inlet surface having a boundary layer flow. A flow control actuator is in fluid communication with the inlet surface. A boundary layer sensing device is associated with the inlet surface for detecting a boundary layer condition at the inlet surface. A controller is in communication with the flow control actuator and the boundary layer sensing device. The controller is programmed to command the flow control actuator in response to the boundary layer sensing device detecting an undesired boundary layer condition. In this manner, the flow control actuator generates a desired boundary layer condition.

Abstract: The present invention comprises a gas turbine engine with a compressor for generating compressed air, a turbine comprising upstream and downstream rows of vanes, vane carrier structure surrounding at least one row of vanes and plenum structure at least partially surrounding the vane carrier structure capable of impinging compressed air onto the vane carrier structure. The gas turbine engine further comprises fluid supply structure including first fluid path structure defining a first path for compressed air to travel to the plenum structure, second fluid path structure defining a second path for compressed air to travel toward the downstream row of vanes, and fluid control structure selectively controlling fluid flow to the first and second fluid path structures.

Abstract: A fixture assembly for securing at least one side rail to a shroud tile of a gas turbine is disclosed. The fixture assembly may include a first support member, a second support member, a first guide block and a second guide block. The first and second guide blocks may be formed from a material that has the same or a similar coefficient of thermal expansion as the material used to form at least one of the shroud tile and the at least one side rail. In addition, the first and second support members may be formed from a material that has a lower coefficient of thermal expansion than the material used to form the first and second guide blocks.

Abstract: A cooling structure of a turbine airfoil cools a turbine airfoil (10) exposed to hot gas (1), using cooling air (2) of a temperature lower than that of the hot gas. The turbine airfoil (10) includes an external surface (11), an internal surface (12) opposite to the external surface, a plurality of film-cooling holes (13) blowing the cooling air from the internal surface toward the external surface to film-cool the external surface, and a plurality of heat-transfer promoting projections (14) integrally formed with the internal surface and protruding inwardly from the internal surface. The turbine airfoil further includes a hollow cylindrical insert (20) which is positioned inside the internal surface of the turbine airfoil and to which the cooling air is supplied. The insert has a plurality of impingement holes (21) for impingement-cooling the internal surface (12).

Abstract: A micro-circuit cooling module for providing endwall cooling for a vane assembly in a gas turbine engine. The micro-circuit cooling module includes an outer perimeter rail, an upper plate and a lower plate defining a mixing chamber therein. A first plurality of spaced apart strip elements extend along a first direction in an upper channel of the mixing chamber, and a second plurality of strip elements extend along a second direction opposite to the first direction in a lower channel of the mixing chamber so that the first plurality of strip elements and the second plurality of strip elements form a criss-cross configuration. Air enters the module through metering holes in the lower plate and flows through the mixing chamber across the criss-cross elements in a turbulent manner and exits the module through slots in the upper plate.

Abstract: The tip portion of a blade of a gas turbine is repaired in-situ in the gas turbine without removing the blade from the turbine rotor disk. To facilitate the in-situ repair of the tip portion of the turbine blades, one or more access holes may be provided in the turbine shroud or blade outer air seal circumscribing the plurality of turbine blades extending radially outward from the turbine rotor dick.

Abstract: A simple system is provided to dramatically reduce the number of bird fatalities and injuries, as these are bird-kills that man should be able to do something about. Essentially, the inventive apparatus comprises one or more instantaneously inflatable mini-airbags on turbine blade leading edges which, in the “stowed position” are tightly conformally elastically wrapped around or juxtaposed to the turbine blade surface(s) and/or edges(s) thereby not affecting the blade's aerodynamic efficiency. The airbag(s) can be activated and restowed or recollapsed very rapidly, thereby not significantly negatively impacting the operational efficiency of the wind machine.

Abstract: A lighting and heating assembly is provided. The lighting and heating assembly is configured for mounting to an existing ceiling fan. The lighting and heating assembly includes a lighting assembly for distributing light and a heating assembly for providing heat to the air circulated by the ceiling fan. The lighting assembly is attachable to the ceiling fan and has the heating assembly detachably connected thereto, which allows the lighting assembly to be used without the heating assembly. Additionally, the lighting and heating assembly is adjustable such that the lighting assembly and/or heating assembly are repositionable at desired locations in relation to one another and the air flow generated by the ceiling fan.

Abstract: A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: Methods of moving a rotating device of a wind turbine during transportation or standstill are provided. The methods include securing at least one auxiliary device to a position and connecting the device to one or more shafts of the rotating device at transportation or standstill. The auxiliary device is able to store, generate and/or convert energy during transportation, transferring energy continuously from at least one auxiliary device to one or more shafts of the rotating device during transportation or standstill, and moving one or more shafts of the rotating device continuously or discontinuously from a position to another. Also provided is a nacelle for a wind turbine, an auxiliary device, a control system for controlling moving of a rotating device of a wind turbine nacelle during transportation of the nacelle and use thereof.

Abstract: A turbine is provided and includes a rotor, which is rotatable about a centerline thereof, a sensor to measure a condition at a point of measurement interest defined on the rotor at a radial distance from the centerline, a communication system by which condition measurements are transmittable from the sensor to a non-rotating recording system and a probe holder to secure the sensor and a portion of the communication system on the rotor proximate to the point of measurement interest.

Abstract: An exemplary center housing rotating assembly includes a turbine wheel; a compressor wheel; a center housing (510) that includes a through bore (515), extending from a compressor end to a turbine end along a bore axis; a bearing assembly (530) positioned in the bore where the bearing assembly includes an outer race (532) that includes keyways (535, 535?) extending from an axial end, the keyways radially inset from an outer diameter of the outer race; and a plate (570) attached to the center housing where the plate includes extending keys (578, 578?), each of the keys (578, 578?) being received by a respective one of the keyways (535, 535?) to restrict rotation of the bearing assembly in the bore. Various other exemplary devices, systems, methods, etc., are also disclosed.

Abstract: A seal carrier for a seal used between rotating and non-rotating components includes an arcuate sheet metal seal carrier body formed to include a stepped, conical configuration wherein an inner diameter at a forward end is larger than the diameter at an aft end, with plural stepped sections defined by alternating radial and axial portions between the forward end and the aft end. Each axial portion is adapted to carry a seal element, preferably a honeycomb seal. Mounting flanges are provided at the forward end and the aft end of the arcuate sheet metal seal carrier body to enable attachment to the non-rotating component.

Abstract: A retention system retains a turbine blade dovetail in a retention ring dovetail slot. The retention system includes a retention opening formed in the blade dovetail. A through hole is formed in the retention ring, wherein the through hole is positioned such that it is aligned with the retention opening when the dovetail is assembled in the dovetail slot. A connector is disposed in the through hole and engages the retention opening. In this manner, undesirable relative movement of parts can be reduced or eliminated, thereby preventing excessive wear.

Abstract: A thermal barrier/cooling system for controlling a temperature of an outer case of a gas turbine engine. The thermal barrier/cooling system includes an internal insulating layer supported on an inner case surface, the internal insulating layer extending circumferentially along the inner case surface and providing a thermal resistance to radiated energy from structure located radially inwardly from the outer case. The thermal barrier/cooling system further includes a convective cooling channel defined by a panel structure located in radially spaced relation to an outer case surface of the outer case and extending around the circumference of the outer case surface. The convective cooling channel forms a flow path for an ambient air flow cooling the outer case surface.