Abstract: A coupling device for coupling a turbine upstream guide vane which is coupled to a supporting part which itself attached to a stabilizing part is disclosed. The coupling device includes a interlocking device for interlocking a supporting end of the supporting part with a stabilizing end of the stabilizing part, and a retaining part to keep the supporting end and the stabilizing end interlocked. The coupling device may be used to couple an upstream guide vane of a turbojet turbine.

Abstract: A method and system of supporting removable static components in a turbine engine stator assembly is described. The method comprises the steps of engaging a stator hanger located at a first location on a first static component with a post located on a first static structure whereby the post supports at least a part of the weight of the first static component, engaging a stator stopper located at a second location on the first static component that is located circumferentially apart from the first location with the stator hanger that is located on a second static component, and engaging a hook located at a third location on the first static component with a second static structure whereby the second static structure supports at least a part of the weight of the first static component.

Abstract: An impeller, for example, a guide wheel for a hydrodynamic speed variator/torque converter, including a plurality of blades. Each blade has a blade base and a blade tip area. Stiffening means are situated in at least one of the blades in at least the blade base area and/or the blade tip area.

Abstract: A locking member for a device for fastening ring sectors to an aircraft turbine engine casing is disclosed. The member has first and second clamping branches, which are connected together by curving joining portions, via a connecting branch. The joining portion of center thickness E1 has an inside surface of mean radius Rm1, and the joining portion of center thickness E2 has an inside surface of mean radius Rm2. Thickness E1 is strictly smaller than thickness E2, and mean radius Rm1 is strictly smaller than mean radius Rm2.

Abstract: An exemplary embodiment of the invention is directed to a turbine engine having a circumferential casing with a circumferentially extending slot formed in an inner wall. A radially inwardly facing fin-ring is disposed in the slot and has a radially inwardly projecting fin extending axially there across. A radially inwardly extending stator blade has a base and an airfoil. The base is disposed in the casing slot, radially inwardly of the fin-ring. A complementary base slot is disposed in the stator blade base and is configured to receive the fin therein for the transfer of a circumferential force, applied to the stator blade, to the fin-ring.

Abstract: A reaction mount system that provides support for the stator vane for a gas turbine engine is described comprising a stator hanger located on an outer band at a first location and a stator stopper located at a second location that is located circumferentially apart from the first location. A stator assembly for a gas turbine engine is described, the stator assembly comprising a stator vane having an airfoil, an outer band located on a radially outer end of the airfoil, a shroud hanger located axially adjacent to the outer band, the shroud hanger comprising a post wherein at least a portion of the post extends in an axial direction over a portion of the outer band, and a reaction mount system located on the outer band wherein the reaction mount system engages with the post to provide support for the stator vane.

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.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1. 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 are joined smoothly with one another to form a complete airfoil shape.

Abstract: A turbine nozzle assembly and a method for assembling the turbine nozzle assembly with respect to a combustor of a gas turbine engine are provided. The method includes coupling a radial outer retaining ring to an aft end of the combustor. A plurality of turbine nozzles are provided. Each turbine nozzle includes an inner band, a radially opposing outer band, and at least one vane extending between the inner band and the outer band. The outer band of each turbine nozzle is coupled to the outer retaining ring to define the turbine nozzle assembly. An inner retaining ring is positioned about an axis of the gas turbine engine and coupled to the inner band of each turbine nozzle.

Abstract: A turbine nozzle is constructed from a plurality of associated circumferential turbine nozzle segments each of which incorporates at least one pre-formed annular-segment passage bounded at a first azimuthal boundary by a first portion of a first bounding nozzle vane, and at a second azimuthal boundary by a second portion of a second bounding nozzle vane, with the at least one pre-formed annular-segment passage therebetween, wherein when assembled in the turbine nozzle, a first portion of a first bounding nozzle vane of one circumferential turbine nozzle segment is joined to a second portion of a second bounding nozzle vane of another adjacent circumferential turbine nozzle segment so as to form therebetween a nozzle vane of the turbine nozzle, wherein the minimum through-flow area of the associated at least one pre-formed annular-segment passage is substantially unaffected by the assembly of the circumferential turbine nozzle segments to form the turbine nozzle.

Abstract: A vane assembly for a gas turbine engine comprising an axial loading element disposed between a mounting element of the vane ring and a cooperating portion of the supporting structure, such as to generate a load force therebetween in an axial direction. The axial load force limits unwanted relative movement between the vane ring and the supporting structure during operation of the gas turbine engine.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1. 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 are joined smoothly with one another to form a complete airfoil shape.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1. 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 are joined smoothly with one another to form a complete airfoil shape.

Abstract: A compressor for compressing a gas comprises an impeller wheel mounted within a housing (2) defining an inlet and an outlet. The inlet comprises a map-width enhanced structure with an annular flow passage (11) defined between inner (9) and outer (7) tubular walls. The flow passage (11) is in fluid communication with the impeller wheel by virtue of a slot (13) in the inner wall (9). A flow-conditioning member (14) is positioned in the annular flow passage (11) and serves to remove swirl from the gas flow that recirculates through the passage. The flow-conditioning member (14) comprises a body penetrated by a plurality of bores (15). The arrangement provides for a significant improvement in the surge margin of the compressor and is particularly suitable for use in a turbocharger.

Abstract: A one piece axial flow turbine case with an inlet volute and an outlet volute with an axial flow turbine positioned between the inlet and outlet volutes, in which the turbine vanes and blades can be installed or removed from one side of the case without disassembling the two volutes. The one piece turbine case eliminates the mating flange, the flange seal, and the flange bolts required in the two piece turbine volute case. The one piece axial flow turbine case reduces the part count, reduces the weight of the turbine, improves the reliability of the turbine, and improved the performance of the turbine. The annular guide vane assembly with an annular outer shroud having guide vanes extending from the shroud is inserted through an opening of the turbine case. The vane outer shroud extends aft to form an outer shroud for the turbine blades.

Abstract: A turbine shroud assembly is disclosed, the shroud assembly including an outer shroud, at least one inner shroud attached to the outer shroud, and at least one discourager enclosed within the inner shroud. The discourager prevents the hot gas or steam in the turbine from having a direct line of access to the outer shroud. In one embodiment, one inner shroud is provided for the shroud assembly, with one discourager enclosed within the inner shroud, the discourager positioned offset from the inner shroud so as to extend past the inner shroud and into an inner shroud of a neighboring shroud assembly. In another embodiment, a plurality of inner shrouds are provided, each inner shroud enclosing a discourager, the discouragers being adjacent to each other within the inner shrouds and positioned offset from the inner shrouds so as to cover a gap between the inner shrouds.

Abstract: The present invention broadly comprises a blade for a torque converter stator including a body, a first end, and a second end; a stator blade assembly; and a stator for a torque converter including a plurality of blades, a housing, and a core ring. The first end is arranged to engage the housing and the second end is arranged to engage the core ring. In some aspects, the blade is stamped or the body is arcuate. The assembly includes a plurality of separate blades. In some aspects, each blade is stamped or bodies for adjacent blades at least partially overlap with respect to a radial plane through an axis for the stator. In some aspects, an axial opening between blades widens radially outward or inward.

Abstract: A fan holder is used for dissipating heat from electronic devices. The fan holder includes a fan bracket and an expansion bracket. The fan bracket has a first plate and a second plate. A plurality of partitions is configured between the first plate and the second plate, for connecting the first plate with the second plate. Thereby four same-size receiving rooms are formed in the fan bracket. These receiving rooms are used to receive fans. A plurality of insert slots is defined in four corners of the receiving rooms adjacent to the fixing member. The expansion bracket includes a front plate and a pair of side plates extending perpendicularly from two opposite sides of the front plate. A plurality of hooks is formed on corners of the backside of the side plates, inserting into the insert slots to mount the expansion bracket on the fan bracket.

Abstract: A system and method for reducing vibration and wear to adjacent platform surfaces and mounting locations of a vane segment in a gas turbine engine is disclosed. The present invention seeks to improve the interaction between mating faces of adjacent gas turbine vane assemblies by increasing the surface area where contact between the adjacent vanes occurs, so as to increase the damping capability and reduce the wear to the mating surfaces.

Abstract: A centrifugal pump with a housing having one or more impellers having an axial or semiaxial, open or closed design disposed therein and an intake channel mounted upstream of the first impeller. A plurality of grooves that are distributed around the circumference and extend in the direction of flow are arranged within the wall area of the intake channel. In the housing wall of the intake channel there is a closed annular wall area constructed between a point of entry of the first impeller and the proximate ends of the grooves, whereby the grooves are operatively connected exclusively with the space in the intake channel.

Abstract: A turbine vane ID support system usable to support the ID of a turbine vane and including a transition seal system and a turbine vane ID forward rail seal system. The transition seal system may seal the turbine vane ID support body to a transition, and the turbine vane ID forward rail seal system may seal the turbine vane ID support body to a turbine vane. Use of the transition seal system and the turbine vane ID forward rail seal system eliminates the problems inherent with conventional seals used to seal transitions directly to turbine vanes. The turbine vane ID support system may also be configured such that the turbine vane ID support system may be removed to facilitate removal of turbine vanes and blades for repair or replacement.

Abstract: A stator assembly for a gas turbine engine includes: (a) an outer shroud having a circumferential array of outer slots; (b) an inner shroud having a circumferential array of inner slots; (c) a plurality of airfoil-shaped vanes extending between the inner and outer shrouds, each vane having inner and outer ends which are received in the inner and outer slots; and (d) an annular, resilient retention ring spring which engages the inner ends of the vanes and urges them in a radially inward direction.

Abstract: A turbomachine has a stator and a rotor, wherein the rotor has blades (21) and the stator has a housing (20) and stationary guide vanes (17), wherein the guide vanes (17) form guide vane rings (11, 12) that adjoin the housing (20) with radially outwardly positioned ends (18) and adjoin the rotor with radially inwardly positioned ends. The guide vane rings are spoke-centered with the aid of bearing journals or guide pins (24) allocated to the housing (20) and penetrating through the housing (20). The guide pins (24) extend at a slant relative to the radial direction and the axial direction of the turbomachine, wherein the ends (26) of the guide pins (24) reaching into the housing engage in forked elements (27) allocated to the radially outer ends (18) of the guide vane rings (11, 12).

Abstract: A load pin has an end portion, and a vane has a base with a cutout in the base, wherein the end portion of the load pin engages a wall portion of the cutout in the base of the vane, thereby inhibiting any movement of the vane in a particular direction.

Abstract: An assembly of airfoils in a compressor of a turbine engine that includes at least three axially stacked rows of airfoils: a middle airfoil row, a first upstream airfoil row, and a first downstream airfoil row. The middle airfoil row may be bordered on each side by the first upstream airfoil row, which comprises the first row of airfoils in the upstream direction from the middle airfoil row, and the first downstream airfoil row, which comprises the first row of airfoils in the downstream direction from the middle airfoil row. The first upstream airfoil row and the first downstream airfoil row may have substantially the same number of similarly shaped airfoils. The first upstream airfoil row and the first downstream airfoil row each may comprise a row of rotor blades, which rotate at substantially the same speed during operation. The middle airfoil row may comprise a row of stator blades, which remains substantially stationary during operation.

Abstract: The strut is for use in a gas turbine engine has body, typically having an airfoil shape, having a leading edge and a trailing edge. The leading edge has at least one gas inlet in direct fluid communication with at least one outlet located in the trailing edge through which gas may be redirected from the leading edge to the trailing edge through the strut for injection back into a wake region downstream of the strut.

Abstract: A compressor vane having a root, a tip and an airfoil portion extending between the root and the tip is disclosed. A grommet is used in conjunction with the vane and has a lip sealingly surrounding a portion of the vane root and a circumferential portion protruding around a perimeter of the lip in engagement with a surface of a platform of the vane root. The circumferential portion has a profile similar to that of the airfoil portion.

Abstract: A vane for a vane assembly of a gas turbine engine includes a vane root connected to the airfoil portion opposite a tip thereof. The vane root includes a platform and a button portion interconnecting the platform and the airfoil position. The button portion has relatively blunt leading and trailing ends which respectively protrude beyond leading and trailing edges of the airfoil portion.

Abstract: A turbine stage includes a stator nozzle having a row of vanes mounted between inner and outer bands. The inner band terminates in an ovate ledge converging aft from the vanes with radially outer and inner convex surfaces joined at a convex apex. The ovate ledge reduces aerodynamic losses at the rotary seal with a row of following turbine rotor blades.

Abstract: A vane assembly for a gas turbine engine including a shroud with openings defined about a circumference of the shroud and vanes extending radially from the shroud with a vane tip in each opening. Isolating apparatus are disposed in each opening to isolate the vane tip from the shroud ring. Each vane tip is engaged with the shroud by retaining apparatus for restricting movement of the vane tip in an axial direction relative to the shroud.

Abstract: A vane including a root, a tip and an airfoil portion extending between the root and the tip, the vane also including a button portion interconnecting the airfoil portion and the root. The button portion protrudes beyond a profile of the airfoil a distance less than the root. The button portion includes leading and trailing ends free of sharp edges. The leading and trailing ends respectively protrude beyond leading and trailing edges of the airfoil portion.

Abstract: A compression and vacuum-producing machine includes a housing, at least one rotating disk having a plurality of blades rotationally supported within the housing, and at least one stationary disk having a plurality of blades fixedly attached to the housing. A drive shaft includes a generally tapered surface and rotatably drives the rotating disks to increase the energy of a fluid stream disposed within the housing. The compression machine includes a transmission in mechanical communication with the drive shaft to convert a rotational input to a desired rotational speed and drive the shaft at the desired speed.

Abstract: A device (10) for suspending gas channel elements, in particular for suspending guide blades or guide blade segments or gas channel segments, on a housing of a gas turbines is provided. The device comprises first plate-shaped elements (11, 12, 13, 14) and second plate-shaped elements (15, 16, 17), whereby the first plate-shaped elements (11, 12, 13, 14) and the second plate-shaped elements (15, 16, 17) are connected together by web-like elements (18) which extend in an essentially perpendicular manner in relation to the first and second elements and form a meandering or crenelated profile.

Abstract: Aspects of the invention relate to a modular turbine vane assembly. The vane assembly includes an airfoil portion, an outer shroud and an inner shroud. The airfoil portion can be made of at least two segments. Preferably, the components are connected together so as to permit assembly and disassembly of the vane. Thus, in the event of damage to the vane, repair involves the replacement of only the damaged subcomponents as opposed to the entire vane. The modular design facilitates the use of various materials in the vane, including materials that are dissimilar. Thus, suitable materials can be selected to optimize component life, cooling air usage, aerodynamic performance, and cost. Because the vane is an assemblage of smaller sub-components as opposed to one unitary structure, the individual components of the vane can be more easily manufactured and more intricate features can be included.

Abstract: A method of assembling a stator assembly includes coupling at least one stator ring segment to a portion of a casing using at least one circumferential stator ring groove defined in the casing. The method also includes coupling at least one stator blade assembly to a portion of the stator ring segment such that at least one radial passage is at least partially defined by at least one of the stator blade assembly and the stator ring segment. The stator assembly includes at least one first radial passage defined within a portion of the stator ring segment. The assembly also includes at least one second radial passage coupled in flow communication with the first radial passage. The second radial passage is at least partially adjacent to at least one of a portion of the stator blade assembly and a portion of the stator ring segment.

Abstract: A method for assembling a gas turbine engine is provided. The method includes providing a turbine nozzle including an outer band and an inner band, wherein each band includes a leading edge, a trailing edge, and a body extending therebetween. At least one of the outer band and the inner band has at least one radial tab extending outward therefrom. The method also includes coupling at least one seal between at least one of the radial tabs extending from the outer band and the inner band and a respective leading edge of the outer and inner band. The method also includes positioning at least one non-planar seal support against at least one portion of the seal.

Abstract: A vane assembly for a gas turbine engine including a shroud ring with openings and isolating arrangement isolating a vane extremity within each opening, the isolating arrangement cooperating to form a continuous gas path surface completely covering at least an axial portion of a surface of the shroud ring.

Abstract: A flange for supporting arcuate shrouds and shroud hangers comprising at least one arcuate rail, each arcuate rail having an inner radius, a first taper location, a first taper region, a second taper location, a second taper region, wherein the thickness of at least a portion of the first taper region is tapered and wherein the thickness of at least a portion of the second taper region is tapered.

Abstract: An automotive compressor is provided having a casing defining an intake section for fluid for compression, and a delivery section for delivering the compressed fluid. An impeller is movable angularly inside the casing to increase the pressure of the fluid. A distributor is carried by the intake section of the casing to conduct the fluid for compression to the impeller. The casing and the distributor are defined by separate members connected releasably to each other.

Abstract: A mounting device, for mounting a plurality of fans (50) to a server chassis (70), includes a tray (20), a plurality of brackets (30), and a plurality of fasteners (40). The tray includes a plurality of pairs of mounting sections each pair fixed with a corresponding bracket. Each bracket is U-shaped and includes a pair of side plates (32) for sandwiching a corresponding fan therebetween. Each bracket defines a pair of coaxial locking holes (35?) in the side plates. Each fastener includes a pair of locking ends (42) received in the locking holes of a corresponding bracket to thereby sandwich the corresponding fan in the bracket. Each side plate defines an outlet (34) having a contour corresponding to a contour of an outlet of a corresponding fan, and each mounting section of the tray has a contour corresponding to a contour of the outlet of a corresponding fan.

Abstract: The distributor sectors (25) of a turbomachine are secured adjacent to a casing (31) with sealing sectors (32) alternating with them in the axial direction. The distributor sectors (25) are provided with force resistant faces (37; 39) through which forces exerted on the distributor sectors are transmitted to the casing. The inner surface of the casing (31) is smoother and is not fitted with any hooks; consequently, this casing (31) is less complicated to make and is less mechanically stressed to retain the 10 distributor sectors, and the distributor sectors may be installed by a purely axial movement.

Abstract: A gas turbine engine compressor including a stator assembly and a method of assembling the same are provided. The method includes providing a compressor casing including at least two stator vane casing rails extending from the casing, coupling a rail liner within each respective casing rail, and coupling a stator vane assembly including two dovetails, and at least two stator vanes coupled together within the casing rails within the liner such that a first dovetail is received within a first casing rail and a first rail liner, and a second dovetail is received within a second casing rail and a second rail liner.

Abstract: A repaired turbine engine stationary vane assembly, including at least one airfoil bonded between inner and outer bands, is provided by a method of providing first and second vane assembly members bonded at respective circumferential edges, for example by brazing or welding. The first vane assembly member includes the outer band, the airfoil, an inner flange, and a first segment of the inner band with a first edge, spaced from the flange and extending between and through inner band circumferential edge portions. The second vane assembly member includes a second segment of the inner band including a second edge of shape and size matched with the first edge and extending through the inner band circumferential edge portions.

Abstract: A spring seal for sealing a gap defined between first and second gas turbine engine components. The spring seal has a grasping portion for graspingly receiving a portion of the first component, and a spring loading portion adapted to extend between the first and second gas turbine engine components for spring loading the first and second gas turbine engine components relative to one another.

Abstract: A mechanical arrangement for protection against catastrophic nozzle failures includes a turbine nozzle segment including an inner platform rail, a turbine nozzle inner support ring in part in axial registration with the rail on one side, an inner retainer segment secured to the inner support ring and in part in axially spaced registration relative to the rail on an axial side of the rail opposite from the support ring, a first inclined conical surface on the inner retainer segment, and a second inclined conical surface on the inner platform rail of the turbine nozzle, the second inclined conical surface opposing the first inclined conical surface, so as to bind the inner platform rail to the turbine nozzle between the inner retainer segment and the inner support ring, resulting in a wedge lock that prevents the inner platform from being lost downstream into rotating hardware of the turbine.

Abstract: An anti-rotation lock for preventing circumferential movement of a stator segment in relation to a split case to which it is mounted is disclosed. A racetrack shaped pocket, disposed within the case and proximate the stator segment, is suitably sized to receive a lug and a spring pin. The lug is received in the pocket and protrudes radially inward from the case and is engagable by the stator segment, thus preventing circumferential movement with respect to the case. The spring pin is received adjacent to the lug and compressively retains the lug in the pocket.

Abstract: A turbine nozzle includes a hollow vane joined to opposite inner and outer bands. The inner band includes a forward lip under the leading edge of the vane, an aft lip under the trailing edge of the vane, and a mounting flange spaced therebetween. An impingement bore extends obliquely and aft from the base of the mounting flange under a corner of the inner band toward the aft lip for impingement cooling thereof.

Abstract: Arcuate seal layers conforming with one another are disposed between inner retainer segments and inner rails of nozzle segments of a gas turbine. The layers are secured to the aft axial face of the segments and project radially outwardly to seal against the forward axial faces of the rails. The rear axial faces of the rails have chordal seals for sealing against the forward axial faces of the support rings. The seal layers have radial cuts misaligned with one another in an axial direction to preclude leakage flows through gaps formed by the cuts. Arcuate spacers are staggered circumferentially with the arcuate retainer segments whereby an intermediate pressure plenum is formed between the finger seals and chordal seals.

Abstract: Nozzle segments are secured to a retention ring against circumferential rotation by anti-rotation pins extending generally axially between the outer bands of the nozzle segments and the retention ring. Retention plate segments overlie the ends of the pins, preventing axial removal thereof. To remove a selected nozzle segment, inner diameter retention plate segments and selected retention plate segments are removed, the latter exposing the ends of the pins for axial withdrawal. Upon removal of a predetermined number of pins, the nozzle segments adjacent the selected segment are displaced away from the latter segment to open a gap between the selected segment and adjacent segments whereby the selected segment can be removed in an axial direction.

Abstract: A housing including an outer casing provided with bearer hooks for stator rings and sealing rings. The hooks are discontinuous angularly and joined to a casing by tenon and mortise assemblies. The hooks and the casing may therefore be made in different materials, the hook material having good resistance to heating and the other material lending itself better to machining and forming. Ventilation, clearance piloting and heat protection are facilitated.