Abstract: A computer-based method of designing a guide vane formation is provided. The vane formation is for use in a gas turbine engine which has a cascade of circumferentially arranged identical guide vane formations. The vane formation has radially inner and radially outer chordal seals. The method allows the elimination of “saw-tooth” leakage gaps between inner chordal seals of neighboring vane formations and between outer chordal seals of neighboring vane formations even when the inner and outer chordal seals are axially offset from each other.

Abstract: An example airfoil includes an airfoil body with a leading edge and a trailing edge joined by a pressure side and a suction side to provide an external airfoil surface extending in a radial direction from at least one platform. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location, and the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of up to +0.050 inches (+1.27 mm).

Abstract: Methods and systems are provided for an adjustable diffuser of a turbocharger compressor. In one example, a compressor includes a diffuser formed in a compressor housing downstream of an impeller of the compressor, the diffuser including guide blades mounted on a rotatable annular support of the diffuser. Further, an engine controller may adjust rotation of the annular support based on one or more engine operating conditions.

Abstract: An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract: A power turbine unit includes a turbine housing, an exhaust duct, a turbine wheel with blades positioned in the exhaust duct, a shaft rigidly connected to the turbine wheel and rotatably supported in the housing, and an oil sealing system. The oil sealing system includes a sealing arrangement positioned in the vicinity of the turbine wheel for preventing oil from escaping from the turbine housing along the shaft to the exhaust duct. The oil sealing system further includes a buffer gas duct that is arranged to supply exhaust gas from the exhaust duct to the sealing arrangement for pressurizing the sealing arrangement.

Abstract: A turbocharger has an annular bypass valve disposed in an annular portion of a bypass passage of the turbine housing. The turbine housing defines an exhaust gas chamber having separate half-annular first and second scrolls, and a portion of the bypass passage is sector-divided by a pair of dividing walls that create two 180-degree bypass sectors respectively connected to the first and second scrolls. Each dividing wall has a through-hole. The valve rotor defines a pair of valve members that close the through-holes when the bypass valve is fully closed. When the valve rotor begins to rotate toward an open position, first the valve members open the through-holes to connect the two bypass sectors, and then the bypass flow passages begin to open.

Abstract: A gas turbine engine component includes an airfoil and a platform. The airfoil has a pressure side and an opposite suction side. The platform is connected to the airfoil and has a first curved edge adjacent the suction side and a second curved edge spaced from the pressure side such that more than half of the platform is located to the pressure side. The platform located to the pressure side has a non-axisymmetrical surface contouring.

Abstract: The present invention relates to a subassembly for a gas turbine, in particular a gas turbine aircraft engine, having a turbine casing (11); a midframe (14), which is adjacent downstream to the turbine casing and has a number of support ribs (15) spaced apart in the peripheral direction. The turbine casing and the midframe define a flow duct (33) for a working gas exiting a combustion chamber of the gas turbine, and a cavity, in particular a cooling air duct (19), with an opening on the flow duct side is formed between the turbine casing and the midframe. An edge contour (40) of the opening on the turbine casing side varies along the periphery radially and/or axially.

Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: Block components having a conductive property are mounted on lands for connection to a harness so as to increase the height of the lands on a circuit board which is to be connected to windings.

Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: An axial compressor includes a plurality of stator vanes attached to an inner surface of a casing defining an annular flow path and a plurality of rotor blades attached to a rotating rotor defining the annular flow path. A flow path is defined between a pressure surface of a stator vane and a suction surface of a stator vane, the vanes being circumferentially adjacent to each other, or between a pressure surface of a rotor blade and a suction surface of a rotor blade, the blades being circumferentially adjacent to each other. The flow path is formed so that a throat portion at which a flow path width is minimized is provided on the upstream side of 50% of an axial chord length.

Abstract: A cross flow fan includes a support plate and an impeller with a plurality of blades disposed on the support plate at predetermined intervals. On each blade, a radius of a pressure surface arc is greater than a radius of a suction surface arc, a radius of an inner peripheral side arc is greater than a radius of an outer peripheral side arc, and a region of maximum thickness is located 40% to 60% from the inner peripheral side arc in the lengthwise direction. The blades are disposed such that the inner peripheral side arcs are positioned on an inner peripheral side of the support plate and the outer peripheral side arcs are positioned on an outer peripheral side of the support plate. A flow path width between the plurality of blades gradually decreases from the inner peripheral side toward the outer peripheral side of the support plate.

Abstract: The invention relates to an axial flow turbine and method of operating thereof. The turbine comprises a last stage of rotating blades located towards a downstream end of the turbine having a distal region at an end of the airfoil of the blades. A monitoring control system has at least one sensor in the distal region of at least one last stage blade for measuring at least one physical property of the airfoil and a control element that is capable of influencing at least one physical property of the distal region. The control system further includes a controller that adjusts the control element based on at least measured physical property so by controlling the at least one physical property.

Abstract: A blower assembly includes a housing having a blower wheel disposed therein and a pre-swirler disposed in a fluid inlet of the housing. The pre-swirler includes an array of spaced apart vanes extending radially outwardly from a central hub. The vanes extend from the hub to an outer ring that is attached to the housing of the blower assembly. The vanes are configured to cooperate with the blower wheel to minimize a noise, a vibration, and a harshness (NVH) of the blower assembly, while maximizing an efficiency thereof.

Abstract: A blade for a runner of a Francis turbine having a throat diameter (Dth), the blade including: a maximum thickness of no less than 0.03 Dth and a leading edge having a maximum lean angle of no less than 45 degrees, wherein the lean angle is defined by a vertical line and the leading edge.

Abstract: A steam turbine 10 according to an embodiment includes: rotor blade cascades each made up at a turbine rotor 22; an inner casing 21 where the turbine rotor 22 is provided to penetrate; an outer casing 20 surrounding the inner casing 21; stationary blade cascades each made up at an inner side of the inner casing 21; and an annular diffuser 60 provided at a downstream side of a final turbine stage, formed by a steam guide 40 and a bearing cone 50, and discharging steam toward outside in a radial direction. An enlarged inclination angle ?1 of an inner surface 70 of a diaphragm outer ring 26a at the final turbine stage relative to a turbine rotor axial direction is an enlarged inclination angle ?2 of an inner surface 80 at an inlet of the steam guide 40 relative to the turbine rotor axial direction or more.

Abstract: A turbine assembly for a turbocharger can include a C-shaped seal that includes an inner diameter, an outer diameter, an axis aligned parallel to a rotational axis of a turbine wheel, a lower lip that contacts a lower axial face of an outer surface of a shroud component along an annular portion of the shroud component, an upper lip that contacts a lower axial face of an inner surface of a turbine housing, and a wall portion that extends between the lower lip and the upper lip. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: A stator for use with a torque converter includes an inner annular shell, outer annular core, a plurality of stator blades and pressure-side fluid directing projections. The plurality stator blades are disposed around the inner shell in a spaced apart configuration and radially extend to the outer core. Each stator blade includes an inlet-side edge, an opposed outlet-side edge and opposed pressure-side and suction-side surfaces extending between the inlet-side and outlet-side edges. The pressure-side fluid directing projections outwardly project from the pressure-side surface in spaced relation to each other and each extend between the inlet-side and outlet-side edges. The fluid directing projections are configured to aid in redirecting torque converter fluid returning from a turbine and reducing fluid separation as the fluid interacts with the stator blades and associated fluid directing projections thereby increasing efficiency and performance of the torque converter.

Abstract: A multi-stage axial compressor incorporating a counter-rotational movement is provided with a series of rotors mounted along and driven by a driveshaft, and a geared counter-rotating outer casing. A planetary gear system is assembled along a static casing, which can be assembled as a forward or aft casing for the compressor. The bearings of the planetary gear system typically will be aligned concentrically with a center rotor drum assembly mounted along the single driveshaft. The counter-rotating drum assembly will be assembled over the rotor drum assembly and will be engaged by the forward and aft casings so as to provide for counter-rotation of selected ones of the rotors driven by the driveshaft of the compressor.

Abstract: An impeller for increasing the pressure of a fluid circulating in an annular fluid path, the impeller comprising: a plurality of centrifugal compressor vanes circumferentially interspaced around the axis of the annular fluid path, the plurality of compressor vanes extending from an axially-oriented inlet to a radially-oriented outlet, and each having an inner edge and a free edge, the free edge of the plurality of compressor vanes coinciding with an outer limit of the annular fluid path, and a hub having a solid-of-revolution shape centered around an axis, the hub having an outer hub surface forming an inner limit to the annular fluid path and to which the inner edge of the plurality of centrifugal vanes is secured, the outer hub surface having a portion which leans forward, forming an axial recess therein.

Abstract: A blade cascade for a continuous-flow machine having a non-axisymmetrical side wall contour, whereby the side wall contour has at least one pressure-side elevation and one suction-side depression, whose highest section and lowest section are located over an area 30% to 60% of an extension of the blades in the axial direction, and the axial positions of the outermost sections differ from each other at the maximum by 10% in the axial direction.

Abstract: A power turbine includes a first stage blade having an airfoil with a cold un-coated nominal profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Abstract: A vacuum pump has a rotor mounted on a rotor shaft and provided with pump active components cooperating with opposite stationary pump active components, fastening element for securing the rotor on the rotor shaft, and a safety element provided in addition to the fastening element for preventing rotation of the rotor and the rotor shaft relative to each other.

Abstract: A blade cascade for a continuous-flow machine having a non-axisymmetrical side wall contour, whereby the side wall contour has at least one suction-side depression that, in the circumferential direction, is at a distance from a suction-side wall, and having a section located upstream from the leading edges and a section located downstream from the leading edges, it has a pressure-side elevation that makes a transition to a pressure-side wall and that is located in a front blade area, and it has a pressure-side depression that is located upstream from the pressure-side elevation, and also discloses a continuous-flow machine having such a blade cascade.

Abstract: A method for repairing a turbine nozzle having at least one vane disposed between an inner and an outer band. Embodiments of the method can comprise separating the inner band from the outer band and securing a replacement part to the inner band. In one embodiment, the methods accommodate replacement parts that include vanes with a base feature that comprises a non-airfoil shape and that integrates cooling features useful for operation of the turbine nozzle.

Abstract: A structural layer (30) may be bi-cast onto ligaments (62) extending from a porous cooling construction (20). The material of the structural layer may be optimized for high-temperature strength, while the material of the porous construction may be optimized for high thermal conductivity. A fugitive material (56) such as wax may be formed on the ligaments of the porous construction. A second fugitive material (58) such as ceramic may fill the remaining part of the porous construction. An investment casting shell (60) may be disposed around the porous construction and the fugitive materials. The first fugitive material may then be replaced with the material of the structural layer (30), and the second fugitive material may be removed to provide coolant paths (26). A second structural layer (52) may be bi-cast onto further ligaments (62) on a second side of the porous construction.

Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including a non-axisymmetric contour proximate a junction between the endwall and the leading edge of the airfoil.

Abstract: A turbine blade has a profile including a blade suction side line, a blade pressure side line, and a blade trailing edge formed by a curve connecting the rear ends of the blade suction side and pressure side lines to each other, wherein the curve forming the blade trailing edge of the profile is formed by connecting a pressure side curve portion which has an arc shape having a constant radius of curvature and extending from the rear end of the blade pressure side line toward the camber line of the profile, and a suction side curve portion which extends from the rear end of the blade suction side line toward the camber line while passing through a region closer to the camber line than a symmetric curve portion which is line-symmetric to the pressure side curve portion with respect to the camber line.

Abstract: A nozzle assembly is provided. The nozzle assembly includes at least one stationary nozzle. An outer ring having a predefined shape includes at least one groove defined therein and the groove is configured to receive at least a portion of the stationary nozzle therein. A coupling portion is formed integrally with the stationary nozzle or the outer ring such that the coupling portion extends outwardly therefrom. An attachment member is coupled to the coupling portion to facilitate substantially restricting movement of the stationary nozzle when the outer ring is substantially distorted.

Abstract: A vane assembly (21) for an axial flow turbine engine provides a plurality of nozzles (22) arranged symmetrically around a turbine axis formed by an inner hub (26), an outer casing (27) and vanes (23) intermediate pairs of adjacent nozzles. The nozzles have a cross-section normal to the turbine axis that changes smoothly with the position of the cross-section along the turbine axis from a first shape having a minimum radius of curvature of a first value that is no less than a limit L, providing the cross-section with no highly curved corners, to a second shape having a minimum radius of curvature of a second value less than the first value, providing corners. This allows the secondary flow structure to be designed to improve aerodynamic loss and cooling performance.

Abstract: A gas turbine stator vane is effective for suppressing a secondary flow in a region sandwiched between a suction surface side and a pressure surface side, as well as for suppressing augmentation of a horseshoe-shaped vortex occurring near a leading edge of the vane. The stator vane includes a vane profile portion having a pressure surface concaved to a chord line of the vane, and a suction surface convexed to the chord line; an outer-circumferential end wall positioned at an outer circumferential side of the vane profile portion; and an inner-circumferential end wall positioned at an inner circumferential side of the vane profile portion. An outer-circumferential end wall inner surface that is an inner-circumferential surface of the outer-circumferential end wall has an inward convexed shape and an outward convexed shape, at the suction surface side of the vane profile portion.

Abstract: A compressor component having an improved airfoil profile so as to eliminate previously known vibratory issues in the blade tip is disclosed. By altering the airfoil profile throughout its span, the natural frequency of the airfoil is altered so as to not coincide with a critical engine order of the compressor. Further, the present invention provides a novel airfoil profile in accordance with the coordinates of Table 1.

Abstract: A turbine of a turbomachine is provided and includes opposing endwalls defining a pathway for a fluid flow and a plurality of interleaved blade stages and nozzle stages arranged axially along the pathway. The plurality of the blade stages includes a last blade stage at a downstream end of the pathway and a next-to-last blade stage upstream from the last blade stage. The plurality of the nozzle stages includes a last nozzle stage between the last blade stage and the next-to-last blade stage and a next-to-last nozzle stage upstream from the next-to-last blade stage. At least one of the next-to-last blade stage and the next-to-last nozzle stage includes aerodynamic elements configured to interact with the fluid flow and to define a throat distribution producing a tip strong pressure profile in the fluid flow.

Abstract: A fan blade system with multiple spaced layers of blades and a centrifugal fan using same are disclosed. The centrifugal fan includes a housing, in which the fan blade system is mounted. The fan blade system includes a hub, and a first and a second blade group outward extended from a circumferential wall of the hub to axially space from each other. The housing includes a main housing portion and a secondary housing portion integrally formed on one side of the main housing portion. When the fan blade system is mounted in the housing, the two blade groups are separately located in the main housing portion and the secondary housing portion to produce higher airflow pressure and more air volume. With these arrangements, the centrifugal fan can have upgraded performance and be manufactured with reduced labor, time and material costs.

Abstract: A vibration damper between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel, the damper including a peg having a substantially spherical portion at each of its two ends, and two hollow inserts for being received in tangential cavities that are provided facing each other in outer platforms of two adjacent composite-material blades of a turbine engine rotor wheel, each spherical portion of the peg coming to bear with point contact against the inside of one of the inserts.

Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: A vane assembly for use in a gas flow duct. The vane assembly includes multiple vanes arranged circumferentially about the duct. A throat angle of each of the vanes at mid-span is greater than the throat angle at the tips of the vane.

Abstract: An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall near the leading edge of at least one of said plurality of airfoils, and a concave profiled region in the endwall near a middle of at least one of said plurality of flow passages.

Abstract: A turbine engine component includes a platform and one or more microcircuit cooling passages embedded within one or more walls of an airfoil portion of the component. Each microcircuit cooling passage terminates within the thickness of the platform so as to provide cooling to the initial 10% span of the airfoil portion. Each microcircuit cooling passage has an inlet for receiving cooling fluid, which inlet is also embedded within the platform.

Abstract: A seal for sealing a rotor of a rotary machine to a stator thereof which circumscribes the rotor and is separated therefrom by a gap comprises a nonrotational sealing element received within an annular slot in the stator and radially translatable with respect thereto, and extending into the gap for sealing to rotational sealing element carried by the rotor. A resilient biasing element received between the nonrotational sealing element and a floor of the slot biases the nonrotational sealing element radially inwardly toward the rotational sealing element and limits radially outward movement of the nonrotational sealing element. A guide extending into said gap from the slot engages the nonrotational sealing element to prevent axial misalignment thereof with the machine's rotor.

Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a purge trough commencing tangentially in a blend area of the platform. The purge trough extending axially toward the suction side of the airfoil, aft of the leading edge, to channel a purge flow.

Abstract: A damper actuator assembly comprises a gear train including a follower gear. The follower gear is arranged such that the position of the follower gear indicates the position of at least one blocking member of a damper that the actuator is connected to. A sensor is positioned within the damper actuator and is configured to monitor the position of the follower gear. Accordingly, the sensor is configured to provide an electrical signal indicative of the position of the follower gear to a processor. A driving member is connected to the gear train and is configured to drive the gear train at two or more variable speeds depending on the electrical signal provided to the processor from the sensor.

Abstract: A turbomachine blade made of composite material including a fiber reinforcement obtained by three-dimensional weaving of yarns and densified by a matrix, includes a first portion constituting an airfoil and a blade root. The first portion constitutes a single part with at least one second portion constituting a blade inner platform, the blade then lacking a blade anti-tilting wall, or a blade anti-tilting wall, the blade then lacking a blade inner platform. The first portion also constitutes a single part with at least one third portion constituting a blade outer platform spoiler plate, the blade then lacking a blade outer platform wiper plate, or a blade outer platform wiper plate, the blade then lacking a blade outer platform spoiler plate.

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 heat dissipating module includes a housing, a first fan and a second fan. The housing has a partition. The first fan is disposed at a side of the partition, and the second fan is disposed at the other side of the partition. The second fan has a plurality of wind deflectors, which are disposed higher than the partition.

Abstract: A vane profile section for an air turbine starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge, the airfoil profile section defined by a set of X-coordinates and Z-coordinates.

Abstract: A turbine stage for a turbine engine, the stage including a nozzle and a wheel mounted inside a sectorized ring carried by a casing. The nozzle is attached to the casing and is retained axially downstream by bearing against an annular split ring. Each ring sector includes at its upstream end a member of C-shaped section that is engaged on the casing rail and that holds the split ring radially. A radially inner wall of the C-shaped member of each ring sector extends inside the split ring over an entire axial dimension thereof and its upstream end portion is engaged in at least one recess of the nozzle.

Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: A turbine-pump system adapted for use with well liquid that is displaceable within a well conduit. The turbine-pump system may include a bowl assembly; and a bowl support device fixedly attachable to the bowl assembly and selectively engageable with the well conduit for holding a portion of the bowl assembly in substantially axially, radially and rotationally fixed relationship with the well conduit.