Abstract: A turbine static structure having reduced leakage air is disclosed. A static structure turbine support ring having few segments is disclosed in which the segments have improved thermal expansion capability with reduced air leakage. A plurality of radially extending slots are placed in the segments to reduce stiffness. In order to minimize air leakage through the support ring, generally circumferential slots are placed in the ring and connect with the generally radially extending slots. Positioned in each of the generally radially extending slots and generally circumferential slots, and in contact with each other, are two sheet metal plates. The plates are staked to the support ring structure so as to provide a seal member, yet compensate for thermal growth.

Abstract: An example exit guide vane for a gas turbine engine is mounted adjacent to a diffuser case defining an air flow path. A thrust balance seal is attached to the diffuser and the exit guide vane is mounted adjacent the diffuser case for guiding air flow into the air flow path. The exit guide vane is mounted adjacent to the diffuser without interfering with the air flow path or restricting thermal expansion.

Abstract: A method is provided for attaching a shim to at least one of a base of a stator vane unit and a ring segment of a ring segment assembly in a gas turbine compressor. The method includes providing a shim shaped to conform to an engaging face of the base of the stator vane unit or the segment ring of the segment ring assembly, with a predetermined thickness dimension; boring at least one hole, normal to the face of the shim and extending fully through the thickness dimension of the shim; positioning the shim on the engaging face of the at least one of the base of the stator vane unit and the segment ring of the segment ring assembly; and welding the shim to the engaging face of the at least one of the base of the stator vane unit and the ring segment of the stator ring assembly.

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: An assembly for mounting a ceramic turbine vane ring onto a turbine support casing comprises a first metal clamping ring and a second metal clamping ring. The first metal clamping ring is configured to engage with a first side of a tab member of the ceramic turbine vane ring. The second metal clamping ring is configured to engage with a second side of the tab member such that the tab member is disposed between the first and second metal clamping rings.

Abstract: A support for the first row turbine vanes (12) in a gas turbine engine, the support including a support framework (18). The support framework (18) includes an outer vane carrier (34), and an inner vane carrier (36) connected to the outer vane carrier (34) by a plurality of struts (44, 46). The outer vane carrier (34) is mounted to an inner casing (16) of the engine and the struts (44, 46) support the inner vane carrier (36) in cantilevered relation to the outer vane carrier (34). An aft outer flange (94) of each first row vane (12) is supported on the outer vane carrier (34) and a forward inner flange (114) of the vane (12) is support on the inner vane carrier (36).

Abstract: A method for assembling a turbine is provided, wherein the method includes positioning an annular nozzle carrier radially inwardly from a casing such that a cavity is defined between the nozzle carrier and the casing. The method also includes extending a flange from at least one of a leading edge of the annular casing and a leading edge of the nozzle carrier, and extending a seal ring between the nozzle carrier and the casing such that the seal ring seals the cavity, wherein the seal ring is positioned between the flange and at least one of the nozzle carrier and the casing.

Abstract: A gas turbine with several shroud segments (1) which enclose rotor blades (3) of a turbine wheel (5) as a seal, with the shroud segments (1) having at least a front and a rear attachment at the radially outward area of stator vane segments (7, 12), and with each of the stator vane segments (7, 12) being located at their radially inner area on a control ring (9, 10), wherein the stator vane segments (7, 12) are located on the control ring (9, 10) in a radially adjustable manner.

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: Device for attaching ring sectors (20) to a turbine casing (16) in a turbomachine, comprising, at the upstream ends of the ring sectors (20), circumferential coupling means (70, 72) engaged on a casing rail (50) and clamped axially onto the casing rail by a C-section annular locking member (80) engaged axially on the casing rail and on the ring sector coupling means.

Abstract: A simplified vane mounting arrangement by which a vane ring can be pre-assembled to an inner support ring before being installed in an outer casing.

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 method is provided for making a repaired turbine engine stationary vane assembly including at least one airfoil bonded between spaced apart first and second platforms. The method comprises providing a first vane assembly member including at least a portion of the first platform, the airfoil, and a first segment of the second platform bonded with the airfoil. Also provided is a second vane assembly member including a second segment of the second platform with a recess of a shape and size sufficient to receive the first segment of the second platform. The first segment is placed in the recess after which the first and second segments are bonded, for example by brazing or welding. Provided is a more structurally sound repaired turbine engine stationary vane assembly including the first and second vane assembly members bonded together.

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: An arrangement 22 for mounting a non-rotating component 28 of a gas turbine engine 10, defining a portion of a gas path of the gas turbine engine 10 comprising: a non-rotating component 28 having an opening 23 to a receptacle 25; and a fastener 30 for retaining the non-rotating component 28, comprising a neck portion 34 and a head portion 32, wherein the neck portion 34 of the fastener 30 extends through the opening 23 in the non-rotating component 28 and the head portion 32 is retained, at least partially, within the receptacle 25.

Abstract: A turbine nozzle support structure supports a ceramic turbine nozzle provided with a flange and disposed at the inlet of a turbine on a nozzle support. Force-multiplying mechanism presses the flange of the turbine nozzle against a nozzle support to support the turbine nozzle on the nozzle support. The force-multiplying mechanisms includes a pressing member having a spring holding part, a fulcrum part and a pressing part, a spring for applying resilient force to the spring holding part, and a fulcrum supporting member having a bearing part for supporting the fulcrum part.

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: 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: The invention relates to a rotation-locking device of a sector of rectifier blades (5) mounted in a sector of the turbojet housing. A sector of blades comprises a support base (3). A housing sector comprises two recesses perpendicular to the axis of the housing, each receiving an edge (34-1, 34-2) of the support base. At one and the same axial end of the housing sector, each recess opens out into a seat (30-1, 30-2) defining an axial face (32-1). The device comprises an axial stop (26) adapting itself on each side in the seats (30-1; 30-1) of the two recesses, and once the complementary sector of the housing is installed and during operation of the turbojet, bearing on the axial faces (32-1) under the thrust of the complementary sector of rectifier blades in order to provide rotation locking.

Abstract: A machine stator and assembly and disassembly methods. The elements of a casing portion are formed of consecutive shells in line with grooves configured to house roots of guide vane stages that are fixed in place by springs and pins for stopping rotation. The elements are arranged in a complete circle, and the assembly is made by axially separating the elements to insert the guide vane stages between the elements by a radial movement.

Abstract: A preloaded spring assembly is provided in a recess in each shroud in axial opposition to an aft facing sealing surface of a turbine nozzle retaining ring. Each spring assembly includes a spring, preferably a bellows type spring, with a plate mounted on one side and a sealing surface on the side of the plate remote from the spring. The sealing surface may be an abradable coating or a honeycomb seal. The seal assembly is maintained preloaded by a wrap which upon reaching turbine operating temperature disintegrates, enabling the spring to load the sealing surface against the retaining ring surface to prevent or minimize air leakage from outside the nozzle retainer ring into the hot gas path.

Abstract: The invention provides a device for holding strip sealing gaskets on a turbomachine nozzle, the nozzle being constituted by a plurality of sectors having guide vanes which extend between inner and outer platforms elements, at least one of said platform elements having a sealing strip (30) disposed radially in a space between said platform element and an adjacent structural element in order to provide fluid tightness between said elements, the corresponding strips of two adjacent sectors touching, and their joint being covered by a joint cover (31) disposed between said strips, and by a holding member for holding said strips in the sealing position.

Abstract: A turbine disk cooling device fed with cooling air from an orifice through an annular support platform for a fixed vane of a low-pressure turbine is disposed between an upstream flange and a downstream flange of the support platform. The device includes upstream and downstream annular plates longitudinally defining an annular cavity, a sealing device extending longitudinally between the upstream and downstream plates so as to close the cooling air cavity, an element to hold the upstream and downstream plates against upstream and downstream flanges of the support platform, and a plurality of holes for ejecting cooling air towards the turbine disks.

Abstract: A method of tuning a compressor stator blade having a base portion and an airfoil portion to achieve a desired natural frequency, includes a) identifying the natural frequency of the compressor stator blade; b) determining a different target natural frequency for the compressor stator blade; and c) removing material from the base portion of the compressor stator blade in an amount and in a configuration that achieves the target natural frequency. A frequency-tuned compressor stator blade includes an airfoil portion and a base portion, the base portion having a substantially solid rectangular shape; and a groove cut across a width dimension of the base portion, the groove having dimensions selected to obtain a predetermined natural frequency for the airfoil portion.

Abstract: A device for stopping rotation of a fixed blade bearing sector in a gas turbine casing. Sectors of synchronizing ring blades are maintained against tangential rotational movements by sliding into grooves of a casing by pins passing through perforations in an extension of the two parts. The pins are prevented from accidental removal either by a flexible lock ring or by a locking tab maintained between the two parts when they have been completely assembled.

Abstract: Aspects of the invention relate to a system for reducing relative movement between the outer shroud of a compressor diaphragm and the compressor cylinder of a turbine engine, thereby minimizing the wearing of these parts. Embodiments of the invention include a system for applying an axial preload on the outer shroud of a compressor diaphragm, preferably in the same direction as the gas load in the compressor. The system can be installed at or near the horizontal joint such that the axial preload can be applied substantially at the horizontal joint, which is the location of the largest relative movement. In one embodiment, the axial preload system can include a two-piece wedge block and pin. As the pin is driven between the two wedge blocks, the force applied to the pin can be converted to an axial load by the spreading apart of the two wedge block sections.

Abstract: Components must often be released again from their holder for maintenance. Since the fastenings are often very complicated, it takes a considerable amount of time to release them. A fastening system is one where components can be fastened in a rotationally locked manner to a holder, and released again in a simple, reliable and quick manner.

Abstract: A jacket ring for the low-pressure-turbine region of a gas turbine, having a plurality of lined-up segments which are arranged between a moving blade ring with a shroud band and the casing of the gas turbine, which carry a run-in lining and which hold guide blades in a positive-locking manner, wherein each segment comprises a hot-gas-side seal carrier and a casing-side securing element, the seal carrier and the securing element are at the greatest possible distance from one another and only have common contact points which are as small as possible, and the securing element is axially supported directly on the casing of the gas turbine.

Abstract: A drop-in nozzle block (40) formed in two 180° segments (52) that can be simply lowered into position within the nozzle chamber casing of a steam turbine (42). An entire 180° segment can be lowered into position because an inner arcuate portion (58) of the nozzle block fits over and captures mating portions of the casing rather than having the casing capture the nozzle block as in the prior art. Elimination of a hook portion of the casing eliminates the necessity for the prior art procedure of rotating 90° segments into position through an arcuate-shaped slot. The drop-in installation allows closer tolerances to be maintained between the nozzle block and the casing, thereby eliminating the need for the expansion pins used in the prior art. The use of two 180° segments rather than the prior art 90° segments also eliminates the need for a dogleg joint between segments for turbines having eight steam inlet segments.

Abstract: A steam turbine includes a stator supporting a plurality of turbine nozzles. The stator has shaped grooves for receiving a complementary-shaped nozzle hook formed on an end of each of the turbine nozzles. A rope seal is disposed in each interface between the nozzle hooks and the shaped grooves, respectively. The rope seal serves to seal a leakage path that may exist over the nozzle hooks between the nozzles and respective stator grooves.

Abstract: A passive clearance control system for a gas turbine engine component. The system provides a blade shroud that is isolated from the component case and can move radially to maintain blade clearance. A plurality of vane sectors define a stator ring including a blade shroud. The stator ring and the control ring are coupled together and mounted within the component by a plurality of radial extending mounting members.

Abstract: A turbine nozzle segment includes at least one hollow airfoil extending radially between radially outer and inner band segments, a clockwise open hook on a clockwise end at an aft end of the outer band segment, and counter-clockwise open hook on a counter-clockwise end at the aft end of the outer band segments. An exemplary embodiment of the turbine nozzle segment includes a load stop extending radially outwardly from the outer band segment. At least one aftwardly facing load face is at the aft end of the nozzle segment at the outer band segment. The clockwise open hook is C-shaped and the counter-clockwise open hook is a shiplap hook. Another embodiment of the turbine nozzle segment has only one hollow airfoil with an airfoil wall surrounding a bifurcated cavity divided into forward and aft cavities by a bifurcating rib extending between pressure and suction sides of the airfoil wall.

Abstract: The invention relates to an axial compressor stator for a gas turbine, the stator having a rigid, external, annular frame and axially juxtaposed rings configured within the frame and bearing annuli of stationary vanes. The rings are defined by arcuate segments affixed to the frame. The inside walls of the arcuate segments externally define the aerodynamic conduit for the compressed gaseous fluid. The arcuate segments are brazed segments that include a honeycomb component sandwiched between an inner sheetmetal bounding the aerodynamic conduit and an outer sheetmetal. The outer sheetmetal solely connects the arcuate segments to the frame.

Abstract: A resilient ring for sealing between an inner housing surface of revolution and a coaxial outer housing surface of revolution, one of the housing surfaces being a sloped surface with a sloped profile intersecting an axially extending plane and the other housing surface being an axial abutment surface in a substantially radially extending plane. The ring has a circumferential sealing surface for sealing engagement of the ring with the sloped housing surface, and a planar abutment surface for sealing engagement of the ring with the axial abutment housing surface.

Abstract: Aspects of the invention relate to a method for clocking a row of stationary airfoils relative to an adjacent row of airfoils, and a turbine blade ring configured for use in such a method. The method according to aspects of the invention is advantageous because it can avoid extensive disassembly of the turbine in order to clock the blade ring. The method includes engaging the outer peripheral surface of a blade ring with a plurality of roller pins such that the weight of the blade ring is entirely supported by the roller pins. A tangential force is applied to the blade ring such that the blade ring rotates on the roller pins, thereby adjusting the position of the stationary airfoils affixed to the blade ring. Additional rotational adjustments can be made to the blade ring until the blade ring is clocked to the desired position.

Abstract: A fixed guide vane assembly includes a circular casing composed of at least two parts (11) and supporting sectors (5), each composed of an inner segment (7) and an outer segment (6) connected by vanes (8). The parts of the casing and the sectors of the guide vane assembly are held together by a system forming a slide and a slider. An anti-rotation mechanism (30) is provided to prevent the sectors from rotating with respect to the casing.

Abstract: A gas turbine engine has an intermediate case. At least one compressor exit stator shroud is welded to the intermediate case.

Abstract: A stator vane span attachment for a gas turbine having a casing 1 in which several stator vane spans 2 are located, wherein means 3 are provided for restraining the stator vane spans 2 against the casing 1.

Abstract: A resilient ring for sealing between an inner housing surface of revolution and a coaxial outer housing surface of revolution, one of the housing surfaces being a sloped surface with a sloped profile intersecting an axially extending plane and the other housing surface being an axial abutment surface in a substantially radially extending plane. The ring has a circumferential sealing surface for sealing engagement of the ring with the sloped housing surface, and a planar abutment surface for sealing engagement of the ring with the axial abutment housing surface.

Abstract: A shroud for the support of vane roots 1 of variable stator vanes 2 in the high-pressure compressor of a gas turbine includes a forward shroud segment 3 and a rearward shroud segment 4, each with an axially open annulus 5 forming an essentially U-shaped cross-section and with a plurality of axial assembly holes 6, wherein an annular cover 7 is arranged in the area of the opening of the annulus 5 which is provided with assembly openings 8 and tubular supports 9 are provided in the area between the assembly openings 8 of the cover 7 and the associated assembly hole 5 of the shroud segments 3, 4.

Abstract: A method for assembling a turbine, wherein the method includes coupling at least one nozzle assembly including an outer band, an inner band, a nozzle, and a dovetail, to a stator that includes a plurality of dovetail slots and channels defined therein, slidably coupling the at least one nozzle assembly into a respective dovetail slot, and fixedly securing the at least one nozzle assembly to the stator with a load pin that extends between the nozzle assembly and the dovetail slot.

Abstract: A method enables a variable vane assembly for a gas turbine engine including a casing to be assembled. The variable vane assembly includes a seal assembly and at least one variable vane that includes a platform and a trunnion, wherein the platform extends outwardly from the trunnion. The method comprises coupling a seal assembly journal bushing to the variable vane such that the journal bushing is against the trunnion and between the trunnion and the engine casing, and wherein the journal bushing has a substantially constant diameter extending between a first and a second end of the journal bushing, and positioning a substantially flat first washer on the variable vane ledge to prevent contact between the variable vane assembly and the engine casing.

Abstract: Upper and lower diaphragms of a steam turbine have mating flanges forming a horizontal midline joint interface. Each flange has a groove which registers with a corresponding groove in the opposite flange. A composite woven tubular seal is provided in the mating grooves. The seal comprises an inner woven metal core surrounded by an annular silica fiber layer, in turn surrounded by a metal foil with an outer protective covering of a braided stainless steel. Upon joining the diaphragms to one another, the compliant seal generally conforms to a maximum to the shape of the grooves, maintaining a seal between the diaphragms along the horizontal midline joint.

Abstract: An axial flow compressor and a method for mounting the stator blades in the compressor. The compressor is comprised of a stator casing having a rotor axially positioned therein. The casing has internal circumferential grooves into which the stator blades are equally spaced therein. Resilient spacers, e.g. leaf spring, are positioned within any spaces which might exist in the groove after all of the blades have been properly spaced around the groove.

Abstract: Upper and lower diaphragms of a steam turbine have mating flanges forming a horizontal midline joint interface. Each flange has a groove which registers with a corresponding groove in the opposite flange. A composite woven tubular seal is provided in the mating grooves. The seal comprises an inner woven metal core surrounded by an annular silica fiber layer, in turn surrounded by a metal foil with an outer protective covering of a braided stainless steel. Upon joining the diaphragms to one another, the compliant seal generally conforms to a maximum to the shape of the grooves, maintaining a seal between the diaphragms along the horizontal midline joint.

Abstract: Nozzles for a turbine have dovetail-shaped bases for reception in corresponding dovetail-shaped grooves in the carrier halves of a turbine. The nozzles at each of the horizontal joint faces of each carrier half have notches formed along their bases including an abutment face. Key slots are formed in the horizontal joint faces and receive keys bearing against the abutment faces. The keys are peened or screwed into the carrier half at the horizontal joint faces. Radial loading pins engage the end nozzle bases to bias the end nozzles radially inwardly without interfering with the keys retaining the nozzles in the grooves.

Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a flexible supplemental seal is disposed between the support ring and inner band of the nozzle segment radially inwardly of the chordal hinge seal. To minimize or prevent leakage flow across the chordal hinge seal, the flexible seal extends between the inner rail and the sealing surface of the support ring radially inwardly of the chordal hinge seal. A first margin of the flexible seal engages in a linear groove carried by the inner rail. The opposite margin extends arcuately in sealing engagement with the nozzle support ring.

Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner rail of each nozzle segment radially inwardly of the chordal hinge seal. To minimize or prevent leakage flow across the chordal hinge seal, the seal is formed of flexible sheet metal which extends between the inner rail and a seat projecting from the annular sealing surface of the support ring radially inwardly of the chordal hinge seal. A first margin of the flexible seal engages in an arcuate groove carried by the inner rail. The opposite margin extends arcuately in sealing engagement along the seat carried by the nozzle support ring.

Abstract: A turbine nozzle includes a plurality of vanes joined at opposite ends to outer and inner bands. The inner band has a forward hook which is segmented to reduce thermal mismatch. And, in additional embodiments the vane includes an impingement baffle having preferential cooling.