Abstract: An impeller for a pump is disclosed herein. The impeller can include a hub having a fixed end and a free end. The impeller can also have a plurality of blades supported by the hub. Each blade can have a fixed end coupled to the hub and a free end. The impeller can have a stored configuration and a deployed configuration, the blades in the deployed configuration extending away from the hub, and the blades in the stored configuration being compressed against the hub.

Abstract: The present invention is an improved wind turbine comprising: a wind turbine wheel having a hub, a rim and a cable extending between the hub and the rim; a set of airfoils rotatably carried by the cable and disposed between the hub and the rim; a cinch attached to the cable and disposed between adjacent airfoils; and, an upturned section included in at least one airfoil in the set of airfoils and disposed at a trailing edge of the airfoil wherein each airfoil has a different angle of attack relative to an adjacent airfoil.

Abstract: A vacuum pump and a temperature control device are capable of preventing, with a simple configuration, overheating and overcooling of a pump that are caused due to abnormality in a temperature sensor used to control a heater or a water-cooling solenoid valve that is provided to prevent the deposition of products. Problems such as overheating and overcooling of a heater can be avoided in a case where a temperature sensor system fails and consequently the measured temperature continues to be constant between the upper limit and the lower limit. TMS function controls the measured temperature of the temperature sensor to a target temperature. Thus, if an application such as a target to be heated or a heater capacity is identified, the same cycles of turning ON/OFF of the heater or the water-cooling solenoid valve are repeated, and the upper limit of the time in which the ON/OFF state is sustained continuously is determined.

Abstract: An airfoil assembly for a turbine engine can include an airfoil having an outer wall bounding an interior, and an insert located within the interior with a space between the insert and airfoil outer wall. A cooling hole can pass through the insert with an outlet fluidly coupled to the space between the insert and outer wall.

Abstract: Cooling a torque probe involves an elongated sleeve extending along a sleeve axis between a first sleeve end and a second sleeve end. The sleeve is mountable about the torque probe to define a flow passage between an inner surface of the sleeve and an outer surface of the torque probe. The flow passage is in fluid communication with a flow passage inlet of the sleeve and with a flow passage outlet of the sleeve spaced apart along the sleeve axis from the flow passage inlet. A cooling fluid is configured to flow into the flow passage via the flow passage inlet, through the flow passage along the outer surface of the torque probe to cool the torque probe, and out of the flow passage via the flow passage outlet.

Abstract: An airfoil for a gas turbine engine is provided that includes a first portion formed from a first plurality of plies of a ceramic matrix composite material and defining an inner surface of the airfoil, as well as a second portion formed from a second plurality of plies of a ceramic matrix composite material and defining an outer surface of the airfoil. The first portion and the second portion define a non-line of sight cooling aperture extending from the inner surface to the outer surface of the airfoil. In one embodiment, a surface angle that is less than 45° is defined between a second aperture and the outer surface. A method for forming an airfoil for a gas turbine engine also is provided.

Abstract: The present embodiments set forth a blade including an airfoil, the airfoil including a tip cap, a pressure sidewall and a suction sidewall extending axially between corresponding leading and trailing edges and radially between the base and the tip cap. The blade, including the airfoil and base, being formed in at least two airfoil parts, each of the two airfoil parts including contacting edges engaging each other respective contacting edges, the contacting edges defining a joint for preloading each of the at least two parts with each other and with the base. The at least two airfoil parts forming the airfoil being retained to each other by an interference fit at the joint. The interference fit providing frictional damping of vibrations in the blade during blade operation.

Abstract: A thermal shielding arrangement for a turbine probe extending through an exhaust case and a turbine housing of a gas turbine engine comprises a sleeve having a radially inner end fixedly mounted to the turbine housing and a radially outer end floatingly received in a probe boss on the exhaust case. The radially outer end of the sleeve opens to an air cavity between the exhaust case and a surrounding engine nacelle to allow for air circulation around the probe.

Abstract: An aircraft rotor system including a hub having a hub axis about which the hub is configured to rotate; a plurality of rotor blades configured to extend from the hub and rotate about the hub axis, at least one of the rotor blades rotatable about a respective pitch change axis; wherein the hub is configured to be rotated about the hub axis only by the plurality of rotor blades. Another aspect includes a method of operating the rotor system.

Abstract: A bracket assembly includes a first bracket arranged along a damping axis and having a clevis body, a second bracket, and a vibration isolator including an elastomeric body. The second bracket is arranged along the damping axis and has a clevis portion and a mount portion. The clevis portion slidably receives the clevis body of the first bracket. The elastomeric body is arranged axially between the first bracket and the second bracket and is fixedly arranged between the clevis portion of the second bracket and the clevis body of the first bracket through an on-axis load path and through an off-axis load path extending through the bracket assembly. Actuator arrangements and methods of damping vibrational forces are also described.

Abstract: The invention is a device (1) for cooling a power electronic system (EP) comprising at least one power electronic component (2) mounted on at least one circuit board (3), the cooling device (1) comprises a hose (4) for circulating a flow (5) at an ambient temperature. The cooling device (1) comprises a first heat exchange surface (6) that is thermally connected to the power electronic components (2) and at least one second heat exchange surface (7). The second heat exchange surface (7) is for heat exchange with the flow (5) circulating through the hose. The second heat exchange surface (7) is fitted inside the circulation hose (4) to remove heat by convection with the circulating flow (5). The second heat exchange surface (7) is thermally connected to the first heat exchange surface (6).

Abstract: A wind turbine (1) comprising a tower (2), a nacelle (3) and a hub (7) is disclosed. The hub (7) comprises a blade carrying structure (4) with one or more wind turbine blades (5) connected to thereto. Each of the wind turbine blades (5) defines an aerodynamic profile having a thickness which varies along a length of the wind turbine blade (5). Each of the wind turbine blades (5) is connected to the blade carrying structure (4) via a hinge (6) at a hinge position of the wind turbine blade (5), each wind turbine blade (5) thereby being arranged to perform pivot movements relative to the blade carrying structure (4) between a minimum pivot angle and a maximum pivot angle.

Abstract: A rotor blade attached to a rotor shaft rotatable around an axis includes: a blade body extending in a radial direction with respect to the axis and having a blade-shaped cross section orthogonal to the radial direction; a shroud provided at an end of the blade body on a radial outer side, and a seal fin protruding from the shroud toward an outer circumferential side, and the seal fin includes: a seal fin body extending in a plate shape in a circumferential direction; and a reinforcing portion provided on at least one plate surface of the seal fin body to increase a thickness of the seal fin, the reinforcing portion gradually increasing in dimension in the radial direction toward the center in the circumferential direction.

Abstract: An impeller for a pump is disclosed herein. The impeller can include a hub having a fixed end and a free end. The impeller can also have a plurality of blades supported by the hub. Each blade can have a fixed end coupled to the hub and a free end. The impeller can have a stored configuration and a deployed configuration, the blades in the deployed configuration extending away from the hub, and the blades in the stored configuration being compressed against the hub.

Abstract: A transitioning wind turbine for land or offshore use having a tower base; a wind turbine tower attached to the tower base; a wind turbine attached to the wind turbine tower having a hub and an outer perimeter with spokes disposed between the hub and outer perimeter; a set of vanes carried by the spokes; a generator configured to engage the outer perimeter of the wind turbine and convert a rotational energy of the outer perimeter into power; a lifting tower having a pivot disposed at a proximal end of the lifting tower; a cable attached between the lifting tower and the wind turbine tower; and, wherein the lifting tower is configured to transition from the upright position to the tilted position as the wind turbine tower transitions between the horizontal position to the vertical position.

Abstract: Provided is a method, computing system, and computer program product for reducing floating wind turbine loads induced by ocean waves by adjusting a blade pitch angle of at least one rotor blade of a floating wind turbine to minimize a moment imbalance at a platform top of the floating wind turbine caused by ocean wave activity.

Abstract: An exemplary section of a gas turbine engine according to this disclosure includes, among other things, a first array of airfoils including a first number of airfoils, and a second array of airfoils downstream of the first array of airfoils. The second array includes a second number of airfoils. The second number of airfoils is at least 1.19 times the first number of airfoils thereby providing a predetermined modal.

Abstract: A turbofan gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure rotationally support a fan shaft. A fan rotor bearing support structure extends radially inward from the front center body and at least partially supports the bearing structure. The fan rotor bearing support structure includes a passage that communicates buffer supply air from a hollow strut to the bearing structure.

Abstract: An airfoil has a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib extends from the first side to the second side and partitions an internal core cavity into a forward cavity and an aft cavity. A baffle is disposed in the forward cavity and has a showerhead array of impingement orifices adjacent the leading end of the airfoil wall. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has an inlet orifice through the inner portion of the airfoil wall, an array of pedestals, and at least one outlet orifice through the outer portion. The inlet orifice opens to the forward cavity at a location aft of the showerhead array of impingement orifices.

Abstract: The invention relates to a cooling device (21) extending circumferentially around a turbine engine casing (1), such as, for example, a turbine casing (7), comprising a support (24) extending axially and intended to be attached to the casing (18), at least one cooling tube (23) extending circumferentially, at least one attachment member (25) comprising a radially inner portion (36) at least partially surrounding the tube (23), and a radially outer portion (37) attached to the support (24), the radially outer portion (37) of the attachment member (25) being attached to the support (24) through connecting means (30) formed by L-shaped sheets.