Abstract: A fan case assembly adapted for use with a gas turbine engine includes a fan track liner and an annular case. The fan track liner extends circumferentially at least partway about a central axis of the gas turbine engine. The annular case is configured to support the fan track liner at a radial position relative to the central axis. The fan case assembly further includes an air recirculation duct configured to redirect air around the fan track liner.

Abstract: A diffuser includes a lower element and an upper element. The upper element is fixed on the lower element, and the upper element and the lower element are formed separately. The lower element includes a lower inner wall and a lower outer wall, and the upper element includes an upper inner wall and an upper outer wall. The upper inner wall is connected to the lower inner wall to form an internal air-guiding surface, the upper outer wall is connected to the lower outer wall to form an external air-guiding surface, and the internal air-guiding surface is disposed opposite to the external air-guiding surface to define an air-guiding channel for air flow diffusion. The upper element further includes an upper air-guiding wing for connecting the upper inner wall and the upper outer wall, and the lower element further includes a lower air-guiding wing for connecting the lower inner wall and the lower outer wall.

Abstract: A gas turbine engine includes a first spool, a second spool, a third spool, and a epicyclic differential. The epicyclic differential includes a sun gear, planet gears supported from a planet carrier, a ring gear, and a locking member, each housed within an accessory gearbox. The planet carrier couples to the second spool. The sun gear couples to the third spool, and the ring gear couples to engine accessories. A method of operating the gas turbine engine includes supplying a first fuel flow rate to a primary combustor associated with the first and third spools and supplying a second fuel flow rate to a secondary combustor associated with the second spool based on a power lever angle within an intermediate power level range.

Abstract: A control valve composed of sectors of stationary blades, which are externally connected to a stator, includes an inner platform divided into an outer portion formed of sectors and associated, by radial slide connections, with an inner portion in the form of a ring which is continuous over a circumference, which carries an abradable seal. Springs ensure the radial position of the crown, and the concentricity thereof to the rest of the machine. The diameter of the crown is essentially determined by the temperature of the gases which pass in front of it. The independence of the radial thermal deformations is ensured by slides composed of sliding sleeves.

Abstract: A compressor section for a gas turbine engine includes a blade including a platform, a tip and an airfoil extending between the platform and tip. The airfoil includes a root portion adjacent to the platform, a midspan portion and a tip portion. Each of the root portion, midspan portion and tip portion define a meridional velocity at stage exit with the tip portion including a first meridional velocity greater than a second meridional velocity of the midspan portion. A blade for an axial compressor of a gas turbine engine and a method of operating a compressor section of a gas turbine engine are also disclosed.

Abstract: A multi-propeller assembly for a drone, the multi-propeller includes a housing, a motor coupled having a circular cavity surrounded by a plurality of magnets disposed at the opposing second side of the housing, a first, second, and third three-bladed propeller having drive members rotatably coupled within the circular cavity of the motor and nested within each other, wherein the motor is configured to simultaneously rotate the first and third three-bladed propeller in a first direction and the second three-bladed propeller in an opposite second direction using the plurality of magnets.

Abstract: Disclosed are a compressor, which is a cantilever type that is easy to manufacture and assemble, and is capable of minimizing the vane tip clearance as the elastic member absorbs the impact and is compressed when the vane collides with the shroud segment due to expansion of the vane, and a gas turbine including the same.

Abstract: A fan shroud for a heating, ventilation, and/or air conditioning (HVAC) unit may include an outer wall to couple to a housing of the HVAC unit and an inner wall disposed within the outer wall. Additionally, the inner wall may be air permeable. The fan shroud may also include an acoustic damping material disposed between the outer wall and the inner wall. The fan shroud may encircle a fan of the HVAC unit to reduce noise.

Abstract: A turbine engine including a fan, a nacelle circumscribing at least the fan, a compressor section downstream of the fan, and a conduit defined, at least in part, by the nacelle. The conduit includes a first opening at the compressor section, a second opening downstream of the fan and upstream of the compressor section, and a third opening upstream of the fan. Pressure sensors coupled to the nacelle are communicatively coupled to at least one actuator. The at least one actuator can adjust airflow between the first opening and the second opening, or between the first opening and the third opening. The pressure sensors can provide outputs for generating commands that control the at least one actuator.

Abstract: A turbomachine defines an axial direction, a radial direction perpendicular to the axial direction, and a circumferential direction extending concentrically around the axial direction. The turbomachine includes a nozzle having an inner platform, an outer platform, and an airfoil. The airfoil includes a leading edge, a trailing edge downstream of the leading edge, a pressure side surface, and a suction side surface opposite the pressure side surface. The trailing edge defines a circular arc between the inner platform and the outer platform.

Abstract: The present invention provides a vertical, axial flow oil pump (10). The oil pump includes: a casing (11), the casing having a cylindrical shape as a whole and being able to rotate around its own central axis (O); a suction port (12), located at a lower end of the casing in an axial direction, and configured to suck oil into the oil pump; a discharge port (13), located at an upper end of the casing in the axial direction, and configured to discharge the oil from the oil pump to outside; and an impeller (14), provided in and formed integrally with the casing. The impeller rotates together with the casing when the casing rotates, so that the oil is flowed from the suction port to the discharge port. The present invention also provides a scroll compressor having the oil pump.

Abstract: A compressor has a rotor assembly having an impeller for generating an airflow through the compressor, a stator core assembly for causing rotation of the impeller, and a diffuser assembly for acting on the airflow generated by the impeller. The diffuser assembly has a first diffuser stage and a second diffuser stage. The first and second diffuser stages are separate components connected to one another by a fastener.

Abstract: The invention relates to an assembly for a turbomachine extending along an axis (X) and comprising: —a ferrule (32) designed to define a fan duct (5) of a gas stream of the turbomachine, —a fan casing (2) radially surrounding the ferrule (32) and defining with the ferrule (32) the fan duct (5), —a rectifier (6) comprising a plurality of vanes (7) comprising a first vane (7a) and a second vane (7b) adjacent to the first vane (7a), the vanes defining between them a converging flow channel (13) designed to direct and accelerate the stream by means of an inlet section (14a) included in a plane non-perpendicular to the axis of the turbomachine and an outlet section included in a plane (14b) perpendicular to the axis (X) of the turbomachine, the first vane (7a) and the second vane (7b) each having an unducted downstream portion which forms a trailing edge.

Abstract: A temperature destratification assembly can include an outer housing. An impeller can be positioned within the outer housing between the inlet and outlet of the outer housing. The impeller can have an impeller hub and a plurality of impeller blades extending radially outward from the impeller hub. The assembly can include an impeller motor configured to rotate the impeller blades about an axis of rotation. A stator can be positioned within the outer housing between the impeller and the outlet of the outer housing. The stator can include a plurality of vanes. The stator vanes can include an upstream edge at the upstream end of the stator, a first surface extending from the upstream edge to the downstream edge of the vane, and a second surface opposite the first surface and extending from the upstream edge to the downstream edge of vane. A plurality of the vanes can have a downstream edge at the outlet of the outer housing.

Abstract: This invention discloses an improved wind turbine suitable for mounting without a wind turbine tower. The wind turbine is based on a rotor with appropriately selected blades. A nozzle and diffuser in the wind flow increase the amount of wind energy available to the rotor. The rotor is interruptibly connected with one or more of a plurality of generators which allows generation at a wide range of wind speeds. The rotor is also interruptibly connected with a co-axial flywheel which allows for storage or use of rotational energy as needed by the availability of wind energy. One or more wind turbines can be grouped together in a common housing. Electricity can also be generated by means of stored energy. The lack of a wind turbine tower and the general compact design allows the wind turbine to be used in close proximity to or on buildings.

Abstract: This invention discloses an improved wind turbine suitable for mounting without a wind turbine tower. The wind turbine is based on a rotor with appropriately selected blades. A nozzle and diffuser in the wind flow increase the amount of wind energy available to the rotor. One or more wind turbines can be grouped together in a common housing. The lack of a wind turbine tower and the general compact design allows the wind turbine to be used in close proximity to or on buildings.

Abstract: Various embodiments provide a rotor disk assembly capable of preventing a slip between rotor disks when rotating, and capable of performing a balancing operation such that the center of gravity thereof is the same as that of a rotating shaft, and a gas turbine including the rotor disk assembly. The rotor disk assembly may include: a plurality of rotor disks disposed parallel to each other; a tie rod passing through the plurality of rotor disks and coupling the plurality of rotor disks to each other; a plurality of coupling depressions formed in each of facing surfaces of the plurality of rotor disks; and a plurality of coupling pins each having opposite ends inserted into the corresponding respective coupling depressions of the facing surfaces.

Abstract: A compressor rotor assembly including a plurality of rotor disks axially spaced from each other, each rotor disk extending radially from an inner end to an outer end. Also included is a spacer extending axially from each rotor disk to engage an adjacent spacer extending from an adjacent rotor disk, the spacer and adjacent spacer disposed proximate the outer end of the respective rotor disks, the spacers forming an outer backbone of the compressor rotor assembly. Further included is an inner backbone of the compressor rotor assembly, the inner backbone comprising a plurality of backbone segments, each of the backbone segments extending axially from each rotor disk to engage an adjacent backbone segment extending from an adjacent rotor disk, the backbone segment and the adjacent backbone segment disposed proximate the inner end of the respective rotor disks.

Abstract: An axial flow compressor comprises a tubular casing which encases a rotatable shaft, a pair of rotor segments coupled to the rotatable shaft and each comprising a bladed disc, and a banded stator segment disposed between the pair of rotor segments and comprising a plurality of stator vanes extending between an outer flowpath ring and an inner flowpath ring. A method of assembling an axial flow compressor comprises installing a rotor segment inside a tubular compressor casing, installing a vane segment adjacent the installed rotor segment, and repeating the steps of installing a rotor segment and vane segment until a desired number of rotor segment and vane segment pairs are installed.

Abstract: The present invention relates to a propulsion unit nozzle for being arranged around a propeller in a propulsion unit, comprising: a load bearing core structure extending in a circumference of the propulsion unit nozzle; and a plurality of hydrodynamic elements mounted on and enclosing the core structure thereby defining the outer and the inner surfaces of the propulsion unit nozzle. The invention further relates to a propulsion unit for a vessel comprising a propulsion unit nozzle and to a method for the manufacture of a propulsion unit nozzle.

Abstract: A wind power system, having at least one rotor, which controls a respective driven utility apparatus, and at least one stator. The rotor includes vanes arranged radially, which have a substantially flat profile. The vanes are inclined with respect to the rotation axis of the rotor through an angle between 25° -90°. The system further includes at least one stator arranged upstream of the rotor and is provided with a tubular body coaxial to both the shaft of the rotor and a substantially cylindrical outer enclosure. The tubular body includes a tapered end and curved blades profiled to direct the air entering the system toward the outerportion of the rotor onto the vanes. Between the inner walls of the enclosure, two adjacent blades, and tubular body, there is a forced path for the air entering the system.

Abstract: A centrifugal blower assembly includes a housing and a blower wheel coupled to the housing. The blower wheel includes a plurality of blades circumferentially-spaced about an axis of rotation. Each blade includes a length and is oriented at a first angle along the length with respect to the rotational axis. The centrifugal blower assembly also includes a plurality of circumferentially-spaced fins coupled in flow communication with said blower wheel, said plurality of fins configured to direct an inlet airflow into the blower wheel such that a relative velocity direction of the inlet airflow is oriented at the first angle with respect to the rotational axis.

Abstract: An exhaust nozzle for a turbine engine includes multiple daisy style corrugations arranged circumferentially about the exhaust nozzle. Each of the daisy style corrugations has a radially inner base portion and multiple lobes protruding radially outward from the base portion.

Abstract: An asymmetric vane assembly includes a high count vane section including a first plurality of vanes oriented in a first position. The asymmetric vane assembly also includes a low count vane section including a second plurality of vanes oriented in a second position, a total number of vanes in the first plurality of vanes being greater than a total number of vanes in the second plurality of vanes, and each vane of the high count vane section and each vane of the low count vane section having substantially similar internal core geometry.

Abstract: An apparatus and method are disclosed for a gas turbine engine including an offtake located within the air flow of the engine. The offtake has an inlet and a louver covering the inlet. The louver has multiple airfoils arranged to direct the air flow into the inlet of the offtake.

Abstract: A system includes a turbomachine with a plurality of blades, a casing disposed about the rotor and the plurality of blades, an access opening disposed in the casing, and an access panel selectively coupled to the access opening, such that the access opening is sized to enable repair or replacement of at least one blade of the plurality of blades.

Abstract: A gas turbine engine comprising in flow series: a fan; a series of outlet guide vanes; and a bifurcation. The outlet guide vanes are more densely distributed in a region circumferentially aligned with the bifurcation than in a region circumferentially offset from the bifurcation.

Abstract: An exhaust gas diffuser (38) including: a radially-outer peripheral casing (46); a hub (42) located within said radially-outer peripheral casing and coaxial with a center axis (40) of the casing; main struts (44) located at circumferentially-spaced locations about the hub and extending radially-outwardly to the radially outer peripheral casing; and small struts (52) located at circumferentially-spaced locations between the main struts; wherein the main struts and small struts have substantially parallel longitudinal chord lines and each of the small struts have a cross-sectional area smaller than a cross-sectional area of the main struts.

Abstract: A sector for a turbine stator includes vanes made of composite material, each including an airfoil extending between first and second ends. The sector has first and second platforms made of composite material, the first platform having openings in which the first ends of the vanes are engaged, and the second platform having openings in which the second ends of the vanes are engaged. The openings in the first platform present dimensions greater than the dimensions of the first ends of the vanes engaged in the openings so as to leave clearance between the first end of each vane and the opening. Each vane first end engaged in an opening presents dimensions that are less than the dimensions of the airfoil so as to define a shoulder extending around the first end. The shoulder presents dimensions that are greater than the dimensions of the openings in the first platform.

Abstract: A gas turbine engine composite vane assembly and method for making same are disclosed. The method includes providing at least two gas turbine engine airfoil composite preform components. The airfoil composite preform components are interlocked with a first locking component so that mating faces of the airfoil composite preform components face each other. A filler material is inserted between the mating surfaces of the airfoil composite preform components.

Abstract: Compliant coupling systems and methods are provided for coupling a shroud to an engine casing. The complaint coupling system includes a retaining ring adapted to be positioned adjacent to the shroud and adapted to be coupled to the engine casing. The retaining ring defines a coupling channel about a circumference of the retaining ring and at least one notch that interrupts the coupling channel. The complaint coupling system also includes a first clip received within the coupling channel. The first clip has a biasing portion that extends into a space defined by the at least one notch, and the biasing portion is adapted to contact the shroud. The complaint coupling system includes a second clip received within the coupling channel. The second clip has a bumper portion that extends into the spaced defined by the at least one notch, and the bumper portion is adapted to contact the shroud.

Abstract: An aircraft gas turbine has a core engine and a bypass duct surrounding the latter, where the core engine includes in its inflow zone a booster, in the area of which at least one booster bleed duct is provided for supplying an airflow from the booster into the bypass duct, and a stator vane row arranged in the bypass duct downstream of a fan. A vane root of the stator vane is designed as a structural element mounting the core engine, and the booster bleed duct is provided inside the vane root and issues downstream of the stator vane into the bypass duct.

Abstract: A centrifugal fan for a refrigerator can include a plurality of vanes arranged radially about a central a shaft; a ring-shaped shroud coupled to the vanes and having a curved portion with a predetermined radius or curvature and also having an angled portion with a predetermined gradient or angle relative to the curved portion; and a bottom surface coupled to the vanes on the side opposite the shroud; where a ratio (r/R) of an inner diameter r, which is the shortest distance between the vane and the shaft, and an outer diameter R, which is the longest distance between the vane and the shaft, is approximately 0.69±0.01.

Abstract: The invention relates to an axial turbomachine stator (2) comprising an inner shell (28) with an annular row of openings; an annular row of blades (26); the said blades extending substantially radially through the said openings, respectively, and each comprising a cut-out (34) on the inside of the shell; at least one blade-retaining plate (36) inserted in at least one cut-out (34), with means of immobilization of the said plate in the cut-out(s). The means of immobilization comprise at least one tongue (38) with an end forming a support surface (40) in contact with a part of the blade (26) or of one of the blades (26) located radially directly above the corresponding cut-out.

Abstract: A compressor casing, a compressor provided with the same, and a method of assembling the compressor are provided. The compressor casing includes a substantially tubular casing, a plurality of sealing surfaces provided on an inner circumferential surface of the compressor casing along an axial direction thereof, a sealing means provided for each of the plurality sealing surfaces, a substantially cylindrical bundle for accommodating a blade inside and for being assembled to the compressor casing so as to have contact with the plurality of sealing surfaces, and a roller provided on an outer circumferential surface of the substantially cylindrical bundle, for rolling on the inner circumferential surface of the compressor casing when the substantially cylindrical bundle is assembled to or removed from the compressor casing. The sealing surfaces are connected with one another with tapered surfaces.

Abstract: A turbine guide vane system, in particular for a gas turbine is provided. The turbine guide vane system includes a number of guide vane rows and a guide vane carrier, to enable particularly simple replacement of guide vanes, while maintaining a particularly high degree of efficiency, and thus designed for particularly short repair durations. For this purpose, the guide vane carrier has a number of segments, wherein a segment extends over the entire radial extension of the guide vane carrier and the connection of the remaining segments may be detached, and wherein the turbine guide vane carrier includes at least two sections along the axial extension thereof that are connected to one another and have a different number of segments.

Abstract: Embodiments of the present disclosure provide an apparatus comprising a power supply, a wireless controller coupled to the power supply, the wireless controller being configured to wirelessly receive a command from a wireless thermostat of a ventilation system, the ventilation system having a vent through which a fluid passes, and a flow controller to automatically control an amount of flow of the fluid through the vent of the ventilation system based at least in part on the command received wirelessly from the wireless thermostat. Other embodiments may be described and/or claimed.

Abstract: A gas turbine engine includes a compressor, a combustor section, and a turbine. The turbine includes an integrated case/stator segment that is comprised of a ceramic matrix composite material.

Abstract: A variable geometry turbocharger includes a vane pack having rotatable vanes constrained by a pair of vane rings connected by a plurality of spacer connectors. The spacer connectors can include a spacer body for maintaining a minimum spacing between the vane rings. The spacer connectors are configured for bayonet mounting to at least one of the vane rings. To that end, the spacer connectors can include shaft portions extending from opposing sides of the spacer body. A plurality of transverse protrusions can extend outwardly from each shaft portion. Each shaft portion can be received in a respective in a vane ring. The spacer connectors can be rotated such that the transverse protrusions are offset from aperture portions that allow passage of the transverse portions, thereby retaining the vane rings in place in spaced relation. Such a system avoids close tolerances, press fits, expensive bolted joints or weld processes.

Abstract: A stator blade diaphragm ring includes a plurality of stator blades each having a root and a radial pin receiver. The diaphragm ring further includes a first ring having a plurality of slots, wherein each slot is engaged by the root of one of the plurality of stator blades and a second ring having a plurality of radial through passageways, wherein each radial through passageway is aligned with the radial pin receiver of one of the plurality of stator blades. The diaphragm also includes a plurality of pins, wherein each pin extends from one of the radial through passageways into the radial pin receiver of one of the plurality of stator blades.

Abstract: A pump for a fluid which can be blood has a stator housing and a rotor hub with leading and trailing portions and an intermediate portion disposed therebetween. At least one impeller blade at the leading portion drives circumferential and axial components of a flow into a pump annulus or intermediate pathway portion. At least one stator blade extends radially inward from the stator housing within the intermediate pathway portion and is configured to reduce a circumferential component of the flow.

Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. 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. The X and Y values 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 may be joined smoothly with one another to form a complete airfoil shape.

Abstract: A turbomachine includes a plurality of rotating blades adjacent to a plurality of stationary vanes attached to a stationary casing. Stationary vanes are spaced apart circumferentially with equal spacing around an inner perimeter of the casing. Optionally, stationary vanes are offset radially and/or circumferentially. Stationary vanes may alternate with leading and/or trailing edges at different distances from the rotating blades. In one embodiment, stationary vanes have tapered leading and/or trailing edge angles to homogenize flow and reduce stator wake excitation, flow excitation, and acoustic excitation due to interaction with spinning modes of acoustic pressure pulsations at rotating blade passing frequency.

Abstract: A turbine section of a gas turbine engine is provided. The turbine section is annular about a longitudinal axis and includes first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine; and a first guide vane disposed within the inter-turbine duct.

Abstract: A ceiling fan system that includes a motor/blade assembly that may include a motor, a main rotor attached to the motor, and a plurality of blades attached to the main rotor. A plurality of hoods may partially enclose the motor/blade assembly. The plurality of hoods may include an intake nozzle hood acting as an air inlet and an outlet surface hood with an aerodynamic surface. The profile of the hoods is designed so that the resulting flow from the blades produces a flow pattern controlled by the aerodynamic shape of the hoods.

Abstract: A method and apparatus for reducing a selected tonal noise generated by a fan operating in a non-uniform flow by locating at least one obstruction in the non-uniform flow such that the at least one obstruction generates a noise that is out of phase with the selected tonal noise. The noise generated by the at least one obstruction interferes with the selected tonal noise, thus reducing the selected tonal noise. It is also contemplated to use additional obstructions to reduce other tonal noises generated by the fan.

Abstract: The invention relates to a cooling fan module for a motor vehicle, having a fan impeller which has a multiplicity of fan impeller blades which are connected to one another via a fan impeller outer ring, having a frame, on which the fan impeller is mounted, having an annular reverse flow guide device, which has an inner ring and an outer ring and which is designed to de-spin a reverse flow between the inner ring and the outer ring and to mix said reverse flow with the slot flow between inner ring and fan impeller outer ring.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of the profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: A gas turbine compression system (1) comprising a gas channel (5), a low pressure compressor section (8) and a high pressure compressor section (9) for compression of the gas in the channel and a compressor structure (14) arranged between the low pressure compressor section (8) and the high pressure compressor section (9). The compressor structure (14) is designed to conduct a gas flow in the gas channel and comprises a plurality of radial struts (15,16,21,24,25) for transmission of load, wherein at least one of the struts (15,16,21,24,25) is hollow for housing service components. The compressor structure (14) is arranged directly downstream of a last rotor (10) in the low pressure compressor section (8) and designed for substantially turning a swirling gas flow from the rotor (10) by a plurality of the struts (15,16,21,24,25) having a cambered shape.

Abstract: A gas turbine that can effectively cool an axial cavity between a stator blade and a rotor blade and a blade-end surface is provided. In a gas turbine in which a blade-count difference between stator-blade segments of a second-stage stator blade and a third-stage stator blade is set to zero, a relative position between the second-stage stator blade and the third-stage stator blade in the circumferential direction is set by clocking so that a wake flow produced by the stator-blade segments of the second-stage stator blade is guided to the leading edges of the stator-blade segments of the third-stage stator blade within a range of 0% to 15% of the length in a span direction from a hub side of the stator-blade segments of the third-stage stator blade.