Abstract: A device is for adjusting guide blades of a gas turbine. The guide blades are each connected to an adjusting ring via an adjusting lever, so as to be able to swivel, a first end of the, or each, adjusting lever engaging with the adjusting ring, and a second end of the, or each, adjusting lever, opposite to the first end, engaging with an end of a shaft or shank of the respective guide blade. The adjusting ring is assigned a rotor of a torque motor, a stator of the torque motor concentrically surrounding the rotor of the torque motor.

Abstract: An outer sidewall retention scheme for a singlet first stage nozzle of a gas turbine. The retention scheme includes a circumferential retaining ring with a main body and a pair of circumferential retaining lands projecting inward radially. A circumferential annular retaining groove is formed between the pair of circumferential retaining lands. A first lug and a second lug mounted on an outer face of the outer sidewall of each nozzle are adapted to fit within the circumferential annular retaining groove of the retaining ring and are supported radially and circumferentially by a first retaining pin and a second retaining pin, each pin passing though the circumferential retaining lands. Each nozzle further includes a chordal hinge rail and seal on the outer sidewall and a chordal hinge rail and seal on the inner sidewall providing axial support for the nozzle.

Abstract: A guide vane assembly for a turbomachine, comprising a guide vane and a liner: the guide vane comprising an aerofoil portion having a radially outer platform, wherein one of the outer platform and the liner has a hook element, the hook element comprising an opening and a circumferentially extending channel, and the other one of the outer platform and the liner comprises a retaining element having a head portion, wherein in an operational orientation the head portion located within the channel and is too wide to be withdrawn through the opening of the hook element.

Abstract: A turbine airfoil usable in a turbine engine and having at least one cooling system. At least a portion of the cooling system may be positioned in an endwall attached to the turbine airfoil. The endwall may include a submerged endwall cooling channel at the intersection between the generally elongated airfoil and the first endwall. The second endwall attached to the endwall on an end generally opposite to the first endwall may have a submerged endwall cooling channel as well. The submerged endwall cooling channels may include film cooling orifices to form vortices of cooling fluids to enhance cooling capacity of the cooling system of the turbine airfoil.

Abstract: Embodiments of the invention relate to a vane assembly formed by a forward airfoil segment and an aft airfoil segment. The aft segment is made of metal and can define the trailing edge of the vane assembly. The forward segment can be made of ceramic, CMC or metal. The forward and aft segments cannot be directly joined to each other because of differences in their rates of thermal expansion and contraction. The forward and aft segments can be positioned substantially proximate to each other so as to form a gap therebetween. In one embodiment, the gap can be substantially sealed by providing a coupling insert or leaf springs in the gap. A separate metal aft segment can take advantage of the beneficial thermal properties of the metal to improve cooling efficiency at the trailing edge without limiting the rest of the vane to being made out of metal.

Abstract: A method of repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes using an salvageable part, such as honeycomb backing strip remnant, from a nozzle segment that is unrepairable, and joining the honeycomb backing strip to a replacement casting. The replacement casting includes a tenon formed on the inner band that mates with a mortise formed on the back side of the honeycomb backing strip. A nozzle segment and nozzle segment casting used in connection with the method is also disclosed.

Abstract: The present invention provides an axial flow fan capable of increasing an air volume and a static pressure more than conventional axial flow fans, and also capable of reducing generation of noise. A guide wall portion 33 is provided to form a guide groove 31 between the guide wall portion 33 and one stationary blade 11. The one stationary blade 11 is disposed in the vicinity of a lead wire engaging portion 25 provided at a housing 3. The guide groove 31 receives a plurality of lead wires 10 and guides the lead wires 10 to the lead wire engaging portion 25. When the guide wall portion 33 is provided and the lead wires 10 are received in the guide groove 31, presence of the lead wires 10 may have less adverse effect on the air volume and the static pressure, and may generate less noise.

Abstract: A stator vane for a turbo molecular pump has stator vane halves each having inner and outer rim portions and radially arranged stator blades connected integrally between the inner and outer rim portions. The inner rim portion of each stator vane half has a pair of inner rim ends and the outer rim portion of each stator vane half has a pair of outer rim ends. The stator vane halves are disposed in abutment with one another along an abutment line to form an annular body with the inner rim ends of one of the stator vane halves being disposed in confronting relation with the respective inner rim ends of the other of the stator vane halves and with the outer rim ends of the one of the stator vane halves being disposed in confronting relation with the respective outer rim ends of the other of the stator vane halves.

Abstract: An air intake structure is located on an airflow guiding casing of a hand dryer communicating with gaps formed between motor blades in the airflow guiding casing. It includes a flow directing frame located on the airflow guiding casing, an axle located in the center of the flow directing frame and a plurality of flow directing blades located between the flow directing frame and the axle.

Abstract: An inlet duct, an induction system, and a system are disclosed for directing an inlet flow into an inlet compressor for use in an internal combustion engine. An example inlet duct may include one or more relief features disposed on an inner surface of the inlet duct. The one or more relief features may be made integral with the inlet duct. The one or more relief features may be disposed to protrude into the inlet flow to cause the inlet flow to swirl before reaching the inlet compressor.

Abstract: A guide vane for a gas turbine aircraft engine includes an aerodynamic shell for turning a flow of working fluid and an internal spar spaced from the aerodynamic shell by an air gap and reinforced by stiffeners.

Abstract: The invention relates to a fan housing for an air-flow heat exchanger having a fan blower comprising an axial-flow fan and a drive motor, the blower being connected to the fan housing by struts and the struts having a cross-sectional profile with a front edge and a rear edge. It is proposed that the struts, particularly their front and/or their rear edges, be arranged in a spherical or spheroidal surface enveloping them.

Abstract: A method for orienting cooling holes of a nozzle singlet for a turbine engine is provided. The method includes providing a nozzle singlet having an inner band, an outer band, and at least one airfoil extending therebetween. The method also includes orienting at least one first row of cooling holes an angle with respect to at least one second row of cooling holes. The orientation of the at least one first row and the at least one second row provides a cooling hole pattern that accommodates a change in the airfoil angle without reorienting the cooling hole pattern.

Abstract: A stator vane that may be used in engine assemblies. The stator vane includes an airfoil having a first sidewall and a second sidewall that is coupled to the first sidewall at a leading edge and at a trailing edge. The airfoil extends radially from a root portion to a tip portion. Each of the leading and trailing edges includes at least one lean directional change and a plurality of sweep directional changes that are defined between the root portion and the tip portion.

Abstract: A method of repairing a vane segment for a gas turbine engine includes removing an engine-run cooling baffle from the vane segment, forming a non-engine-run manufacturing detail that includes an inner platform, an outer platform, and an airfoil, attaching the engine-run cooling baffle to the non-engine-run manufacturing detail, and marking the non-engine-run manufacturing detail with a serial number associated with the vane segment from which the engine-run cooling baffle was removed.

Abstract: A turbine blade is provided, comprising a stator-side end located toward a stationary stator cylinder of the turbine, a rotor-side end located toward an axial rotor of the turbine, a leading edge located between the stator-side end and the rotor-side end, a trailing edge located between the stator-side end and the rotor-side end and located down-stream of the leading edge with respect to a fluid flow direction, wherein the rotor-side and stator-side ends have a negative sweep angle as measured between the instantaneous tangent of the blade surface and the fluid flow direction.

Abstract: A stator vane that may be used in an engine assembly is provided. The stator vane includes an airfoil that has a first sidewall and a second sidewall, which connects to the first sidewall at a leading edge and at a trailing edge. The airfoil also includes a root portion and a tip portion. The first and second sidewalls both extend from the root portion to the tip portion. The airfoil root portion is formed with a negative lean, and the airfoil tip portion is formed with a positive lean.

Abstract: A gas turbine engine airfoil including at least one outer tile coupled to a supporting member. The outer tile is coupled to the supporting member by a pin passing though the supporting member and the outer tile.

Abstract: A method of assembling a gas turbine engine is provided. The method includes coupling at least one turbine nozzle segment within the gas turbine engine. The at least one turbine nozzle segment includes at least one airfoil vane extending between an inner band and an outer band that includes an aft flange and a radial inner surface. The method also includes coupling at least one turbine shroud segment downstream from the at least one turbine nozzle segment, wherein the at least one turbine shroud segment includes a leading edge and a radial inner surface, and coupling a cooling fluid source in flow communication with the at least one turbine nozzle segment such that cooling fluid channeled to each turbine nozzle outer band aft flange is directed at an oblique discharge angle towards the leading edge of the at least one turbine shroud segment.

Abstract: A fan housing with a noise-reducing structure includes a housing having a side wall. An air inlet is defined in the housing and an air outlet defined in the side wall of the housing. A plurality of supporting ribs are disposed in the air inlet and connected between inner and outer peripheries of the air inlet for supporting a motor base. At least one of the supporting ribs is adjacent to the air outlet and extends in a direction coincident to or intersects with a longitudinal line of the air outlet extending through a rotational axis of the motor base.

Abstract: A wind turbine having rotor assembly with a plurality of stacked disks (1) for rotation about an axis. At least one set of the stacked disks has disks being closely spaced from each other for creating a boundary layer effect on surfaces of the disks that contributes in rotating the disks. Each disk has a plurality of rotor blades (2) disposed on an outer circumference thereof. Each rotor blade (2) has at least one surface extending tangentially from the outer circumference of each disk (1) for redirecting the airflow tangentially to a peripheral surface of each disk (1). Each disk (1) defines at least one opening (4) thereon for redirecting the wind axially through each of the disks (1).

Abstract: A pump includes a pump unit, a pump case, a motor unit, a plurality of guide blades forming plural guide paths in tangent directions of the impellers; and a multiplicity of return blades to form paths for collecting the liquid under pressure from the guide paths into a suction opening of a next-stage impeller. The return blades have a configuration in which a total cross sectional area of inlet openings of concave paths formed by a plurality of ribs is set to be equal to or larger than a cross sectional area of the suction port, while a total volume of the concave paths is set to be smaller than the total volume of non-path portions excluding the paths.

Abstract: A float wall heat shield for use on an endwall of a stator vane used in a gas turbine engine. The heat shield includes an attachment extending from a center of the heat shield to secure the shield to the vane. A plurality of ribs formed on the inside surface of the shield forms cooling channels extending in the streamwise direction. The leading edge of the shield curves downward over the leading edge of the endwall and forms a cooling air inlet. The trailing edge of the shield forms a cooling air exit extending in a straight direction to provide purge air for a rim cavity of an adjacent rotor blade assembly. The heat shield includes pressure and suction sides that conform to an outline of the airfoil of adjacent vanes, and forms cooling air exit gaps so that the cooling air passing through the channels can discharge to prevent inflow of the hot gas flow. The heat shield eliminates the need for film cooling holes.

Abstract: The present invention provides an axial-flow fan capable of entirely cooling an object to be cooled even when the distance between the object to be cooled and an air discharge opening of the axial-flow fan is short. A plurality of stationary blades 11A to 11E are disposed at intervals in a rotating direction of a rotor and located inside an air discharge opening 16 of an air channel 19. Each of the plurality of stationary blades 11A to 11E has an external end portion 11a connected to an inner wall portion of a fan housing 3, an internal end portion 11b connected to a peripheral wall portion 11B of a motor case 10, a discharge-side edge portion 11c formed between the external end portion 11a and the internal end portion 11b and located at a side of the air discharge opening 16, and a suction-side edge portion 11d formed between the external end portion 11a and the internal end portion 11b and located at a side of the air suction opening 14.

Abstract: A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a load transfer unit, a torque box rotatably positioned within the load transfer unit, and a plurality of struts. The load transfer unit has a first locking element and combines the first load and the second load into a combined load. The torque box has a second locking element that is engagable with the first locking element of the load transfer unit. The plurality of struts are connected between the torque box and the mount, and transfer the combined load from the torque box to the mount. The first locking element and the second locking element are at least one of a rib or a groove.

Abstract: A method for assembling a turbine nozzle for a gas turbine engine. The method includes providing a turbine nozzle including a plurality of airfoil vanes extending between an inner band and an outer band, wherein the outer band includes a forward hook assembly having a rail and at least one hook, providing at least one scalloped recessed area within the forward hook assembly at least one hook to facilitate reducing stresses induced to the turbine nozzle, and coupling the turbine nozzle into the gas turbine engine using the forward hook assembly such that the turbine nozzle is at least partially supported by the forward hook assembly.

Abstract: A guide vane arrangement 20 for a gas turbine engine (10, FIG. 1) includes a vane member 21 extending between inner and outer platforms 22, 24 which are respectively mounted on inner and outer mounting members 42, 34. One of the inner and outer platforms 22, 24 includes a resilient that abuts the respective inner or outer platform 22, 24 to permit relative movement between the inner or outer platform 22, 24 and the respective inner or outer mounting member 42, 34.

Abstract: A method for modifying a multistage compressor (101) involves exchanging the rotor blades of the first compressor rotor blade row (LA1) for modified rotor blades which have an identical blade leaf profile (121) to the original rotor blades and the blade angle (B?11) of which is different from the blade angle (B?10) of the original rotor blades. Furthermore, the blades of at least one further blade row (LAN, LEN) arranged downstream of the second compressor stage are exchanged for modified blades which have an identical blade leaf profile (125, 126) to the original blades and the blade angle (B?N1, B?N1) of which is different from the blade angle (B?NO, B?NO) of the original blades. The method makes it possible to increase the mass flow of a compressor and essentially maintain the stability reserve against stall.

Abstract: A gas turbine engine nozzle is described. The gas turbine engine nozzle includes at least one nozzle vane having a first end and a second end. The first end is coupled to an inner sidewall and the second end is coupled to an outer sidewall. The gas turbine engine nozzle also includes at least one stress relief pocket defined within at least one of the inner sidewall and the outer sidewall proximate to the at least one nozzle vane. The at least one stress relief pocket is configured to reduce stress on the proximate nozzle vane.

Abstract: In an exhaust gas turbocharger for an internal combustion engine, comprising a turbine rotor, which is rotatably housed in a rotor chamber through which exhaust gas coming from the internal combustion engine is conducted and wherein the flow around the turbine rotor is conditioned by means of a guide apparatus comprising a support ring with rotatably mounted guide vanes. For fixing a first distance (A) between the support ring and the contour sleeve, at least one spacer element with a longitudinal axis, an outer surface and a cross-sectional area is provided so as to have a streamlined shape forming in the exhaust gas flow only a relatively narrow wake line and the spacer element is so arranged that the wake line formed thereby extends essentially through a flow space between two adjacent guide vanes without disturbing the exhaust gas flow around these guide vanes.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: A process for adjusting a throat area (the flow capacity) between airfoils in an airfoil configuration such as a stator ring used in a small gas turbine engine. The airfoils are designed with an over-extending trailing edge forming a throat area sized such that a worst case tolerances design flow area would be achieved. A fluid with a flow rate representing the actual fluid for normal operation in the airfoil configuration is passed through the airfoil throats and the flow rate is measured. A specified portion of the leading edge of each airfoil is removed until the design flow rate through the airfoil configuration is achieved. A plurality of iterations of measuring flow rates and removing trailing edge material is performed until the design flow rate is achieved.

Abstract: An axial-flow fan unit that produces less noise is provided. Blades 19 are exposed from a venturi 29. The shape of each of the blades 19 is so defined that a space formed between at least an inner surface 28a of each of web leg sections 28A to 28C and an edge 19a of each of the blades 19 located in the radially outward direction of the blades 19 expands toward the ends of the web leg sections 28A to 28C (or web bodies 30A to 30C). With this arrangement, noise produced when the blades 19 rotate along the web leg sections 28A to 28C is reduced.

Abstract: A fluid flow machine has a main flow path in which at least one row of blades (2) is arranged, with at least one blade end of a blade row (2) being firmly connected to the main flow path confinement and, in an area of this fixed blade end at a sidewall (9), at least one longish, obstacle-type boundary layer barrier (11) is provided which in at least part of its course is oriented obliquely to the main flow direction, thereby deflecting fluid flowing near the sidewall towards the blade pressure side.

Abstract: A fan includes a fan housing and an impeller. The fan housing includes a frame, a base disposed in the frame, a plurality of stationary blades disposed between the frame and the base, and a plurality of airflow-guiding elements extending inward from the frame and toward the base. The airflow-guiding elements and the stationary blades are alternately arranged. The impeller is disposed in the fan housing.

Abstract: A kinetic hydropower generation system has a turbine and a generator coupled to the turbine. An underwater intake nozzle assembly is fluidly coupled to the turbine. For one embodiment, an underwater tower nozzle may be fluidly coupled between the turbine and the underwater intake nozzle assembly. The underwater intake nozzle assembly may include a collector and a converging nozzle.

Abstract: An axial flow turbine blade and diaphragm construction comprises an annulus of static turbine blades 20 and inner and outer spacer rings 40, 42 having apertures 41, 43 shaped to accommodate inner and outer platform portions 22, 23 of the blades, whereby the platform portions and the spacer rings together form inner and outer port walls of the turbine diaphragm. A particular feature of the blades is that the inner and outer platform portions 22 and 23 have straight side edges 22B, 22C and 23B, 23C, which are joined to each other by curved leading edges 22D and 23D that in plan view have a shape that follows the edge of the corner fillet 24 in the region of the leading edge 26 of the aerofoil 21.

Abstract: A gas turbine engine rotor stack includes one or more longitudinally outwardly concave spacers. Outboard surfaces of the spacers may be in close facing proximity to inboard tips of vane airfoils. The airfoils have dihedral and sweep.

Abstract: A flow-guiding member unit used for assembling a flow-guiding member comprising pluralities of vanes, an outer platform and an inner platform, the unit comprising an integral body member comprising one vane portion, an outer platform portion, and an inner platform portion, a first elastic member attached to a step of the outer platform portion, and a second elastic member attached to a step of the inner platform portion, the body member being formed by the thermal compression of sheet-molding compounds or fiber-reinforced resin pellets, and the first and second elastic members being made of a thermoplastic elastomer.

Abstract: A turbine that allows for the conversion of the kinetic energy of waterway to mechanical power for use in an energy accepting apparatus is described. The turbine has complimentary components that improve the power efficiency of the turbine. The turbine may include a blade shroud and a plurality of blades that are connected to the blade shroud. On the external surface of the blade shroud, a drive mechanism and/or a brake mechanism may be disposed. An inlet nozzle and outlet diffuser may be used in combination with the turbine. The turbine may be useful in a number of settings, including, but not limited to, streams, rivers, dams, ocean currents, or tidal areas that have continuous or semi-continuous water flow rates and windy environments.

Abstract: A Mixer/Ejector Wind/Water Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. Unique ejector concepts are used to fluid-dynamically improve many operational characteristics of conventional wind/water turbines for potential power generation improvements of 50% and above. Applicants' preferred MEWT embodiment comprises: an aerodynamically contoured turbine shroud with an inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass fluid flow. The MEWT can produce three or more time the power of its un-shrouded counterparts for the same frontal area, and can increase the productivity of wind farms by a factor of two or more. The same MEWT is safer and quieter providing improved wind turbine options for populated areas.

Abstract: A bling nozzle/carrier interface design for a steam turbine is provided wherein there is limited contact between the carrier (casing, shell) to allow for ease of assembly. There is also limited contact in strategic locations to both reduce the roll, or downstream deflection, of the inner portion and to improve disassembly due to limited contact in areas where corrosion can occur.

Abstract: A fluid flow engine (1), in particular a turbo engine, has at least one guide vane row (5) with a plurality of guide vanes (6) and at least one rotor blade row (7) with a plurality of rotor blades (8). One guide vane row (5) and one rotor blade row (7) that follows the former directly downstream with respect to a working gas flow (11), together form a stage (10) of the fluid flow engine (1).

Abstract: A turbine nozzle includes a row of vanes extending radially between annular outer and inner bands. The outer band includes a pair of radial flanges defining an annular seal groove therebetween. One of the flanges is crenelated to improve nozzle life.

Abstract: A ring fan and shroud guide system which includes a rotating fan member with a conical outer ring and a cylindrical shroud member overlapping at least a portion of the outer ring. A plurality of guide vanes are provided in the shroud which minimize the tangential velocity component of the air flow entering the tip-gap region and provide improved air flow through the system. The guide vanes can have a curved configuration.

Abstract: An inlet guide vane arrangement for a gas turbine is provided. The arrangement includes a plurality of guide vane duct elements, the guide vane duct elements include a suction side wall and a pressure side wall, both walls facing each other, and are designed to be adjoinable to another of the guide vane duct elements, such that the pressure side wall of one guide vane duct element cooperates with the suction side wall of the adjacent guide vane duct element thereby forming a guide vane. The guide vane duct element includes features to accept a key element adapted to be arranged between the pressure side wall and the adjacent suction side wall, when two guide vane duct elements are adjoining to one another, and to attach together both adjoining guide vane duct elements.

Abstract: A combustor heat shield sealing arrangement comprises a sealing rail extending from the combustor liner shell at the exit of the combustor for sealing engagement with a rail-less downstream end portion of the combustor heat shield. The sealing rail is offset relative to the downstream vane passage. Doing so may minimize the combustor/vane waterfall and, thus, minimize the horseshoe vortex effect at the leading edge of the turbine vanes.

Abstract: A wall configuration of an axial-flow machine which can reduce the secondary flow loss is provided. A trough is formed between a blade and another blade in the blade row and extends in at least an axial direction of the blade row. The region where the trough is formed is axially between a leading edge and a trailing edge of the blade. A center line of the trough has a curvature in the same direction as a camber line of the blade. A maximum amplitude of the trough is located adjacent to an axial center of the blade or located axially between the axial center and the leading edge of the blade.

Abstract: A method for cooling a shroud segment of a gas turbine engine includes providing a turbine shroud assembly including a shroud segment having a leading edge defining a forward face. A turbine nozzle is coupled to the turbine shroud assembly such that a gap is defined between an aft face of an outer band of the turbine nozzle and the forward face, wherein a lip formed on the aft face is positioned radially inwardly with respect to the gap and extends substantially axially downstream from the gap. Cooling air is directed into the gap. Cooling air exiting the gap impinges against the lip. Post impingement cooling air is directed at the forward face to facilitate forming a film cooling layer on the shroud segment. The film cooling layer is shielded from combustion gases flowing through the gas turbine engine.

Abstract: An arrangement for delivering gasses from can combustors of a can annular gas turbine combustion engine to a turbine first stage section including a first row of turbine blades, the arrangement including a flow-directing structure for each combustor, wherein each flow-directing structure includes a straight path and an annular chamber end, wherein the annular chamber ends together define an annular chamber for delivering the gas flow to the turbine first stage section, wherein gasses flow from respective combustors, through respective straight paths, and into the annular chamber as respective straight gas flows, and wherein the annular chamber is configured to unite the respective straight gas flows along respective shear planes to form a singular annular gas flow, and wherein the annular chamber is configured to impart circumferential motion to the singular annular gas flow before the singular annular gas flow exits the annular chamber to the first row of blades.