Abstract: The invention is a turbomachinery module (10) whose forwardmost vanes, which are the most damage susceptible vanes in the module, are easily removable and replaceable without substantial disassembly of the module. The module includes a case (12) and a forwardmost array (1V) of vanes. Each vane (34) of the forwardmost array has an axially proximal and distal end (90, 92) relative to the forward end (16) of the case. The distal end of each vane has a foot (102) that abuts but is not connected to a vane guide (32) on the case. The proximal end of each vane has an attachment bracket (110) that can be secured to or disengaged from a vane support (28) on the case. Vane removal is accomplished by disengaging the attachment bracket (110) from the vane support (28) and withdrawing the vane through the forward end of the case. The invention improves upon conventional turbine modules in which the forwardmost vane array is removable only from the aft end of the case after the module has been substantially disassembled.

Abstract: A gas turbine first-stage stator blade sealing structure for preventing the sealing air from leaking from the inside even if the blade falls or inclines due to thermal stress. A rear flange (12) of a first-stage stator blade (31) is formed in an arcuate shape having a straight rib (10). A stator blade support ring (13) contacts the straight rib (10) to form a sealing face. When the rear flange (12) and the stator blade support ring (13) fall or incline relative to each other due to thermal stress during operation, the upper end or lower end of the rib (10) contacts linearly with the face of the stator blade support ring (13) so that no clearance is established to inhibit leakage of the sealing air. In the prior art, where the horizontal rib (10) is absent, an arcuate clearance is established between the stator blade support ring (13) and the rear flange (12) as the support ring (13) inclines, and thus sealing air is allowed to leak from the inside to the gas passages.

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 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 seating spring is provided for a compressor stator having a radially outer casing with a circumferential casing slot for mounting a plurality of circumferentially adjoining vane sectors at outer bands thereof. The seating spring includes a reaction tab configured to abut the casing at one side of the casing slot. A resilient spring arm is fixedly joined to the reaction tab and is configured to abut a respective one of the outer bands to in-turn bias the one outer band against the casing at an opposite side of the casing slot.

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 stationary vane assembly for a turbo-machine in which the vane is restrained against motion in the circumferential direction by first and second locking pins. The second locking pin extends radially through a turbine cylinder and engages a notch in a downstream support rail formed on the vane outer shroud. The first locking pin is affixed to the front radial flange of the cylinder and has a projection that extends into a notch in an upstream support rail formed on the outer shroud. An over-sized slot in the first locking pin allows the circumferential location at which the first locking pin is fixed to the cylinder to be adjusted, thereby ensuring that the first locking pin can be pre-loaded against the outer shroud notch at assembly in a manner that will allow it to restrain the motion of the vane.

Abstract: A fan stator includes a split outer casing having a pair of outer rails, and a pair of key slots disposed at a splitline thereof. A plurality of standard stator vanes have outer platforms and hooks which engage the casing rails for supporting the vanes, with the vanes also having inner hooks extending from inner platforms thereof. A pair of locking stator vanes are disposed at the casing splitline and include an outer platform having outer hooks which engage the casing rails, an anti-rotation key disposed in the casing key slot, and an inner platform having first and second locking hooks extending therefrom. The first locking hook is equal in size with the first inner hooks and includes a first dam blocking the first locking hook at one end thereof, and the second locking hook is axially shorter than the second inner hooks and includes a second dam blocking the second locking hook at the same end thereof.

Abstract: The invention relates to a method and a device for mounting an axial turbo-machine, preferably a low-pressure compressor for a gas turbine, constructed without a parting line with a whole or constructed rotor. From the design point of view, problems arise regarding the mounting of the stationary guide vane rings in the case of a design without a parting line and a whole rotor. The problem is solved by dividing the guide vane rings into sectors in a number greater than two. These sectors are brought radially into position and are guided and fixed in the correct position by guide rings which are applied around each guide vane ring composed from sectors. Each composed guide vane ring with the surrounding guide ring is guided and fixed to the preceding guide ring and all the guide vane rings are successively built up around the whole or constructed rotor. The guide rings mounted together constitute a stiff annular element.

Abstract: The arcuate vane support segments (26) each carry a plurality of vanes (28) and have a pair of axially extending feet (38). These feet do not slide axially into a groove, but move radially against an arm (22) of the "T" shaped air seal. The casing ring 62 is translated axially in place entrapping the feet (38).

Abstract: The present invention discloses a spring clip made of a directionally solidified nickel-base superalloy for use in a high pressure compressor stator sub-assembly of a gas turbine engine. The spring clip includes a body section and a pair of arms integrally connected to opposing sides of the body section and the spring clip is used as a means for attaching circumferentially segmented flowpath liners to an annular casing. Each arm of the spring clips exerts a spring force against a flowpath liner mount lug causing the mount lug to be seated radially against an inner surface of the casing and axially against an annular seal, wherein the pair of arms of each spring clip engage mount lugs located on circumferentially adjacent ones of the flowpath liners.

Abstract: A steam turbine with replaceable nozzle portions including a replacement ring element welded to the remaining portion of the original turbine, the replacement ring element having a groove seat with tapered spaced opposing walls to receive a plurality of vane portions releasably locked in the groove, stabilized and sealed to prevent steam leakage therearound.

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 gas turbine engine stator assembly includes an annular casing, a stator nozzle segment, and a shroud joined therewith. The nozzle segment includes an outer band having a forward hook joined to a complementary forward hook extending from the casing. The outer band also includes a plurality of circumferentially spaced apart stator lugs defining therebetween stator slots. The stator lugs are disposed between an aft flange and complementary lugs extending from the casing. Slots defined respectively between the stator and casing lugs are axially aligned for receiving axially extending lugs on the shroud for restraining rotation of the stator segment about the centerline axis of the casing.

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: 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: A turbine assembly includes a unitary rotor spool having first and second rotor discs. A set of first blades having axial entry dovetails are joined to the first disc, and a set of second blades having axial entry dovetails are joined to the second disc. A unitary annular spacer is disposed axially between the first and second dovetails for preventing the first and second blades from sliding axially toward the spacer. The spacer has an inner diameter greater than an outer diameter of the first rotor disc for allowing the spacer to be assembled over the first rotor disc during assembly.

Abstract: A mounting ring is provided which adapts an oversized exhaust flow guide to the existing inner cylinder of a steam turbine. The mounting ring is comprised of six arcuate segments which allow the mounting ring to be radially installed into a groove, machined in the outer diameter of the inner cylinder, despite the presence of lugs which preclude axial installation. The mounting ring and exhaust flow guide form a moisture removal gap just upstream of the tips of the last row rotating blades. Arcuate filler segments are installed in the vicinity of the horizontal joint to create a uniform moisture removal gap around the circumference of the steam flow path. The mounting ring creates an access space above the horizontal joint flanges in the cover half of the innert cylinder for installation of the horizontal joint bolts.

Abstract: An apparatus and method are provided for aligning and supporting vane segments in the turbine section of a gas turbine. According to the invention, the vane segments are supported and aligned to an inner cylinder. The apparatus features a plate, having threaded holes, which is fixed to the inner cylinder. A threaded plug, having an eccentric hole, is threaded into each threaded hole in the plate. A pin, having flats and a chamfer formed at one end, is inserted into the eccentric hole in the plug. At assembly, the plug is rotated in the threaded hole and the pin is rotated in the eccentric hole until the pin enters a slot in the inner shroud of the vane segment. The pin supports and aligns the vane segment by bearing against a side of the slot. The plug is locked in place by a nut threaded onto the plug.

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: Improved methods and apparatus for retrofitting longer last row rotational blade assemblies in steam turbines are disclosed. The apparatus of the present invention permits the exhaust flow guide to be mounted directly to modified last row stationary turbine blades. In a preferred embodiment, the outer blade ring of the last row of stationary blades in a steam turbine is modified by machining two grooves which permit a modified blade assembly outer ring and integral blade ring extension to be mounted in the turbine. The extension section is configured to accept connecting means, such as bolts, which permit the direct attachment of an exhaust flow guide to the modified outer blade ring at each end of the turbine. The present invention simplifies the attachment of such flow guides and can improve the harmonic characteristics of the turbine by lowering the natural frequency of the assembly and include the mass of the flow guide in the mass of the stationary blade assemblies.

Abstract: The stator is made of ceramic matrix composite material and comprises: a bladed hub carrying blades with a radially projecting finger at the end of each blade; and two toothed rings having teeth facing one another with the rings being urged towards each other in order to hold each tenon of a blade both axially and circumferentially between a flank of one of the teeth of one of the rings and a flank of one of the teeth of the other ring. The rings are urged towards each other by resilient coupler which enables them to move apart from each other with the two rings also rotating relative to each other under the effect of the blade tenons expanding, with the stator being fixed to the casing of the turbojet by mechanical connections between the casing and one of the rings.

Abstract: A shroud for supporting the vanes in the hot sections of a gas turbine engine is comprised of composite segments retained in a metal ring. The metal ring has a positive coefficient of expansion, while the segments have a zero (or much smaller) coefficient. When the ring is heated and grows, it carries the segments with it, so that there is an apparent corresponding growth of the segments.

Abstract: In a turbomachine, such as a turboshaft aero-engine, having a compressor casing composed of upstream and downstream casing rings, and a variably settable stage of stator blades which is mounted in one of said casing rings near the junction therebetween so that, in normal operation, the blades have their leading (or trailing) edges projecting into the other casing ring, the setting of the blades being adjusted by a control ring surrounding the casing, there is provided a locking system for temporarily locking the blades in an angular setting in which the leading (or trailing) edges are retracted clear of said other casing when the casing is to be dismantled or assembled.

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: An improved blade mounting arrangement for a gas turbine engine with a turbine and an annular flowpath therethrough is disclosed. The improvement comprises a one-piece outer casing and a one-piece inner casing bounding the flowpath. The outer casing has a plurality of circumferential recesses disposed therein with each of the recesses having first and second axially opposite circumferential slots. A plurality of first turbine blades, each with axially facing tangs on a mounting platform, mate with the slots in the outer casing recess. The inner casing has a plurality of recesses disposed therein, each of the recesses including a forward circumferential slot and concentric aft radially outer and radially inner circumferential slots. A plurality of second turbine blades, each with forward and aft axially facing tangs on a mounting platform, mate with respective ones of forward slot and radially outer slot in the inner casing recess.

Abstract: An annular fairing forming a bolt guard associated with the heads of screws of an attachment carries, inside thereof and in line with each screw, first cylindrical sockets each comprising two slightly inwardly bent tongues which cooperate with apertures provided in a respective second socket disposed within the first socket and comprising an inturned downstream edge which is impressed over and thereby engaged with peripheral teeth on the head of the respective screw.

Abstract: A steam turbine has an outer blade ring supporting a row of stationary blades and an adjacent downstream row of long rotatable blades. The outer blade ring has a generally conical flow-guiding surface for outwardly guiding the steam as it flows through the row of stationary blades. The outer blade ring is supported by a radially juxtaposed carrier ring having a flow-guiding surface axially adjacent to and extending outwardly from the flow-guiding surface of the outer blade ring. A spacer ring is axially adjacent to the carrier ring and has a flow-guiding surface adjacent to and extending outwardly from the flow-guiding surface of the carrier ring. An exhaust flowguide is axially adjacent the spacer ring and radially adjacent the row of rotatable blades for guiding the steam from the rotatable blades.

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: An annular fairing forming a bolt guard associated with the heads of screws of an attachment carries, inside thereof and in line with each screw, first cylindrical sockets each of which comprises notch-shaped cut-outs at its inner end which cooperate with a pair of first lugs formed at the end of a respective second socket disposed within the first socket and further comprising a pair of inwardly curved second lugs cooperating with the head of the screw in such a way as to prervent rotation of the screw.

Abstract: A nozzle assembly for a turbine engine comprises an annular ceramic-matrix composite hub having integral radially outwardly extending vanes, and a pair of annular ceramic-matrix composite shrouds which interlockingly engage and secure the radially outermost ends of the vanes, whereby the hub is peripherally supported. The quasi-isotropic laminate structure of both hub and shroud materials generates like physical properties radially and circumferentially in the hub, and axially and circumferentially in the shrouds. Such quasi-isotropism in turn provides cooperative thermal expansion of the hub and shrouds during engine operation, whereby the radial, axial, and circumferential abutting surfaces of the ends of the vanes increasingly interlockingly engage with the correspondingly opposed surfaces of the shrouds to effect increased structural integrity of the nozzle assembly.

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: In an axial guide blade assembly for a compressor stator, the root end of each guide blade is attached in a ring gap of a preferably axially split, i.e. split along a normal plane, compressor housing made of a fiber reinforced synthetic material. The root of each blade is received in the ring gap or circumferential groove formed between two adjacent housing sections joined together along the axial separating plane. The guide blades hang on fiber rings with which the blade roots are clamped into the circumferential groove.

Abstract: A fairing for mounting onto a gas turbine frame to isolate the frame from the hot gases passing the flowpath. The fairing includes mating forward and aft annular sections with each section having an outer wall and an inner wall defining the flowpath therebetween. A plurality of circumferentially-spaced hollow fairing struts radially extends between the inner and outer walls. The two sections are manufactured such that there are no misalignments or steps between the lineup of the two sections. The sections are placed over the frame struts and are coupled together.

Abstract: A compressor for a gas turbine engine has a split case and a split stator vane inner shroud. Selected rotatable stator vanes longitudinally restrain the shroud and seal carried thereon to retain the desired roundness.

Abstract: An initially flat sheet of a fan cylinder assembly is formed to an exact cylindrical configuration in such a manner that less than 20% of the material comprising the sheet in a direction along the thickness of the same is exposed to stress above the yield strength of the material. The sheet is provided with tabs bent to a perpendicular orientation relative to remaining regions of the sheet, and holes are punched in certain of the tabs at precise, predefined locations and which are related to precise, predefined locations of apertures spaced around the periphery of an exact circular opening in an upright support panel of the tower housing. The sheet is formed to a true cylinder by causing the major region of the sheet to bear against the periphery of the circular opening of the support panel so that the flat panel functions as a guide both during forming of the cylinder and also thereafter to retain the sheet in its proper cylindrical configuration.

Abstract: A stator assembly for a gas turbine engine is provided having novel means for securing it to the casing of the engine's compressor section. The stator assembly includes inner and outer shrouds secured, as by brazing, to a plurality of vanes and also includes a plurality of vane assemblies for clamping the shrouds and associated vanes to the casing of the compressor section. The vane of each vane assembly projects through but is not secured to the shrouds, the inner end of each vane of the vane assemblies having an integral plate engaging the interior of the inner shroud and means at its outer end for fastening the vane assembly to the casing by drawing the plate firmly into compression against the interior of the inner shroud. Since the vane assemblies are not secured to the shrouds, expansion of the casing during engine operation can be accommodated without imposing any destructive stresses on the shrouds, thereby protecting the structural integrity of the engine.

Abstract: A blade ring for a steam turbine having an outer generally cylindrical casing, an inner generally cylindrical casing disposed within the outer casing and supported by the outer casing and a blade ring to which are affixed a plurality of circular arrays of stationary blades forming stationary blade rows, the blade ring being disposed partially within the inner casing and partially within the outer casing and having a support arm which extends outerwardly to and is supported by the outer casing.

Abstract: Annular, circumferentially segmented components of a gas turbine engine are secured to a support structure by C-shaped couplings which prevent movement of the components in a radial and circumferential direction. The coupling has spaced apart legs which trap the component and support structure therebetween, and a key between the legs which engages a keyway formed by cooperating slots in the component and support structure.

Abstract: The adjacent spacers that make up a compressor case for a multistage axial flow compressor carry a row of vanes at one end that are held in position during assembly of the compressor by a ring that is bolted to a flange at that end of the spacer and the spacer extends over the row of vanes of an adjacent spacer and is secured by a row of bolts to the adjacent spacer. This ring is T-shaped to pilot the ring on the spacer to which it is secured and also to pilot the opposite end flange of the adjacent spacer during assembly.

Abstract: A ceramic nozzle assembly for a gas turbine engine is provided. The assembly includes ceramic inner and outer shroud rings dimensioned to be concentrically disposed relative to one another. Recesses are provided in the outer circumferential surface of the inner shroud ring and apertures extend through the outer shroud ring in register with the recesses. Vanes extend through the apertures in the outer shroud ring and are engaged by the recesses in the inner shroud ring. A ceramic outer support ring slides over the outer shroud ring to securely retain the vanes. Slots or recesses are provided in both the inner and outer shroud ring to prevent rotation of the nozzle in the engine.

Abstract: A system for fixing nozzles to a power turbine stator casing, in which each nozzle sector is locked to the respective shroud by means of a key which has its two diverging vertical flanges inserted into a radial dovetail guide in the front surface of the shroud, where it is held in position by an elastic element or spring acting between the key and the inner wall of the guide, its lower vertical nose or beak acting as a shoulder abutment for a radial fork of the nozzle sector, which is mounted over, and kept centered by, the two projecting sidepieces of said key, which also has a projection at its upper end. Each shroud is locked to the stator casing by an insertion-fit between the uncinated edges of a cavity in the outer peripheral surface of the shroud and the corresponding uncinated edges of a circumferential cavity in the stator casing, the insertion being secured by a leaf spring acting between the mutually facing, uncinated edge-free walls of the two said cavities.

Abstract: A device for axially and circumferentially locking two stationary components of a turbomachine, each of which is at least part of a ring and wherein the components are concentrically engaged along opposed surfaces. The device comprises a locking member including a disc portion and an axially projecting angular segment on the disc portion forming a step thereon. The components have axially aligned intercommunicating hollows, the hollow of a first of the components having a laterally open recess. The locking member is engaged in the hollow of the stationary components in a locking position by inserting the disc portion into the hollow of the first component through the recess thereof, then axially displacing the locking member to engage the disc portion thereof into the hollow of the second component and thereafter angularly rotating the locking member to engage its angular segment into the hollow of the first component through its recess.

Abstract: A device for attaching the stator vanes of an axial compressor to an external housing is disclosed. The attachment utilizes an inner casing, having the vanes mounted on it, and an outer casing surrounding the inner casing in such a manner that differential thermal expansion between the various elements is minimized. This allows more accurate control of the clearances between the rotor and the stator.

Abstract: A turbocharger compressor housing unit includes an outer housing and a wall insert for engagement with the outer housing. The outer housing has a compressor inlet port, a wall transverse to the inlet port and extending outwardly therefrom and a circumferential chamber attached to the transverse wall spaced from the inlet port. The chamber has an opening substantially in the plane of the transverse wall. The wall insert is formed with a tubular throat having a disc attached at one end of the tubular throat transverse thereto. The disc has an aperture corresponding to an opening defined through the throat. Rivet protrusions are integrally formed and extend from the disc and correspond to apertures in the transverse wall of the compressor housing. The rivet protrusions engage the apertures in the transverse wall to join the insert to the outer housing with the disc in engagement with the transverse wall. The disc partially encloses the opening in the plane of the wall of the circumferential chamber.

Abstract: A one-piece, investment cast stator structure is provided including inner and outer shrouds 14 and 12 with a hollow airfoil-shaped vane therebetween and with areas 34, 36, 42 and 44 in the vicinity of the intersections of the shrouds with the airfoil vane walls being of reduced thickness relative to the remainder of the shrouds to provide improved properties of the material in these areas to better respond to thermal stresses imposed on the structure.

Abstract: A structure useable as a spacer. In a preferred embodiment, the spacer is eally suited (as one of a plurality of identical spacers) for use as a spacer between every two adjacent stator vanes of a stator vane ring of a multiple-stage fan of a gas turbofan engine. The spacer is in the form of a rectangular solid and comprises a metal face skin member having a curved aerodynamically configurated outer surface with a centrally-located longitudinally-positioned concavity which functions as a rib, and a backing pad member that is made of a molded polyethelene material with integral peripheral edge lip seals that are coated with a polyurethane material, and that is joined by its outer surface to the inner surface of the face skin member, with the backing pad member having an embedded rib skin stiffener positioned under, along, and in contact with the concavity in the face skin member.