Abstract: A turbine nozzle assembly includes a plurality of nozzle segments and a nozzle support for supporting the nozzle segments. Each nozzle segment includes an outer band, an inner band and at least two vanes disposed between the outer and inner bands. A retention flange extends radially inwardly from the inner band and has a first hole formed therein. The nozzle support includes a recess formed therein and a mounting flange extending therefrom. The mounting flange is disposed in contact with the retention flange and has a second hole formed therein. A pin is disposed in the first and second holes to position the flanges with respect to one another. A pin retainer is disposed in the recess and has a holding flange for retaining the pin in place. The nozzle support includes a substantially conical portion and an air seal integrally formed thereto.

Abstract: A bladed rotor and surround assembly comprising an annular casing, a bladed rotor element that is rotatable about an axis concentrically within the casing, and an annular shroud liner. The shroud liner, typically made up of an annular array of circumferentially abutting shroud liner segments, is disposed within the casing in an annular radial space defined between the casing and an outer circumference of the bladed rotor. The shroud liner segments have location members to locate each segment within the casing. The location members and the annular radial space are configured to enable axial insertion of the shroud liner segment between the bladed rotor and the casing. In addition the location members and the annular radial space allow a limited amount of radial translation of the shroud segment during insertion. The location members also provide a positive radial location to prevent radial translation of the shroud segment once each shroud segment is in a final assembled position.

Abstract: The flow path shroud includes a plurality of generally channel-shaped shroud segments having forward and rearward rails interconnected by a flow path section along radial innermost portions of the rails. The volume bounded by the forward and rear rails and flow path sections is unbounded at the ends and the shroud therefore is without side walls. The free ends of the front and rear rails have relief cuts such that thermal induced bowing of the front and rear rails in the axial direction limits the mechanical stress applied to the turbine casing hooks. The thickness of the front and rear walls lies in an approximately 1:1 thickness ratio with the thickness of the flow path section.

Abstract: A stator assembly of a gas turbine engine includes first and second annular metal stator rims. The stator rims, positioned in parallel, include a plurality of ceramic blades therebetween, each ceramic blade having a rounded nose and a flattened and tapered tail. Each ceramic blade further includes an opening for receiving a mounting pin. The mounting pin mounts between the first and second annular stator rims, clamping and containing the ceramic airfoil therebetween in a position relative to an axis of the turbine engine.

Abstract: A guide device for a turbine with a guide-blade carrier installed in a turbine housing, preferably the housing of a steam turbine, and equipped with guide blades, includes positioning elements for positioning and fastening the guide blades to the guide-blade carrier and for ensuring a specific installation position of the guide blades. In order to simplify the production of the guide device, two halves of a guide-blade ring divided in the region of a parting plane of the turbine housing serve as the positioning elements. Radially extending profile holes for inserting a guide-blade root of each guide blade are formed in the guide-blade ring. At least one first holding element is preferably releasable and in each case fixes the guide-blade root to the guide-blade ring. At least one second holding element retains each of the two halves of the guide-blade ring on the guide-blade carrier.

Abstract: A support and alignment assembly for supporting and aligning a vane segment is provided. The support and alignment assembly comprises a torque plate which defines an opening for receiving an eccentric pin and a locking end member for receiving a lock socket member. An eccentric pin adjustably supported by the torque plate opening for supporting and aligning a vane segment is provided. A lock socket member adapted to securely receive the eccentric pin and rotated therewith, and adjustably engage the torque plate locking end is provided. The lock socket member receives the eccentric pin, such that when the eccentric pin is adjusted to align the vane segment, the lock socket member engages the torque plate locking end to secure the vane segment in the desired position.

Abstract: An exhaust gas turbine for an exhaust gas turbocharger has a nozzle ring having an inner ring and an outer ring supporting a plurality of guide vanes. The nozzle ring is diagonally supported between a covering ring and the inlet casing, with the outer ring bearing against the covering ring and the inner ring bearing against the inlet casing. The outer ring provides an axial expansion gap with gas inlet casing and a radial expansion gap with the gas outlet casing. The nozzle ring is free to expand into the axial and radial gaps as a result of thermal expansion, without causing stress to the adjacent components.

Abstract: A stator vane assembly for a gas turbine engine includes a plurality of stator vane segments and fasteners. Each stator vane segment includes an inner radial platform, an outer radial platform, at least one airfoil extending between said platforms, and a first mounting flange extending radially outward from said outer radial platform. Each first mounting flange is aligned with a second mounting flange extending radially inward from an outer case surrounding the stator vane assembly. Each fastener includes a bolt extending through the first and second mounting flanges, a nut for threaded engagement with the bolt, and apparatus for preventing vibration of the fasteners.

Abstract: A turbine diaphragm assembly includes inner and outer endwall rings, nozzle vanes each with a tenon extending outwardly from one end, and inner and outer retaining rings. The inner and outer endwall rings each have inner and outer radial surfaces and a plurality of openings extending radially through the inner and outer endwall rings about their circumference. Each of the vanes is positioned between the inner and outer endwall rings, with one of the tenons protruding radially inward through one of the openings in the inner endwall ring and with the other tenon protruding radially outward through one of the openings in the outer endwall ring. The inner radial surface of the inner endwall ring is located adjacent to the outer radial surface of the inner retaining ring with the portion of the tenons protruding radially inward through the openings in the inner endwall ring and positioned in a first circumferential groove in the outer radial surface of the inner retaining ring.

Abstract: A highly accurate, reproducible and economnical method of manufacturing split diaphragms for use in turbomachinery wherein the diaphragm is first machined axially, and then split across the axial machining to for precision positioning channels into which a pin of matching dimensions is placed to preserve the circularity and stability of the diaphragm when the diaphragm pieces are replaced together about a turbine shaft. Alternatively, the diaphragm is split first and is then machined axially through the split to form precision positioning channels.

Abstract: A repair kit for replacing an unserviceable vane assembly in a turbine engine includes a serviceable vane subassembly 120 having a serviceable airfoil 124 with a base 134 attached to the root end thereof and an opposing base 156 which is unattached to but slidably engagable with the serviceable airfoil. The opposing base is slipped over the tip end of the airfoil and slid toward the opposing base. The vane subassembly and opposing base are pivoted into position between inner and outer engine cases in place of an unserviceable vane assembly so that receptor sockets 148, 150 in the attached base engage support pins 72 extending from the inner case. An adhesive 182 is applied to the tip end of the serviceable airfoil and the opposing base is translated into its installed position near the tip end of the airfoil. Upon curing of the adhesive, the opposing base becomes attached to the airfoil. The base is secured to the outer case by studs 196 and nuts 198.

Abstract: An airfoil and nozzle assembly including an outer shroud having a plurality of vane members attached to an inner surface and having a cantilevered end. The assembly further includes a inner shroud being formed by a plurality of segments. Each of the segments having a first end and a second end and having a recess positioned in each of the ends. The cantilevered end of the vane member being positioned in the recess. The airfoil and nozzle assembly being made from a material having a lower rate of thermal expansion than that of the components to which the airfoil and nozzle assembly is attached.

Abstract: The reheat tub 10 in a double-flow steam turbine is provided with additional setback from the rotor buckets 16 by forming a three-part reheat tub construction including first and second discrete diaphragm segments 26a and third inner ring segments 28a. The annular arrays of these segments are dimensioned to enable greater axial spacing between the nozzles and buckets. To refurbish an in-service double-flow turbine, the damaged reheat tub is removed and cut along axial and radial part lines to form discrete first and second diaphragm segments. The diaphragm segment nozzles are then refurbished by machining an arcuate hook 46 with a tapered surface 48 on the inner ring portion. The annulus 28 is provided with a complementary hook 50 and tapered surface 52. The diaphragm and annulus segments 26a and 28a are aligned end-to-end and rotated to join the segments along the hooks.

Abstract: Power generation turbines having different power outputs for different power grid frequency applications have modular second and third stages, rotors, bucket wheels for all stages and other ancillary parts. The first and second turbines have sizes not geometrically scaled according to speed. Four-stage turbines having different outputs for different power grid frequencies not geometrically scaled have an identical annulus through the first, second and third stages, different geometry in the first and fourth stages, and identical geometry in the second and third stages.

Abstract: A gas turbine engine's nozzle structure includes a nozzle support ring, a plurality of shroud segments, and a plurality of airfoil vanes. The plurality of shroud segments are distributed around the nozzle support ring. Each airfoil vane is connected to a corresponding shroud segment so that the airfoil vanes are also distributed around the nozzle support ring. Each shroud segment has a hook engaging the nozzle support ring so that the shroud segments and corresponding airfoil vanes are supported by the nozzle support ring. The nozzle support ring, the shroud segments, and the airfoil vanes may be ceramic.

Abstract: A stator vane assembly for a gas turbine engine that includes a plurality of circumferentially spaced ceramic vanes, each of which has an inner and outer ceramic shroud, and a ceramic post extending from one of the shrouds, and a metallic platform having a plurality of circumferentially spaced recesses. The posts are inserted into a metallic sleeve and then brazed. The brazed sleeves are then mounted in the recesses. A method for assembling these components to form the stator assembly is also described.

Abstract: A split retaining ring 22 has deep internal scallops 26 which clear lugs 36 during installation while the ring fits within lip 40. The ring is opened with ridges 30 clearing lugs 36 while the ring is rotated. Shallow internal scallops rest on and lock with lugs 36 in the final position.

Abstract: A system for locking the radial extremity of vanes, wherein the extremities include heels situated behind a ring for delimiting the flow of gases, the heels including hooks between which extend other hooks of the ring. Bolts are disposed in the notches of both types of hooks and fasteners are used to secure the bolts. The assembly obtained is compact, rigid and able to be embodied easily and effectively. It is also virtually free of clearances and vibrations.

Abstract: In a gas turbine having a blade carrier (2) which is suspended coaxially in a turbine casing (3), both the turbine casing and the blade carrier are provided with a horizontal junction plane. An exhaust gas casing (5), whose bounding walls consist essentially of an annular inner part on the hub side and an annular outer part (7), is gastightly connected by means of an annular flange (7A) to an annular flange (3A) of the turbine casing (3). Between the annular flanges a two-part separating ring (13) having at least one conically extending face (13A) is disposed. The angle of the conically extending face (13A) has a self-locking effect.

Abstract: The backbone which is a load carrying support member of the aft end of the compressor of a gas turbine engine is fabricated from an annular disk-like element that is generally straight in cross section. The points of attachment permit circumferential thermal growth with radial restraint and snugness at judicious locations for minimizing scrubbing of the case-tied segmented inner stator case.

Abstract: A stator for a turbo-engine and a method for mounting the stator serve to improve fixing of the vanes of the stator and resistance of these vanes to impact in the event foreign bodies enter the turbo-engine. The stator includes several vanes radially maintained by their external and internal pivots between an internal ferrule and an external casing. The internal ferrule includes at least one bore intended to receive one of the internal pivots and the external casing includes a mechanism for the radial positioning and locking of the vane so as to make it possible to keep the internal pivot of the vane in the bore.

Abstract: A full-round compressor casing assembly is employed in a gas turbine engine which includes alternating axially-arranged stages of movable blades and stationary vanes, with each stage of movable blades having a row of rotor blades attached to and extending radially outwardly from a rotor and each stage of stationary vanes having a row of stator vanes. The full-round casing assembly includes a plurality of vane sectors with the vanes projecting therefrom in defining each stage of stationary vanes, an inner casing inserted over the rotor and blades, and an outer casing inserted over the inner casing and spaced radially outwardly therefrom. The inner casing includes alternating axially-arranged full-round shroud bands and mounting bands. Each shroud band encircles the outer ends of the rotor blades. Each mounting band has a circumferential guide track on an interior side mounting the vane sectors in side-by-side relation around the mounting band with the vanes extending radially inwardly.

Abstract: In a gas turbine engine having an annular casing with a stationary support structure, a high pressure turbine, and an annular high pressure turbine nozzle having at least one stage which includes a plurality of circumferentially aligned nozzle segments and which is disposed in the annular casing between a combustor and the high pressure turbine, a nozzle support arrangement is provided for mounting each nozzle segment to the stationary support structure. The arrangement includes a single mounting pin mounted on and extending from an annular nozzle support flange on the casing support structure and a hole defined in an oval shape in the one end portion of an inner band flange for receiving the mounting pin in an interference fitting relation.

Abstract: A structural frame component for use in a gas turbine engine having an outer casing includes an annular inner central hub, a plurality of circumferentially-spaced struts attached at their inner ends to the inner central hub and extending therefrom toward the outer casing of the engine, and an attachment ring including an annular member and a plurality of circumferentially-spaced clevises attached to the annular member and extending radially inwardly therefrom. The annular member encircles and is spaced radially outwardly from the outer ends of the struts and is releasably attached to the flanges on the turbine casings. Each clevis is releasably attached to the outer end of a respective one of the struts.

Abstract: A composite multi-stage fan stator assembly including a continuous ring composite fan case assembly supports at least one composite fan stator assembly for disposal between two respective fan rotor stages. The fan case assembly includes a forward fan case assembly and an aft fan case assembly use to mount and secure a fan stator stage axially disposed between them using hook and slot attachment means. A rotor access means comprising at least one removable vane segment in the fan stator stage and a corresponding access port through the composite fan case assembly for removing the removable vane segment is also provided.

Abstract: The invention comprises the use of a thermal barrier coating on a member of a gas turbine engine component with one surface of the member exposed to high temperature but not exposed to high velocity gases, as an insulating material to slow the heat transfer to the substrate of the component member and allow thermal gradients within acceptable material limits between the thermal barrier coated member and the remainder of the component. In a particular application, the use of a thermal barrier coating enables making a high pressure turbine nozzle integral with a discourager seal lip, eliminating fasteners protruding into the rotor/stator cavity and split lines between segments of the prior art that allowed high temperature gas ingestion further into the cavity and caused windage losses.

Abstract: A method and apparatus which facilitate separation of a gas turbofan powerplant into modules for shipping, maintenance and repair is disclosed. Various construction details are developed which provide means for mounting a fan cowling to an engine core in a manner which permits transference of operational loads from the fan cowling to the engine core and separation of the fan cowling from the engine core. In one embodiment, a fan cowling (46) is attached to an engine core (18) by a plurality of radially extending through struts (64). The through struts include a bolted joint (72) which permits separation of a powerplant (12) into a first module and a second module. For this embodiment, a method for varying between an assembled and disassembled condition is comprised of manipulating the joints between an engaged and disengaged position and axially moving the separate modules along a longitudinal centerline (14).

Abstract: A locator pin retention device comprises a pin with threaded and smooth portions cooperating with a bushing having spaced apart threaded and smooth portions to allow alignment of inner and outer gas turbine engine members exposed to different thermal environments, allowing thermal growth of the inner member in a radially outward direction toward the outer member and reacting axial and circumferential loads to prevent transverse movement to the outer structural member. The device reduces machining of the structural members because machined retention means are inexpensive and replaceable parts.

Abstract: The invention comprises the use of a split retaining ring cooperating with an inner nozzle support member to retain nozzle segments and a stationary seal without the use of threaded fasteners. Elimination of bolt heads from the rotor/stator cavity reduces windage losses and enables a shortening of the inner nozzle band overhang, reducing the requirement for high pressure cooling and cavity purge air.

Abstract: An inventive turbine nozzle attachment comprises a nozzle mount having a radial and tangential load carrying hook and a radial load carrying land. The nozzle hook fits onto a stud in a stationary nozzle support. The stud is adapted for carrying the tangential and radial load from a respective one of a plurality of nozzle segments, each nozzle segment includes a nozzle mount for coupling to a corresponding stud. The plurality of nozzle segments are joined circumferentially to form an annular turbine nozzle. Each nozzle segment further includes the radial land on one circumferential end of the mount and a circumferentially extending support member on an opposite circumferential end of the segment. The radial support member of one segment rests on the land of an adjacent segment. The gas loads on the nozzle segments cause each segment to load up on the support studs in the tangential and radial directions. The support members on each opposite segment end load radially downward on a land of an adjacent segment.

Abstract: An axial flow turbomachine's engine core (16) and radially outwardly disposed fan case (18) are joined together with a radially extending segmented fan case strut (10). The strut (10) is segmented into a radially inner portion (20) and a radially outer portion (20) at a midspanly disposed strut joint (14). The strut joint (14) has an axially extending tapered tongue (26) which slidably engages with a mating axially extending groove (46). A radially extending flange (36) disposed proximate to the trailing edge (35) of the inner portion (20) is bolted to the radially extending flange (56) disposed proximate to the trailing edge (55) of the outward portion (40) when the tongue (26) is fully engaged with the groove (46) to releasably secure the strut joint (14). Another embodiment shows a pair of interlocked axially extending channels (60) each having a U-shaped cross-section replacing the interlocked tongue and groove (26,46) of the first embodiment.

Abstract: A stator vane liner assembly includes seal keys supported in slots in the ends of vane liner segments in an engine casing. Stationary vanes supported in the liner segments for directing an engine airflow are urged against the keys by the engine airflow gas loads. The seal keys engage the ends of adjacent vane liners for sealing, and prevent further motion of the vanes with respect to the liner segments due to the engine airflow gas loads. Secondary seal means can be slidably captured between the seal key and vane liner segment to prevent axial and radial leakage around the seal key. The liner assembly reduces leakage of engine airflow and helps to isolate the engine casing from the thermal effects of leakage of engine airflow.

Abstract: The clearances between an array of high pressure turbine blades and its surrounding high pressure turbine shroud as well as the clearances between an array of low pressure turbine blades and its associated low pressure turbine shroud are carefully controlled by a support structure which provides for evenly controlled circumferential cooling of the shroud support structure. Radial loads on the shroud support structure are reduced by counterbalancing loads imposed on the support structure by the shroud with predetermined pressure loads controlled and set through a series of cooling air cavities. The high pressure turbine shroud and low pressure turbine shroud are formed as integral segments in a segmented shroud design. Forward and aft shroud hanger members interconnect the shroud with its support so as to facilitate assembly and disassembly of the shroud segments to and from their support structure.

Abstract: The after end of each of the segments of a segmented stator at the end of the compressor section of a gas turbine engine is supported to the full hoop outer case by an annular disk-like element that is generally straight in cross-section where each segment is joined to the disk-like element by a single bolt extending axially through a radial flange integrally formed on each of the segments and the bolt is located intermediate the ends of the flange and the flange fits into an annular groove formed in the end of the disk-like element permitting circumferential thermal growth with radial restraint.

Abstract: In a gas turbine engine having a ceramic nozzle guide vane supported by a metal turbine casing the radially outer end of the vane is provided with opposed frustoconical sections which converge towards each other onto a middle cylindrical section. A metal split ring surrounds the cylindrical section, and the radially inner and outer ends of the ring abut the frustoconical sections. The split ring is provided with a flange which cooperates with a groove structure on the turbine casing, thus enclosing the split ring to the casing. A bolt means fastens together two sections of the casing either side of the vane, thereby holding the split ring against the vane. On increase in temperature the split ring expands more than does the vane. The ends of the split ring therefore slide against the frustoconical surfaces of the vane to take up the expansion, and in so doing maintain contact with the vane.

Abstract: Power output of a steam turbine is increased by removal of at least one stage of blading in order to increase mass flow through the turbine. A flow guide or annular ring is installed in the space in the inner cylinder or blade ring surrounding the area from which the blading stage has been removed. The flow guide has a radially inner surface conforming generally to the surface configuration of the inner cylinder surrounding the turbine blades. The flow guide presents a relatively smooth, continuous surface to inlet steam flow so that flow separation and turbulence are reduced with a corresponding increase in efficiency.

Abstract: A compressor diaphragm assembly for combustion turbines includes a plurality of vane airfoils, each of which is formed with an integral inner shroud and an integral outer shroud, joined together by connecting bars which transfer loads between the vane airfoils and the casing slots of the turbine within which the vane airfoils are suspended.

Abstract: A water jet propulsion module is generated about a central axis and has an inlet opening and a discharge opening concentric with said axis. The module includes a stator having an inner wall and an outer wall with curved stator vanes connected between said inner and outer walls. An impeller shroud is adjustably connected to the outer stator wall. A motor secured to the stator drives a planetary gear drive attached to an impeller by a parabolic impeller cone. The impeller draws water into the inlet opening and drives the water past the stator vanes out of the discharge opening along a substantially linear path at high speed and pressure.

Abstract: A stator vane stage in a split-case, variable geometry axial flow compressor includes two 180-degree spoke-like arrays of stator vanes on upper and lower case halves of the compressor case and a pair of unitary, 180-degree arc shroud ring segments. Each stator vane has a pivot shaft at one end rotatably supported in a radial bore in the corresponding case half by a bushing and a cylindrical vane button at the other end. Each shroud ring segment has a corresponding plurality of cylindrical vane button sockets in an outer surface thereof which rotatably receives a corresponding vane button. The spoke-like array of the stator vanes rigidly positions the shroud ring segments relative to the compressor case.

Abstract: A stator vane array is made by cutting vane blanks from a machined linear bar having a predetermined trapezoidal section using a wire tool electroerosion machine, the blanks being cut to an outline which conforms to the shape of the head and root portions of each vane. Each blank is then machined by electroerosion or by chemical machining to form the back and the face of the blade of the vane, and after carrying out finishing operations the vanes are butt-welded together edge to edge to form a complete annular array or a sector thereof. The method is particularly applicable to the manufacture of stator arrays for turbomachine compressors in which the stator vanes have blades with an evolutive profile.

Abstract: A gas turbine of the type having turbine vanes retained in a cylinder and utilizing torque pins to transmit the torque load on the vanes to the cylinder is provided with improved structure for enabling insertion and withdrawal of the pin from engagement with the outer vane shroud in the vicinity of the cylinder flanges.

Abstract: The cartridge of a fan outlet for a multiple flow turbojet engine is made of composite material and includes two thick lateral strips (8a, 8b) positioned in the interior of the outer case and a narrow central band pierced with slots (10) in which guide vanes (5), provided with an in-molded cover, come to be fixed. The outer cartridge can be integral with the support of soundproofing panels (7 and 9) and support the abradable part (6) facing fan (3).

Abstract: An adjustable spacer (20) is located in a unison ring (16) disposed about a gas turbine engine case (18). The spacer (20) includes a pad bolt (44) having a flattened surface (52) for contacting the case (18). The pad bolt (44) is adjusted radially by a threaded cylinder (28) and adjusting nut (36). The assembly is locked in place by a locknut (54) which includes a frangible link (72) for separating a headed portion (70) from a threaded portion (68).

Abstract: A two-stage, high-pressure centrifugal pump comprises a pump housing and at least one pair of external inlets and outlets for charging and discharging each stage of the pump. The inlets and outlets are located through the periphery of the pump for allowing on-line maintenance. Prerotator vanes are located along the interior wall of the pump housing and convey a fluid from the external inlet to the impeller while reducing the inlet relative velocity at the impeller inlet and primarily at the impeller inlet tip. A pair of face-to-face impellers located along the pump shaft are designed to increase the fluid velocity while transferring fluid to a vaneless radial diffuser. The diffuser then decreases fluid velocity and increases fluid pressure due to increasing diffuser volume. From the diffuser the fluid is conveyed into a fold-over volute which is likewise designed to increase fluid pressure while additionally eliminating flow patterns which would increase losses within the system.

Abstract: Methods and apparatus for vane segment alignment and support in a combustion turbine. The vane segment alignment device is comprised of a rotatable, eccentric bushing and pin which is inserted into a slot of the vane segment. The eccentric bushing is further comprised of a cover plate which is peened to a splined torque plate thus holding the eccentric bushing in place against the vane segment but allowing for fine adjustments of the alignment of the vane segments. The vane segment support and alignment device provides for efficient and economical adjustment of the vane segments especially in electric generating plants where combustion turbines undergo high peak load operation. Additionally, the vane segment support and alignment device transfers torques and moments generated by aerodynamic flow from the vane segments to an inner cylinder thereby reducing the amount of misalignment due to aerodynamic drag.

Abstract: A compressor diaphragm assembly for combustion turbines includes a plurality of vane airfoils, each of which is formed with an integral inner shroud. A segmented seal carrier is suspended from the inner shrouds, and an outer ring supports the plurality of vane airfoils from a casing portion of the turbine in a parallel relationship at a predetermined angle with respect to the longitudinal axis of the turbine. The outer ring has one or more grooves formed at the predetermined angle to engagably receive respective rows of the vane airfoils at their outer portion. Each seal carrier segment includes a pair of disc-engaging seals, and is formed to be engaged with the inner shrouds of one or more vane airfoils, in order to provide a labyrinth seal with discs assembled to form a rotating shaft.

Abstract: The invention comprises a turbine nozzle and nozzle support assembly in which a turbine nozzle support seating flange is positioned adjacent to a turbine nozzle mounting flange and pins are used to affix the turbine nozzle to the nozzle support. Retainer strips are installed into the nozzle support to trap the pins in engagement with the mounting and seating flanges. In the preferred embodiment of the invention seal means is provided for restricting the airflow through the completed turbine nozzle and nozzle support assembly.

Abstract: A gas turbine with at least one fixed guide vane ring (1) with a sealing ring (3) cooperating with a sealing member on the turbine rotor (7). The sealing ring (3) is connected to the guide vane ring (1) through a number of links (19) which are suitably oriented in a substantially tangential direction. The attachment of the sealing ring (3) by means of the links (19) means a perfect centering of the sealing ring (3) relative to the rotor (7) when the guide vane ring (1) expands relative to the sealing ring (3).

Abstract: A stator assembly 14 includes an annular support structure, such as an outer case 24, and an element, such as a stator vane assembly 30. The stator vane assembly is restrained against circumferential movement by a key 58 integral with the stator vane which engages the outer case. Various construction details, including a radial projection 82 on the key, are developed which improve the fatigue life of the support structure and enhance the ease of assembly of the structure. In one method of assembling the structure, the method includes the step of using the radial projection on the key as an alignment device.

Abstract: An inner shroud for a gas turbine engine is described comprising six approximately equiangular segments each segment adapted to securely contain a plurality of vane stems. The segments comprise interlocking first and second sections forming a channel having an aperture suitably sized to securely contain the vane stem. The sections when fit together form an outer recess area suitably sized to substantially accommodate the button portion of the vane stem and an inner cavity suitably sized to accommodate the inner portion of the vane stem. This results in reduced shroud curling when used in a split case compressor.