Abstract: A bearing assembly for a wind turbine includes a bearing housing and a bearing surface defining a passageway configured to receive a shaft. The bearing surface includes a stationary portion and a movable portion, the movable portion being defined by a movable member coupled to the bearing housing. The movable member is movable between a first position, wherein the movable portion is flush with the stationary portion such that the bearing surface is smooth, and a second position wherein the movable portion is spaced from the stationary portion to define a fluid cavity in the bearing surface. A method of operating a plain bearing assembly includes operating the plain bearing assembly as a hydrostatic plain bearing during low dynamic conditions and operating the plain bearing assembly as a hydrodynamic plain bearing during high dynamic conditions.

Abstract: A blade retainer clip for retaining a foot of a turbine blade in a shoe of a turbine disc of a turbine wheel includes: a clip shank that fits into a mating slot in the blade foot; a protuberance along a central portion of the clip shank that fits into a mating recess along the mating slot in the blade foot; a clip heel on one end of the clip shank that engages a heel of the blade foot and a heel of the disc shoe that expands radially from at least opposite sides of the clip shank; and a clip toe that extends beyond a toe of the disc shoe that is deformable to contact at least the toe of the disc shoe.

Abstract: A vane includes a composite airfoil having one or more pockets and one or more spars received therein respectively. The spars extending radially away from a bridge of a vane mount supporting airfoil. The spars may be integrally formed with the bridge. The spars may be adhesively bonded to the composite airfoil within the pockets. A passage may extend between an airfoil base and an airfoil tip. A gas turbine engine annular fan frame includes an annular row of the composite outlet guide vanes extending radially between and connecting radially inner and outer rings of the fan frame.

Abstract: An exemplary axial flow steam turbine is disclosed which includes a motor, a turbine casing and at least first and second turbine stages, with the second turbine stage being located adjacent to and downstream from the first turbine stage. A radially outer static diaphragm ring of the second turbine stage includes an annular axial extension extending in an upstream axial direction and carrying a circumferential tip sealing device which cooperates with shrouds of a circumferential row of moving blades of the first turbine stage. An upstream end of the annular axial extension is axially spaced from a radially outer static diaphragm ring of the first turbine stage such that a circumferential passage is defined between the upstream end of the annular axial extension and the radially outer static diaphragm ring of the first turbine stage. Solid particles are diverted from steam flow by a circumferential passage during operation.

Abstract: A diffuser for decelerating a compressed gas, is provided, which includes a ring divided at circumferential positions around the ring into several arcuate sections, the complete ring is assembled from these sections. The ring defines one or more passages, the cross-section of which increases in the direction of flow of a fluid through the diffuser. The interface between adjacent sections is configured so that relative movement between the sections is prevented. The interface is configured to have a series of interlocking serrations along the axial length of the diffuser. In an embodiment, there are two arcuate sections involving two interfaces, and the peaks and troughs of the serrations of each of the two sections are arranged at an angle to a longitudinal axis of the diffuser. A small relative movement between the sections is achieved when the two angles at the two interfaces have opposite signs.

Abstract: An arrangement with a nacelle and a radiator of a wind turbine is provided. The nacelle is rotatable connected with the radiator. Thus, a joint component of the wind turbine is built by these elements. The connection is constructed and arranged such that the radiator is allowed to pivot between a first position and a second position. The radiator is locked in the first position and projects above the nacelle when the radiator is used to remove heat from the nacelle to the environment. When the radiator is locked in the second position the radiator is close to a side of the nacelle. Thus a minimum height of the joint component is achieved.

Abstract: A vane includes a composite airfoil having one or more outer pockets and one or more outer spars received therein respectively. The outer spars extending radially inwardly from an outer bridge of the outer vane mount outwardly supporting airfoil. The spars may be integrally formed with the bridge and adhesively bonded to the composite airfoil within the pockets with a passage extending between an airfoil base and an airfoil tip. A metallic leading edge tip may be disposed along the leading edge of the composite airfoil. A gas turbine engine annular fan frame incorporates the vanes in an annular row of composite outlet guide vanes extending radially between and connecting radially inner and outer rings of the fan frame.

Abstract: A bucket pair in a turbomachine includes a first bucket having an airfoil and a shank; a second adjacent bucket having a second airfoil and a second shank adjacent the first shank; a first axial slot in the first shank; and an elongated, straight damper pin adapted to seat in the first axial slot, the damper pin formed with slanted forward and aft end faces.

Abstract: An air cycle machine including a housing with a compressor housing portion and a turbine housing portion secured to one another by fasteners. The compressor and turbine housing portions each provide a surface. An insulator plate is provided between and engages the surfaces. The fasteners extend through circumferentially arranged holes in the insulator plate. The insulator plate has an axial width, an inner diameter and an outer diameter. The outer diameter to the inner diameter provides a first ratio of 1.19-1.21, and the inner diameter to the width provides a second ratio of 53-59. In one example, the insulator plate is a composite structure constructed from 9-12 carbon fiber laminations with each layer having directional carbon fibers oriented transversely relative to the carbon fibers of an adjacent layer.

Abstract: A tower type vertical axle windmill includes a tower portion. The tower portion has a plurality of layers and a plurality of wind turbines and a computer is used to open and close the walls of the tower portion. Each of the wind turbines includes a seat portion, an energy output assembly and a rudder assembly. The seat portion can carry other components. A circular platform is disposed on the base portion of the energy output assembly and is supported by bearings to enable it to turn around. A flywheel is disposed on the outmost portion of the blade module and can store the energy extracted from the wind and enhance the balance of the windmill. In addition, an output axle is connected with the circular platform and a generator.

Abstract: A fluid machine includes a non-streamline casing capable of forming a stable vortex street on a downstream side by internal and external flows, and an impeller disposed inside the casing. The casing has a vortex generator configured to form the vortex street on the downstream side. The vortex generator is provided with a phase control structure which regulates a phase of a vortex formation that fluctuates along a circumferential direction in a plane including a rear face of the casing and which clarifies a cell structure to be formed along the circumferential direction of the casing to fix, on a surface of the casing, respective positions of cells into a plurality of segmented regions arranged in the circumferential direction. The velocity of the internal flow is increased by the phase control structure.

Abstract: A device for improving performance of an aircraft with a propeller includes a constant torque blade setting device that slaves, automatically and independently, blade setting angles, respectively associated with blades of the propeller, to a constant reference control moment predetermined, for a desired propeller thrust value. The blade setting angles are intended to be applied on each blade such that torsion aerodynamic moments applied on blades stay roughly equal to the reference control moment regardless of the angular position of blades in the propeller plane. A corresponding method for improving performance of an aircraft includes the use of the constant torque blade setting device to slave blade setting angles to a constant reference control moment.

Abstract: High bypass ratio turbofan propulsion engines are designed with a two-step approach to surviving foreign object damage to the fan assembly. First, a containment system encircling the fan assembly to capture any part of a released fan blade in the event of damage occurring, and two in order to cope with the vibrations resulting from a rotating unbalanced fan assembly the support structure for the bearing of the rotating assembly is constructed with frangible parts to introduce a snubber gap to permit the rotating, unbalanced fan assembly and bearing to orbit thereby to reduce the resulting vibrations. However, in the case of very wide chord fan assemblies, the largest acceptable snubber gap is insufficient to reduce the induced vibrations.

Abstract: An elevator system for a wind turbine is provided. The elevator system comprises a suspension device and an elevator car. The elevator car is suspended to the suspension device wherein the suspension device is mountable to a mounting section of a nacelle of the wind turbine.

Abstract: An arrangement with a nacelle and an instrument bar is provided. The instrument bar is arranged on top of the nacelle. A rotational axis interacts with the nacelle and with the instrument bar. The rotational axis is constructed and arranged such that the instrument bar is allowed to pivot between a first position and a second position in reference to the top side of the nacelle. The instrument bar projects above the top side of the nacelle when locked in the first position, while the instruments are operated. The instrument bar is locked close to the top side of the nacelle in the second position to allow access to the instruments.

Abstract: A method of operating a compressor in an adaptive core engine is disclosed. The method comprises the steps of operating a front block compressor to increase pressure of a fluid to a first pressure ratio in a high-power mode operation; operating a rear block compressor coupled to the front block compressor such that the front block compressor and the rear block compressor operate at the same physical speed; closing a rear block stator vane located axially forward from the rear block compressor such that the flow of the fluid into the rear block compressor is substantially cut off; and keeping a blocker door opened such that substantially all of the fluid pressurized by the front block compressor flows through a bypass passage during the high-power mode operation.

Abstract: A joined rotor that includes a primary join and a locking device and a method for joining thereof is disclosed. The primary join includes a threaded boss that is inserted in a tapped cavity formed in an adjacent rotor section. The primary join is locked, so as to prevent unscrewing, by at least one locking member that is located partially in both first and second rotor sections. This arrangement enables the join to be locked at a desired torque point.

Abstract: A fan module with vibration-damping mounting includes a cooling fan, a support frame and a clip detachably fixing the cooling fan to the support frame. The clip includes a mounting portion fixed to the support frame, fixing portions supporting the cooling fan, and vibration reducing portions. Each of the vibration reducing portions is connected between a corresponding fixing portion and the mounting portion. The fixing portions are spaced from the support frame, to prevent a vibration of the cooling fan from being transferred to the support frame.

Abstract: The invention relates to a sectored distributor (112) for a turbomachine, including two coaxial platforms mutually connected by radial blades, the inner platform (130) being connected to an annular partition (138) for suspending an annular mounting (140) carrying elements (136) made of material subject to abrasion, this mounting sliding circumferentially on the partition and comprising a means engaging with means corresponding to the inner periphery of the partition to ensure radial restraint of the mounting on this partition.

Abstract: An annulus filler for mounting to a rotor disc of a gas turbine engine is provided to bridge the gap between adjacent blades. A first part is connectable to the rotor disc between adjacent blades. There is a separate second part that engages with the first part after connecting the rotor blades to the rotor disc. When installed, the filler is spaced from each blade by a respective clearance gap (G), and an operational configuration in which it contacts each of said blades. Engagement of the second part with the first part is effective to urge the first part from said installation configuration to said operational configuration and thus into blade contact. The first part may have a mounting region for connection to the rotor disc and allow, in said first step of said procedure, the mounting region to remain visible from a radially outer viewpoint.