Abstract: A turbomachine stator stage including two coaxial shrouds, respectively an inner shroud and an outer shroud with substantially radial vanes extending therebetween, the radially outer ends of the vanes being welded to the outer shroud and the radially inner ends of the vanes passing through orifices in an outer ring of the inner shroud, the inner ends being held by elastomer spacers in an annular cavity formed between the outer ring and an inner ring that is fastened to the outer ring.

Abstract: A strut for application between an outer ring and an inner ring in a gas turbine structure and a gas turbine structure including such a strut are provided. The strut includes an end portion which has a diverging shape so that an internal space is formed in the end portion for receiving at least part of an engine mount. Engine mounting lugs can be positioned at such struts.

Abstract: An airfoil assembly is disclosed. The airfoil assembly may comprise a series of airfoils such as vanes radially extending between an ID endwall and a substantially concentric OD endwall. The airfoils are circumferentially spaced apart and define a plurality of fluid flow passages between adjacent airfoils. The ID endwall and the OD endwall define contoured regions to optimize fluid flow through the passages. A geometric relationship between the ID endwall contoured regions and the OD endwall contoured regions assures that the throat area generally increases or decreases in the direction of fluid flow.

Abstract: A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage. At least one of the airfoils have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the midspan plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°.

Abstract: A vane structure for a gas turbine engine includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a metal alloy inner 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 structural and aerodynamic module including two blades each extending along a longitudinal axis, in which each blade includes a leading edge, a trailing edge, a radially inner edge, and a radially outer edge, is provided. The module also includes a radially inner platform mechanically connecting the radially inner edges of the two blades, and a radially outer platform mechanically connecting the radially outer edges of the two blades such that the two blades and the radially outer and inner platforms delimit a flow stream. The two blades and the platforms are made from a composite material and the two blades are fixed on the radially outer and inner platforms using screw-nut assemblies.

Abstract: The invention relates to a nozzle stage for a turbomachine compressor, the stage comprising two coaxial shrouds, a radially inner shroud and a radially outer shroud, and radial vanes extending between the shrouds and being connected via their ends to the shrouds, together with a support for abradable material that is mounted by crimping onto the upstream and downstream edges of the inner shroud, the inner shroud presenting openings in which the radially inner ends of the vanes are inserted and fastened. The radially inner ends of the vanes are plane and do not have any projecting tenons.

Abstract: A strut configuration of a static vane ring used in a gas turbine engine having an enlarged end section at least at one of the opposed ends thereof to be welded or brazed to either an outer or inner duct wall of the vane ring. The enlarged end section provides a inner corner curve with a predetermined fillet radius between the strut and the duct wall.

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

Abstract: The present invention relates generally to propulsion systems, and, more particularly, to a propulsion system including an axial flow water pump assembly and a laminar flow box assembly for generating a streamline laminar slipstream of water velocity that is used in aquatic therapy, aquatic sport fitness rehabilitation, aquatic rehabilitation, swimming, and a variety of other functional therapy and training modalities.

Abstract: A nozzle blade and nozzle ring assembly includes a nozzle blade having radially inner and outer sidewalls with an airfoil portion extending therebetween; the inner and outer sidewalls walls formed with axially-extending first surface features along forward and aft marginal edges of the inner and outer sidewalls, respectively; and radially inner and outer nozzle rings formed with corresponding axially-extending second surface features mated with the first surface features, wherein the radially inner and outer sidewalls are welded to the radially inner and outer nozzle rings only along the mated first and second surface features.

Abstract: A fan assembly includes an axial flow fan between an inlet stator and an outlet stator. The inlet stator has inlet stator blades which extend outwardly from an inner ring. Each inlet stator blade has a downstream edge which has a tangent which is oriented at a first variable angle with respect to a plane which is perpendicular to the fan axis. The first angle increases with increasing distance from the inner support ring. The outlet stator has a plurality of outlet stator blades which extend outwardly from a second inner ring. Each outlet stator blade has an upstream edge which has a tangent which is oriented at a second variable angle with respect to a plane which is perpendicular to the fan axis. The second angle decreases with increasing distance from the inner ring.

Abstract: An example airfoil retention arrangement includes a retention assembly having a first retention segment and a second retention segment. Each of the retention segments is separately moveable to an installed position relative to an airfoil assembly and a support structure. The retention segments each have a portion position between a lip of the airfoil assembly and a collar of the support structure when the retention segments are in the installed position. The retention assembly is configured to limit radial movement of an airfoil relative to the support structure when in the installed position.

Abstract: A method for assembling a rotary machine includes providing a rotor including a plurality of rotor wheels. The method also includes positioning the rotor such that at least a portion of a stationary portion of the rotary machine extends at least partially about the rotor. The method further includes providing a blade that includes a blade platform that is formed with a substantially double-C shape. The method also includes coupling the blade to the rotor.

Abstract: A steam turbine diaphragm stage having a self-aligning flow splitter is disclosed. In one embodiment, a steam turbine flow splitter body is disclosed, the steam turbine flow splitter body having a central portion and two end portions, and including: a flow divider proximate to the central portion; and a substantially radially outward extending hook proximate to at least one of the two end portions.

Abstract: A high temperature resistant turbine stator vane with an airfoil section made from oxide dispersion strengthened (ODS) material extruded through a die, an internal cooling circuit is machined into the airfoil section after the extrusion, and then two endwalls are formed separately and then secured to the airfoil section ends to form the stator vane. Film cooling holes can be drilled into the airfoil section and the endwalls.

Abstract: A columnar air moving device can comprise separately formed modular stator vanes in a stator vane assembly. The stator vanes can be arranged in a radial pattern, and can direct air in an axial direction. The modular stator vanes, as well as other components of the stator vane assembly, can be replaced, adjusted, and/or removed from the columnar air moving device.

Abstract: The present invention relates to a strut for a turbine center frame of a jet engine, in particular a gas turbine, with a first end for disposition on an internal structure of the turbine center frame and a second end opposite the first end for attaching the strut on a housing or an internal boundary wall of the turbine center frame, and on the second end at least one flange-like element with at least one first aperture is removably arranged with at least one first aperture for accommodating or passing through an attachment means. The invention further relates to a turbine center frame for a jet engine, in particular a gas turbine as well as a method for producing a turbine center frame of a jet engine, in particular a gas turbine.

Abstract: A stator vane assembly comprising inner and outer support rings connected by an annular array of stator vanes at locations around the supporting rings, at least one of said stator vanes in said array being a separate, pre-formed stator vane which is slidably connected to one or both of the supporting rings for radial movement relative to the respective support ring thereby to accommodate relative radial expansion of the support rings.

Abstract: A compressor diaphragm for a gas turbine engine having improved wear capability, manufacturability, and assembly techniques is disclosed. The diaphragm includes a shiplap-type joint at an outer vane platform for connecting to adjacent vane assemblies and a clamshell-like assembly of a seal box secures and seals regions around the inner vane platform of the compressor diaphragm so as to reduce wear between the seal box and the vane assemblies. The inner platform of the diaphragm segments are fastened to each other through circumferentially-oriented fasteners at the inner diameter platform.

Abstract: A turbine vane ring has a radially outer and inner annular shrouds defining therebetween an annular gaspath. Circumferentially spaced-apart airfoil vanes extend radially across the gaspath between the outer and the inner shrouds. The radially outer shroud has a circumferentially continuous cylindrical wall extending axially from a leading edge to a trailing edge. A set of circumferentially distributed stress relieving slots is defined in the leading edge of the cylindrical wall at locations adjacent to the leading edge of at least some of said airfoil vanes. The stress relieving slots extend radially through the cylindrical wall from the radially inner surface to the opposed radially outer surface thereof.

Abstract: A static vane ring for gas turbine engines includes a plurality of radial struts extending between and interconnecting outer and inner duct walls which define an annular duct therebetween. A load transfer apparatus is attached to at least one of the outer and inner duct walls to transfer load from vane to ring, and between vanes.

Abstract: Guide vane stage of a turbine engine comprising a series of fixed blades connecting an inner collar to an outer collar, characterized in that said fixed blades comprise attachment platforms with flat surfaces that co-operate with a plurality of juxtaposed flat facets, the flat facets being located on the inner face of the outer collar in order to ensure attachment with a contact of a flat/flat type between the fixed blades and the outer collar.

Abstract: A stator blade ring is provided with which the possibilities of thermal deformation and a decrease in strength can be reduced, the shape flexibility can be ensured, and the compression performance can be improved. It includes stator blade segments (21) in each of which an inner shroud portion (31) and an outer shroud portion (29) divided corresponding to one stator blade (27) are provided at both ends of the stator blade (27) so as to be formed as a single part, and connecting members (23) that are formed of arch-shaped plates and are disposed on at least one of the inner shroud portions (31) and the outer shroud portions (29) of the stator blade segments (21) adjoining in a circumferential direction, on a side opposite to the stator blades (27). The stator blade segments (21) are welded to the connecting members (23) at a portion of the length thereof in the circumferential direction.

Abstract: Bearing support structure for turbines comprising an inner ring (1) and an outer ring (2) radially connected by means of structural vanes (5) and aerodynamic vanes (6) in a circumference-like arrangement between both rings (1, 2). The aerodynamic vanes (6) are thinner and lighter than the structural vanes (5), and the number of structural vanes (5) depends exclusively on the loads of the bearing (3) housed in the structure to be transmitted to the anchoring points (7) of the engine assembly located in the outer ring (2), and on the amount of service fluids which must go through between the inner ring (1) and the outer ring (2), while the number of aerodynamic vanes (6) and their section depends exclusively on the aerodynamic requirements demanded from the support structure for the straightening of the turbine main flow. Thus, the structural vanes (5) fulfill only structural functions and the aerodynamic vanes (6) fulfill only aerodynamic functions.

Abstract: In exemplary embodiments, a nozzle can include a first flow wall, a second flow wall and a vane disposed between the first and second flow walls, wherein the vane is mechanically coupled to the first flow wall and in contact with the second flow wall.

Abstract: Plasma generators (48, 49, 70, 71) in an endwall (25) of an airfoil (22) induce aerodynamic flows in directions (50) that modify streamlines (47) of the endwall boundary layer toward a streamline geometry (46) of a midspan region of the airfoil. This reduces vortices (42) generated by the momentum deficit of the boundary layer, increasing aerodynamic efficiency. The plasma generators may be arrayed around the leading edge as well as between two airfoils (22) in a gas turbine nozzle structure, and may be positioned at correction points (68) in streamlines caused by surface contouring (66) of the endwall. The plasma generators may be oriented to generate flow vectors (74) that combine with boundary layer flow vectors (72) to produce resultant flow vectors (76) in directions that reduce turbulence.

Abstract: A retaining seal assembly for use in a gas turbine engine is provided. The retaining seal assembly comprises an outer retaining ring coupled to an aft end of a gas turbine engine combustor. A turbine nozzle is coupled to the outer retaining ring and comprises an outer band. The outer band comprises a leading edge and an opposing trailing edge that defines a slot. A retention seal comprises a first end positioned within the slot, a generally opposing second end that contacts the outer retaining ring, and a body extending between the first end and the second end. The body further comprises an insertion portion positioned within a passage formed in the outer band. The retention seal is fabricated from a resilient material and is configured to facilitate coupling the turbine nozzle to the outer retaining ring.

Abstract: A section of a gas turbine engine including a radial spoke is provided. The spoke includes an aerodynamic shape with a leading side and a trailing side and, extending from the leading side to the trailing side, a first side and a second side, opposite the first side. The spoke also includes at least one flow guiding element arranged on at least the first side.

Abstract: A generating line of a casing surrounding an outer periphery of vanes of a stator disposed downstream of a rotor of the axial-flow compressor includes: a recessed region recessed outward in a radial direction from a position forward of a front edge of each of the vanes to a position rearward of a rear edge of the vane; and a protruding region bulging inward in the radial direction at an intermediate position of the recessed region in a front-rear direction thereof. Thus, a distribution of static pressure in the radial direction on a surface of the vane is improved by a first recessed portion forward of the protruding region, and the static pressure on the tip side is raised by a second recessed portion rearward of the protruding region.

Abstract: An inner shroud assembly includes an aft core segment mountable to a forward core segment to support a multiple of vanes for rotational movement relative thereto. A shroud backing plate segment engageable with the aft core segment and at least one fastener which passes through the shroud backing plate, the aft core segment and the forward core segment.

Abstract: A system and method for configuring a steam turbine to accommodate changing resource conditions, such as may be encountered with geothermal wells. A plurality of sets of nozzle/blade assemblies are provided for installation in a diaphragm structure and on a rotor, respectively. As the condition of steam provided to the turbine changes, a different set of nozzle/blade assemblies may be installed to maintain a preferred thermodynamic efficiency for the turbine.

Abstract: A nozzle segment is disclosed that includes a first platform configured to be connected with a casing of a gas turbine engine, a second platform configured to be connected with the casing, the second platform being disposed apart from the first platform in a radial direction of the gas turbine engine, and a plurality of blades disposed between the first and second platforms and connected thereto, a portion of an inside surface of the first platform or the second platform being scalloped so as to increase a throat area of the nozzle segment in order to increase the nozzle segment's mass flow rate handling capability.

Abstract: A cooling fan having a fan housing, a motor which is positioned within the fan housing and a plurality of electronics components which are associated with the motor includes at least one strut which extends radially between the motor and the fan housing and on which the electronics components are mounted.

Abstract: A stem (34) extends from a second part (30) through a hole (28) in a first part (22). A groove (38) around the stem provides a non-threaded contact surface (42) for a ring element (44) around the stem. The ring element exerts an inward force against the non-threaded contact surface at an angle that creates axial tension (T) in the stem, pulling the second part against the first part. The ring element is formed of a material that shrinks relative to the stem by sintering. The ring element may include a split collet (44C) that fits partly into the groove, and a compression ring (44E) around the collet. The non-threaded contact surface and a mating distal surface (48) of the ring element may have conic geometries (64). After shrinkage, the ring element is locked onto the stem.

Abstract: An impeller is provided for a pump unit, in particular for a waste water pump unit, having two cover plates (2, 4), which are spaced apart from one another in the axial direction (X) and are connected to one another by at least one connecting element (8). The impeller has at least one blade (12, 14) which is arranged between the two cover plates (2, 4) and extends from an inner diameter of the impeller to an outer diameter of the impeller. The blade (12, 14) has a continuous slot (16), which extends from the edge (22, 24) of the blade (12, 14) which is situated at the inner diameter to the edge (26, 28) of the blade (12, 14) which is situated at the outer diameter. A pump unit is also provided having an impeller of this type.

Abstract: A support frame includes a rail engaging a hook of a composite article having plys. The rail included a rail contact surface generally conformal to and contacting a hook contact surface of the hook. The rail and hook contact surfaces being substantially normal to the plys beneath the hook contact surface. One embodiment of the article is a composite nozzle segment including one or more airfoils extending radially between arcuate radially outer and inner band segments having plys curved about a centerline axis and the rail engages a hook of the radially inner band segment. The hook and the rail may be straight or arcuate. The frame includes a central body extending axially aftwardly from the rail to an aft frame flange. A frame pin may be mounted on the frame, engage the inner band segment or one of the airfoils, and may extend into a cavity in the airfoil.

Abstract: A turbine includes an inner casing, a rotor extending in a longitudinal direction, and rows of buckets transversely disposed on the rotor. A bearing cone covering a portion of the rotor and a flow guide extending from the inner casing define an annular passage for flow of exhaust gases. Exhaust gas movement is facilitated by a guide cap having a streamlined surface and situated in a downstream direction of the flow guide, a tip leakage flow injection channel to inject exhaust gases at the inner surface of the flow guide, an incline of the casing of the turbine surrounding the last stage buckets relative to the longitudinal axis, or use of a first portion of the annular passage with a substantially constant surface area and a second portion of the annular passage with a progressively increasing surface area.

Abstract: A turbine nozzle includes a hollow vane mounted between inner and outer bands. The inner band includes a mounting flange between forward and aft lips. An aft pocket is found in the inner band between the flange and aft lip. And, an impingement bore extends through the flange into the windward half of the pocket and is directed aft toward the opposite leeward half of the pocket for co-rotation with purge flow during operation.

Abstract: An inner shroud portion and an outer shroud portion dividedly formed per stationary blade are formed integrally with each stationary blade. A plurality of the stationary blades adjacent to each other in a circumferential direction are coupled together by a band member at the outer shroud portions. The inner shroud portions are held between seal holders which are formed as two divided members in the flowing direction of a working fluid, which are fastened by a bolt, and which have a length corresponding to the plurality of the stationary blades. The plurality of stationary blades, the inner and outer shroud portions, the band member, and the seal holders assembled in this manner constitute a unit. A plurality of the units are connected in the circumferential direction to constitute a stationary blade ring of an axial compressor.

Abstract: A vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The shell includes a region having a depth-wise coefficient of thermal expansion and a second coefficient of thermal expansion transverse thereto, the depth-wise coefficient of thermal expansion being greater than the second coefficient of thermal expansion.

Abstract: An inlet case for a small gas turbine engine, where the inlet case is formed as a hybrid piece with a metallic inner shroud cylinder and plastic guide vanes and plastic outer shroud molded around the metallic inner shroud cylinder. The metallic inner shroud cylinder carries an electric generator and provides for a good convective heat transfer surface to carry heat away from the electric generator and into the inlet air flow entering the engine. The plastic guide vanes and outer shroud allow for a light weight inlet case assembly that is also much easier to form the airfoil shapes than a machined metallic inlet case. The plastic guide vanes and outer shroud are injection molded around the metallic inner shroud cylinder to produce a rigid single inlet case. The metallic cylinder includes axial extending slots that receive the lower ends of the guide vanes during the injection molding process.

Abstract: A stator assembly having an inner shroud and an outer shroud with a plurality of airfoils extending between the shrouds, and a vibration damping horn extending from one of the shrouds and aligned with the airfoil, the vibration damping horn having a higher stiffness than the airfoil, the vibration damping horn extends into a damping chamber formed between the shroud and a seal plate, and the damping chamber is filled with ceramic balls that rub against the vibration damping horn to dissipate vibration energy from the airfoil by friction.

Abstract: A steam turbine nozzle assembly having a flush aperture is disclosed. In one embodiment, the steam turbine nozzle assembly includes a diaphragm assembly comprising: an inner diaphragm ring segment; an outer diaphragm ring segment; a static nozzle blade positioned between the inner diaphragm ring segment and the outer diaphragm ring segment; and a first cavity between the static nozzle blade and one of the inner diaphragm ring segment or the outer diaphragm ring segment; wherein the one of the inner diaphragm ring segment or the outer diaphragm ring segment includes a first aperture fluidly connected with the first cavity.

Abstract: The monocrystalline turbomachine blade according to the invention that is cast and directionally solidified, is disclosed. The blade includes an airfoil with a leading edge, a pressure face, a suction face, a trailing edge, a skeleton and having a longitudinal axis, the faces and having a neck line, respectively a pressure face neck and a suction face neck relative to the adjacent blade in the turbomachine rotor of which it forms an element; an endpiece of the airfoil, such as a heel or a platform, having an airfoil end face, on the stream side, forming an angle with the axis ZZ; and a connection zone between the airfoil and the airfoil end face. The connection zone forms a fattening of the airfoil. The connection zone extends about the leading edge between a point P1 situated on the suction face of the airfoil upstream of the suction face neck and a point P3 situated on the pressure face of the airfoil upstream of the pressure face neck.

Abstract: A damping arrangement for guide vanes, in particular for guide vanes of a gas turbine or an aircraft engine, is disclosed. Referring to this damping arrangement, the radially external ends of the guide vanes of a guide vane grid or a guide vane ring are mounted to a housing. The radially internal ends of the guide vanes form an inner shroud. At least one seal bearing is mounted to the inner shroud of the guide vanes. At least one spring element is installed between the inner shroud of the guide vanes and the, or each, seal bearing. The, or each, spring element is configured as a leaf spring.

Abstract: A vane assembly for a gas turbine engine comprising a number of radial loading elements disposed between lugs of the vane ring and the vane support, such as to generate a radial load force against the vane ring. The radial load force prevents unwanted relative movement between the vane ring and the vane support during operation of the gas turbine engine.

Abstract: A stator vane segment, for constructing a circumferential array of like segments in a gas turbine engine, each segment in the array being separated by an axially extending joint from an adjacent segment and being releasably mounted to an outer engine casing. Each stator vane segment has: a number of vane airfoils spanning radially between an inner platform and an outer platform, and the outer platform includes: a casing mounting fastener on an outer surface and mating lateral joint edges extending between forward and aft edges.

Abstract: A retention structure includes a center body including an outer surface, an enclosed end, an open end, and a contact section, the outer surface adapted to define a first portion of a flowpath, and the contact section extending radially outwardly from a centerline and located on the enclosed end and configured to reduce a radial and a torsional component of a first load that exceeds a first threshold applied to the contact section, when the turbine rotates and applies the first load to the contact section and an energy absorber coupled to the center body, disposed adjacent to the contact section, and having an outer surface adapted to define a second portion of the flowpath, the energy absorber further adapted to collapse, when the turbine rotates and contacts the energy absorber and applies a second load that exceeds a second threshold to the energy absorber.