Abstract: The present invention relates to a propulsion unit comprising a pair of contra-rotating coaxial propellers, that are referred to as upstream (2) and downstream (3), the downstream propeller, forming a rotating reference frame, being mounted for rotation about a central member forming a stationary reference frame, and being provided with a device for changing the pitch of the blades, characterized in that the downstream propeller is supported by bearings arranged externally on the cylindrical central support, an upstream bearing (40) of which is arranged downstream of a device for changing the pitch of the blades of the upstream propeller, and in that said device for changing the pitch of the downstream propeller comprises a linear actuator (23) in the stationary reference frame with an element (235) that is able to move axially along the axis of the downstream propeller, the upstream bearing comprising an inner ring that is rigidly connected to the linear actuator and an outer ring that is rigidly connected t

Abstract: A hydraulic control device includes an oil pump for generating a hydraulic pressure by being rotated by power of a driving force source, a driving force source stopping unit that stops rotation of the driving force source when a predetermined condition holds, and a cut-off unit that cuts off transmission of the power from the driving force source to the oil pump when the driving force source rotates in a reverse direction as the rotation of the driving force source is stopped by the driving force source stopping unit.

Abstract: A method of controlling a floating-body wind turbine power generating apparatus including a wind turbine generator disposed on a floating body includes a pitch-angle increasing step of increasing a pitch angle of a blade of the wind turbine generator when the wind turbine generator is stopped, so that an aerodynamic braking force is applied to a rotor of the wind turbine generator. In the pitch-angle increasing step, a first change rate of the pitch angle of the blade in a first period during which the wind turbine generator is in an inclining motion toward an upwind side from a vertical direction due to sway of the floating body, is smaller than a second change rate of the pitch angle of the blade in a second period during which the wind turbine generator is in an inclining motion toward a downwind side from the vertical direction due to the sway of the floating body.

Abstract: A variable stator vane for a compressor guide vane is provided. The vane includes a blade and a pivot. The pivot includes an internal pivot element and a pivot cap. The blade and the internal pivot element are each made from a composite material. At least one contact surface of the pivot cap is metallic.

Abstract: This disclosure describes a removable flow control device which may be used in a rotating flow supply system in a gas turbine to optimize coolant flow by improving flow dynamics, reducing leakage of coolant, and reducing pressure loss in the flow supply system. The flow control device may be coupled to a blade and rotor assembly and may include a flow modifier for directing flow through a junction at which cooling channels intersect and are in fluid communication. The device may direct, control, meter, channel, or otherwise modify the flow of coolant, and may be coupled to the blade and rotor assembly independently of other blade components so that coupling and decoupling the flow control device does not require modification or de-stacking of the rotor assembly.

Abstract: Methods for positioning neighboring nozzles of a gas turbine engine are provided. A method includes assembling a first nozzle assembly. The first nozzle assembly includes a first nozzle and a first nozzle support structure. The method further includes assembling a second nozzle assembly. The second nozzle assembly includes a second nozzle and a second nozzle support structure. The method further includes adjusting the first nozzle assembly and the second nozzle assembly such that an engineering dimension between the first nozzle and the second nozzle is within a predetermined engineering tolerance, and joining the first nozzle support structure and the second nozzle support structure together.

Abstract: A gas turbine engine includes first and second shafts rotatable about a common axis. A first turbine section is supported on the first shaft. Second compressor and turbine sections are supported on the second shaft. The gas turbine engine includes a fan. A first compressor section is arranged in an axial flow relationship with the second compressor and the first and second turbines. A geared architecture operatively connects the first shaft and the fan. An inducer operative couples to the gear train.

Abstract: A foil assembly for a gas powered turbine includes a plurality of floating wall sectors arranged circumferentially about an axis defined by a flowpath. Each of the floating wall sectors includes a first flowpath strut component, a second flowpath strut component, a floating wall panel connected to the first flowpath strut component by a first clamp seal at a first axial joint and connected to the second flowpath strut component by a second clamp seal at a second axial joint, and a plurality of leading edge structures fore of the plurality of floating wall sectors. Each of the leading edge structures is configured to define a foil profile in conjunction with a first flowpath strut component of a first floating wall sector and an adjacent flowpath strut component of a second floating wall sector.

Abstract: Embodiments of the application disclose a fan and a mold for making a fan blade structure for the fan. An embodiment of the fan comprises a fan blade structure and the fan blade structure comprises a mounting ring and a plurality of fan blades provided on the mounting ring, wherein mounting ring and the fan blades are integrally formed. The mold comprises a mounting ring and a plurality of fan blades provided on the mounting ring, the mold comprising a cavity having a ring-shaped channel configured for forming the mounting ring and a plurality of fan blade channels configured for forming the plurality of fan blades, in order to integrally form the fan blade structure.

Abstract: A propulsion unit having reduced noise employs a rotor having a plurality of variable pitch blades. A tensioning joint mechanism is carried within each blade and a tension element is engaged by the tension joint mechanism. The tension element is configured to maintain tension between the blades in the rotor and the tensioning joint mechanism adapted to allow variation of pitch of the blades without altering tension in the tension element.

Abstract: The invention relates to a fan and a fan module, wherein the fan comprises: a fan hub which comprises a fan rotation axis to rotate in a predetermined direction, a plurality of fan blades comprising a lower end and an upper end, wherein each fan blade is attached with its lower end to the fan hub and extends radially outwardly from the fan hub, wherein each fan blade comprises a lower back sweep portion and an upper forward sweep portion, wherein a maximum ratio r/R of the lower back sweep portion is at least 0.90, wherein r is the local radius of a point of the fan blade edge, and R is the radius of the upper end of the fan blade.

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge. The airfoil extends to a tip. A tip pocket is formed in the tip and terminates prior to the trailing edge. A heat transfer augmentation device is formed in the tip pocket.

Abstract: Hydraulic systems and tools having an actuator that actuates a pump and a control valve are described. The pump transports fluid into a chamber to advance a piston in the chamber. The control valve is biased open and regulates flow of hydraulic fluid from the chamber to a reservoir. The actuator is operable in a first state in which the control valve is open, allowing flow of fluid from the chamber to the reservoir, and the pump is not pumping. The actuator can be operated in a second state in which the control valve is closed, restricting flow of fluid from the chamber to the reservoir, and the pump is not pumping. The actuator can be operated in a third state in which the control valve is closed and the pump is pumping fluid from the reservoir into the chamber in order to advance the piston.

Abstract: A pneumatic valve, in particular a pneumatic proportional pressure control valve includes a valve housing (3), in which a piston valve element (5) is guided in a guide (7) under the effect of an actuating device (9) and of a restoring device (11). The restoring device exerts a spring force and acts on the valve element (5) counter to the applied magnetic force (FB) of the actuating device (9). The valve element controls a media flow between a first media connection (13) and a second media connection (15) on the valve housing (3). With the actuating device (9), the valve element (5) establishes a media-conducting connection (17) between the respective media connections (13, 15), while allowing for the forces prevailing, on the basis of the applied pressures multiplied by the respective pressure-active surfaces, the spring force, the flow forces and the magnetic force.

Abstract: An object is to provide a variable-geometry exhaust turbine whereby it is possible to prevent deformation and damage to a nozzle support under a high temperature. A variable-geometry exhaust turbine includes: a nozzle mount, a nozzle support including a first end portion joined to the first surface of the nozzle mount, a nozzle plate including the first surface joined to the second end portion of the nozzle support 6 and supported so as to face the nozzle mount at a distance, and the opposite second surface facing an exhaust—as channel through which exhaust gas flows, and a plurality of nozzle vanes supported rotatably between the nozzle mount and the nozzle plate. The nozzle support is capable of tilting along a radial direction so as to absorb a relative displacement in the radial direction between the nozzle mount and the nozzle plate due to thermal expansion.

Abstract: Disclosed is a gas turbine engine including a compressor section and a turbine section. The gas turbine engine includes a gas turbine engine component having a first wall providing an outer surface of the gas turbine engine component and a second wall spaced-apart from the first wall. The first wall is a gas-path wall exposed to a core flow path of the gas turbine engine. The second wall is a non-gas-path wall. A cooling passageway is provided between the second wall and the first wall. The second wall has a trip strip provided thereon.

Abstract: A fluid-flow machine includes: a main flow path boundary and at least one row of relatively rotating blades with a gap existing between blade ends and the main flow path boundary. At least one secondary flow duct having one opening each is provided in the main flow path boundary at ends spaced apart in the flow direction, such that the secondary flow duct is connected to the main flow path via the two openings. The structural assembly has at least one support component and at least one insertion component. The support component includes a recess extending in the circumferential direction that receives the at least one insertion component such that the support component surrounds the at least one insertion component largely on its sides not facing the main flow path, and where the insertion component completely surrounds or forms at least one secondary flow duct.

Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. A core housing has an outer peripheral surface and a fan housing defining an inner peripheral surface. At least one bifurcation duct extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger is received within the at least one bifurcation duct.

Abstract: A flexbeam unit for a multi-blade rotor of a rotary wing aircraft, the flexbeam unit comprising a plurality of flexbeam elements defining a predetermined number of torsion elements that are connectable with associated rotor blades of the multi-blade rotor, at least one of the predetermined number of torsion elements comprising at least one flexbeam element having an associated longitudinal direction, the at least one flexbeam element comprising at least one twisted area in which the at least one flexbeam element is twisted in the associated longitudinal direction.

Abstract: A fan impeller includes a plurality of fan blade assembly members, each one of the fan blade assembly members respectively includes a metal ring bracket and a plurality of metal blades, one end of each one of the metal blades is respectively connected to the corresponding metal ring bracket and the plurality of metal blades of each one of the fan blade assembly members arranged radially to circumference the corresponding metal ring bracket. The metal ring brackets are configured to stack with each other and the metal blades are arranged in a radial centric row, a width of at least one portion of each one of the metal blades is not smaller than a distance between any two adjacent metal blades along a fan impeller circumferential direction. Accordingly, metal blades of a greater width can be densely arranged on the fan impeller.