Abstract: A compressor includes: an upper half casing having upper half casing parting planes; upper half diaphragms configured to be disposed on an inner circumferential side of the upper half casing and having upper half diaphragm parting planes; and upper half position regulating parts that regulate positions of the upper half casing and the upper half diaphragms. The upper half position regulating parts are fixed to at least one of the upper half casing and one of the upper half diaphragms, and have upper half abutting members at which upper half abutting surfaces, each of which comes into contact with an upper half casing recessed surface of the upper half casing and an upper half diaphragm recessed surface of the upper half diaphragm, are formed.

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 compressor includes a compressor impeller configured to rotate about an axis of rotation as intake gases flow along the compressor impeller. The compressor impeller includes an inducer and an exducer. The compressor impeller defines a first impeller end at the inducer and a second impeller end at the exducer. The second impeller end extends along a radial axis. The compressor further includes a compressor housing encasing the compressor impeller. The compressor housing defines a compressor volute. The compressor housing partially defines a diffuser in fluid communication with the compressor volute. The diffuser is elongated along a diffuser axis. The diffuser axis is obliquely angled relative to the axis of rotation. The diffuser axis is obliquely angled relative to the radial axis to minimize a turbulence of the intake gases flowing from the diffuser to the compressor volute.

Abstract: A machine having a rotor that is radially bounded at least in part by a containment assembly. The containment assembly may comprise a casing and a containment liner. The casing may have a radially inner surface facing a rotor of the machine. The containment liner may be formed form a plurality of panels bonded to the radially inner surface of the casing. The panels may form joints between adjacent leading and trailing panels relative to the direction of rotation of said rotor. At least one joint includes a portion of a trailing panel positioned radially outboard of a portion of the leading upstream panel.

Abstract: An assembly can include a shaft that includes threads and a free end that includes a shaft drive feature; a compressor wheel that includes a compressor wheel drive feature and a through bore that receives the shaft; and a nut that includes threads that mate the threads of the shaft.

Abstract: A turbine shroud assembly including an outer shroud arranged within a turbine and further comprising opposed extending portions. The turbine shroud assembly further including an inner shroud shielding the outer shroud from a gas flowing along a gas path within the turbine during operation of the turbine and comprising opposed first and second arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud for supporting the inner shroud from the outer shroud. The turbine shroud assembly further including a spline seal extending between the first and second arcuate portions and positioned between the inner shroud and the outer shroud. The turbine shroud assembly further including at least one of the inner shroud, the outer shroud and the spline seal including at least one protrusion for maintaining positive retention of the spline seal during non-operation of the turbine.

Abstract: The present disclosure concerns the detection of ice within a system. More specifically, but not exclusively, the disclosure concerns the detection of ice accretion within a gas turbine engine. The apparatus and method relies on heating a first region (38) of a component (44) and comparing the measured temperature of the first region (38) with a second temperature value, possibly measured at a distinct second region (40) of the component (44).

Abstract: A centrifugal blood pump prevents a shaft member from oscillating due to expansion of a pump housing resulting from pressurization of the blood. The centrifugal blood pump is manufactured by assembling a bottom member 21 and a lid member 22, and compressing them in a direction in which the bottom member 21 and the lid member 22 approach each other by a deformation amount along their outer circumferential walls. The lid member and the bottom member are joined while in the compressed state in order to create a preloading force between the shaft member and bearings to resist the expansion due to pressurization of the blood during use.

Abstract: Disclosed herein may be a sealing structure for turbines, and a turbine and a gas turbine having the sealing structure. The sealing structure is mounted on a sealing housing of a vane sealing assembly of the turbine to prevent combustion gas passing through a blade of the turbine from being drawn into an internal space between a disk of the turbine and the sealing housing. The sealing structure may include a mounting plate mounted to the sealing housing, and baffles which are provided on the mounting plate at positions spaced apart from each other and protrude toward the disk. Therefore, thanks to the sealing structure, turbulent currents are generated in the flow of combustion gas that passes through the turbine blade. The generated turbulent currents block space between the sealing structure and the turbine disk, thus preventing the combustion gas from flowing into the internal space.

Abstract: This document discloses a wall arrangement for a gas turbine engine, comprising: an annular wall comprising a plurality of circumferential wall segments, adjacent wall segments having opposing first and second end wall portions which define a separating gap therebetween, the gap including a saddle portion which faces radially outwards and comprises a first sealing face on the first end wall portion and a second sealing face on the second end wall portion; and, a longitudinal seal member having a curved sealing surface located within the saddle portion, wherein the curved sealing surface contacts either or both first and second sealing faces along the length of the saddle portion in use, wherein the seal member includes one or more axial restraint features which engage with a corresponding feature of the wall segment or a supporting structure thereof.

Abstract: An inlet for a turbofan engine, including an inlet wall surrounding an inlet flow path. The inlet wall extends axially from an upstream end to a downstream end adjacent the fan. The inlet wall has a shape defining a plurality of teeth circumferentially spaced around the inlet. The teeth extend axially and project radially inwardly toward the central longitudinal axis. A central portion of the inlet flow path has a cross-sectional dimension measured diametrically between opposed teeth, the cross-sectional dimension varying along the axial direction. The central portion defines a geometric throat at a minimum value of the cross-sectional dimension. The inlet wall is shaped so that the geometric throat is axially spaced from the upstream end and the downstream end. A gas turbine engine and a method of shielding tips of fan blades from impact by an object having a predetermined minimum dimension are also discussed.

Abstract: A component for a gas turbine engine includes a interleaved structural rib that extends between the first multiple of axial standoff ribs and the second multiple of axial standoff ribs. The second multiple of structural rib span segments that extend from the second sidewall, the first multiple of structural rib span segments interleaved with the second multiple of structural rib span segments to form an interleaved structural rib that extends between the first sidewall and the second sidewall.

Abstract: A blower apparatus includes a propeller fan configured to rotate about a rotational axis, and a bell mouth annularly disposed to surround the propeller fan as seen in a direction of the rotational axis of the propeller fan. The bell mouth includes a flare portion located downstream of the propeller fan The flare portion has at least one first part and at least one second part. The first part has a first inner circumferential surface region. The second part as a second inner circumferential surface region. A first length of the first part inner circumferential surface region in the direction of the rotational axis is greater than a second length of the second part inner circumferential surface region in the direction of the rotational axis.

Abstract: A turbine engine that includes an engine casing including a fluid supply plenum, a mating surface, and a nozzle supply passage and a cavity flow passage that both extend between the fluid supply plenum and the mating surface. The turbine engine further includes a turbine nozzle assembly including a mating band. The mating band includes an inlet scoop in flow communication with the nozzle supply passage. An interface is defined between the mating band and a first portion of the mating surface, and a band cavity is defined between the mating band and a second portion of the mating surface. The cavity flow passage couples the fluid supply plenum in flow communication with the band cavity.

Abstract: A magnetic energy convertor for vehicle axles includes an annular housing, a rotor shaft, a bearing, an annular bracket, a magnetized female adaptor, a magnetized male adaptor, a magnetized impeller assembly, and a fluid turbine system. The rotor shaft is rotatably mounted within the annular bracket by the bearing. The annular housing is radially mounted around the annular bracket. The magnetized female adaptor is terminally mounted to the rotor shaft. The magnetized male adaptor is terminally mounted to the rotor shaft, opposite of the magnetized female adaptor. The magnetized impeller assembly is slidably engaged within the annular housing so that the magnetized impeller assembly can be magnetically engaged with the magnetized female adaptor and the magnetized male adaptor through the rotation of the rotor shaft. The fluid turbine system is in fluid communication with the annular housing, wherein the circulation of fluid flow generates electricity within the fluid turbine system.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.78-0.91 inch (19.7-23.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.49-0.62 inch (12.5-15.6 mm). The airfoil element includes at least two of a first mode with a frequency of 3533±15% Hz, a second mode with a frequency of 8291±15% Hz, a third mode with a frequency of 17362±15% Hz and a fourth mode with a frequency of 23365±15% Hz.

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: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.55-0.65 inch (14.0-16.5 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 0.76-0.86 inch (19.3-21.8 mm). The airfoil element includes at least two of a first mode with a frequency of 3335±10% Hz, a second mode with a frequency of 5715±10% Hz and a third mode with a frequency of 41797±10% Hz.

Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

Abstract: A tuned mass damper for damping an oscillating movement of a structure along a first direction is provided. The tuned mass damper comprises a mass arranged to perform a reciprocating movement along the first direction in response to the oscillating movement of the structure, wherein the mass comprises a braking mechanism configured to at least partially brake the movement of the mass along the first direction when the mass exceeds a predefined speed.