Abstract: The invention concerns an apparatus for supporting blades of axial-flow machines, in particular turbojet propulsion units, which is distinguished by at least one pair of mutually oppositely disposed support rings (12, 14) which are supported adjustably relative to each other for assembly between guide or rotor blades of adjacent compressor or turbine stages.

Abstract: A seal is provided between a pair of members by a flexible seal element fixed to one member and having a turned edge. The seal element overlies a contact surface of the other member to effect the seal, the seal element spanning a gap between the members and being pressed into the contact surface by a high pressure region on the same side of the gap as the sealing element. In other forms, a second sealing element is employed in conjunction with a spline seal forming a tortuous sealing path between the members.

Abstract: A seal is provided between a pair of members by a flexible seal element fixed to one member and having a turned edge. The seal element overlies a contact surface of the other member to effect the seal, the seal element spanning a gap between the members and being pressed into the contact surface by a high pressure region on the same side of the gap as the sealing element. In other forms, a second sealing element is employed in conjunction with a spline seal forming a tortuous sealing path between the members.

Abstract: An axial seal assembly is provided at the interface between adjacent wheels and spacers of a gas turbine rotor and disposed about tubes passing through openings in the rotor adjacent the rotor rim and carrying a thermal medium. Each seal assembly includes a support bushing for supporting a land of the thermal medium carrying tube, an axially registering seat bushing disposed in the opposed opening and a frustoconical seal between the seal bushing and seat. The seal bushing includes a radial flange having an annular recess for retaining the outer diameter edge of the seal, while the seat bushing has an axially facing annular surface forming a seat for engagement by the inner diameter edge of the seal.

Abstract: The invention relates to a compensator modular unit for a multistage pump housing, ensuring as compensation device during hot or cold temperature shocks compensation of changes in length caused by said shocks.

Abstract: A gas turbine engine arcuate segment has an arcuate band segment, at least one tab and an arcuate rail segment spaced axially apart from the tab and located along an axial end of the band segment. The tab and the arcuate rail segment extend radially away from the band segment and a space is located between the tab and the rail segment. A tab aperture extends entirely through the tab. The rail segment has a rail aperture entirely therethrough. A leaf seal and a spring are disposed within the space to bias the leaf seal against the aft rail. In an exemplary embodiment, a spring aperture extends entirely through the spring, a seal aperture extends entirely through the leaf seal, and a headless pin is disposed in the apertures such that the leaf seal and the spring are radially restrained by the pin.

Abstract: A seal between two static turbine parts is provided with a carrier piece comprising a flat metal piece with a middle piece and end pieces each of which is arranged in a groove in the static turbine parts. A second part comprising a flat metal piece and having a middle piece and end pieces which are also arranged in grooves is attached to the middle piece of the carrier. The end pieces are constructed resiliently, ensuring a sealing contact between the end pieces and the inside surfaces of the grooves even in the case of a relative shift of the grooves. The seal does not depend on the level of a pressure differential.

Abstract: Cooling is facilitated in stationary flowpath components, such as turbine nozzle segments and shrouds, by providing circumferential edges defining a non-linear curvature that matches the curvature of the flow line defined by the gas flow past the stationary flowpath component. A flexible seal member is provided to accommodate the non-linear edges.

Abstract: A leaf seal assembly is secured to the trailing edge of a shroud segment for sealing between the shroud segment and the leading edge side wall of a nozzle outer band. The leaf seal includes a circumferentially elongated seal plate biased by a pair of spring clips disposed in a groove along the trailing edge of the shroud segment to maintain the seal plate in engagement with the flange on the leading edge side wall of the nozzle outer band. The leaf seal plate and spring clips receive pins tack-welded to the shroud segment to secure the leaf seal assembly in place.

Abstract: A tip clearance control device for a gas turbine engine having a shroud surrounding a stage of rotor blades. The tip clearance control device comprises a one-piece split ring having opposed overlapping end portions. The split ring is directly supported onto the inner surface of the shroud and is adapted to automatically adjust for thermal growth of the shroud during engine operation.

Abstract: A support and locking device for nozzles of a high-pressure stage in gas turbines comprises a plurality of groups of stator vanes, which are associated with a plurality of outer sealing plates, for connection of the groups to the outer liner of the combustion chamber, and are associated with a plurality of inner sealing plates, for connection of the groups to the inner liner of the combustion chamber. Each of the groups of stator vanes is locked by an inner ring, and the ring has a first series of outer holes to reinforce this locking, and a second series, of inner, through holes, which are provided in an inner extension of the ring and are used to secure the ring itself to the structure of the gas turbine.

Abstract: A turbine inner shroud and a turbine assembly. The turbine assembly includes a turbine stator having a longitudinal axis and having an outer shroud block with opposing and longitudinally outward facing first and second sides having open slots. A ceramic inner shroud has longitudinally inward facing hook portions which can longitudinally and radially surround a portion of the sides of the outer shroud block. In one attachment, the hook portions are engageable with, and are positioned within, the open slots.

Abstract: Cooling is facilitated in stationary flowpath components, such as turbine nozzle segments and shrouds, by providing circumferential edges defining a non-linear curvature that matches the curvature of the flow line defined by the gas flow past the stationary flowpath component. A flexible seal member is provided to accommodate the non-linear edges.

Abstract: The present invention relates to a flexible inlet tube for a high and intermediate pressure steam turbine. A reheat steam inlet tube is constructed integrally with a casing. The inlet tube has a double tube portion to form an annular groove. The lower end of the double tube portion has an expanded diameter, and a vertical sliding motion can be accomplished between the expanded diameter portion and a flange fixed to a thermal shield, so that thermal elongation is absorbed. Low-temperature steam flows into the annular groove from an in-casing space through a hole, circulates in the annular groove, and flows out to a steam passage in an intermediate pressure turbine section, by which the interior of the annular groove is cooled, so that a temperature rise of the casing can be prevented.

Abstract: A sealing device for a gas turbine stator blade, in which an outer shroud (32) is mounted by heat insulating rings (32a,32b) on a blade ring (50). The blade ring (50) has a first air hole (1), which communicates with a space (53), and a second air hole (51), which communicates with a seal tube (2). The seal tube (2) is inserted into the second air hole (51), and a spring (6) is arranged between a projection (4) of the tube (2) and a retaining portion (5) of the air hole (51) to removably secure the seal tube (2). Cooling air (54) flows through the first air hole (1) to cool the shrouds and the inside of a stator blade (31) until it is released from the trailing edge of the blade. The cooling air also flows into a cavity (36) so that a high pressure can be maintained without a pressure loss because the tube (2) is independent of the space (53) in the blade ring.

Abstract: A seal assembly that seals a gap formed by a groove comprises a seal body, a biasing element, and a connection that connects the seal body to the biasing element to form the seal assembly. The seal assembly further comprises a concave-shaped center section and convex-shaped contact portions at each end of the seal body. The biasing element is formed from an elastic material and comprises a convex-shaped center section and concave-shaped biasing zones that are opposed to the convex-shaped contact portions. The biasing element is adapted to be compressed to change a width of the seal assembly from a first width to a second width that is smaller than the first width. In the compressed state, the seal assembly can be disposed in the groove. After release of the compressing force, the seal assembly expands. The contact portions will move toward a surface of the groove and the biasing zones will move into contact with another surface of the groove.

Abstract: An interface seal for a turbine engine including a rotor shroud hanger including at least one opening, an outer band including an aft rail, and a seal spring mounted in the opening and extending over an interface between the outer band and the shroud hanger, is described. The seal provides a barrier that prevents the leakage of high pressure cooling air through the interface into the combustion gas flowpath bypassing turbine engine components, and thus forces the high pressure cooling air through the necessary turbine engine components.

Abstract: A ceramic turbine inlet vane(s) is resiliently mounted to stator portions (10) and (15) of a gas turbine engine by outer and inner resilient mounts (20) and (25). The resilient mounts each include springs, which accommodate varying rates of radial and axial thermal expansion between the vane and adjacent metallic stator structure.

Abstract: A turbine assembly having a turbine stator, a ceramic inner shroud, and a first spring. The stator has a longitudinal axis and an outer shroud block with opposing and longitudinally outward facing first and second sides. The first side has a longitudinally outward projecting first ledge and has a first side portion located radially outward of the first ledge. The ceramic inner shroud has a first hook portion longitudinally and radially surrounding the first ledge. The first spring is attached to one of the first side portion and the first hook portion and unattachedly and resiliently contacts the other of the first side portion and the first hook portion.

Abstract: A rotating shaft for pumping or degassing hydrogen from molten metal comprising a motor connected to the upper end of a hollow shaft. An impeller is connected to the lower end of the shaft in the molten metal. The shaft is telescopically housed within a heat resistant shield shaft. The shield is clamped in a state of longitudinal compression to prevent tensile forces from damaging the shield as the impeller is being rotated.

Abstract: A turbine plant, in particular a steam-turbine plant, includes at least two turbine sections, each having a turbine rotor extending along a main axis and an inner casing accommodating guide blades. At least one inner casing is displaceable in axial direction and a thermally expanding thrust element is provided for an axial displacement. The trust element has first and second expansion components connected to one another by a coupling component. The coupling component mechanically and/or hydraulically produces an axial displacement of the second expansion component which is greater than a thermal expansion and/or axial displacement of the first expansion component. A thrust element for reducing different axial expansions between two components expandable independently of one another along a main axis, is also provided.

Abstract: A variable diameter shroud ring (21) for the turbine of a gas turbine engine (10) comprises a support structure (25) which carries an annular array of circumferentially spaced apart ceramic segments (26). The radially outer surfaces of the segments (26) are overlaid by a plurality of circumferentially extending metallic sheets (38). The sheets (38) serve to inhibit gas leakage through gaps between the segments (26) as the diameter of the shroud ring (21) is varied.

Abstract: The high pressure inlet bleed heat system includes a plurality of tubes which receive heated compressed air from the compressor extraction discharge manifold. The tubes extend into the inlet duct of the compressor, are uniformly spaced one from the other and have a uniform distribution of laterally opening apertures along their lengths in registration with the apertures of next laterally adjacent tubes. The tubes are located downstream of the silencer baffles. By providing choked flow through the apertures and lateral registration of the apertures of adjacent tubes, complete mixing of the heated air with the inlet air vortices behind the silencer baffles is achieved, affording a uniform temperature distribution across the inlet duct with minimum pressure loss. The tubes are constructed to accommodate thermal expansion of the manifold receiving compressor discharge air, the manifold also being supported to accommodate thermal expansion and contraction.

Abstract: A cooling medium path structure for cooling a gas turbine blade. The structure includes a disk-side cooling medium path, a blade-side cooling medium path formed at the root portion of the blade and a delivery block disposed between the two cooling medium paths so as to establish communication therebetween. The delivery block is provided with an elastic engaging section which comes into elastic and line-contact with the disk-side cooling medium path and the blade-side cooling medium path. Thus, the sealing property of the contact portions of the structure is secured so as to allow a cooling medium to be supplied without leaking from the cooling medium paths. The heat of the cooling medium, generated as a result of cooling the high-temperature portion of the gas turbine, can be recovered so as to make the best use of the heated medium.

Abstract: A sealing element seals a gap which may be formed between two components that are movable thermally relative to one another. Each component has a component groove located one opposite the other. The sealing element is directed along a center line, in a cross-section essentially perpendicular to a main line, and has a first end, a second end located opposite the first end and a toothed middle region located between the ends. The sealing element is suitable in particular for sealing off a gap between guide blades at high temperatures in a gas turbine plant for the purpose of preventing a gas flow out of a cooling-gas region into a hot-gas region. A gas turbine plant is provided with the sealing element for sealing the gap.

Abstract: An assembly for improving the operation of a gas turbine engine having an annular turbine support case and a plurality of shroud segments supported on the inner, radial side of the turbine support case. The shroud segments are located end-to-end to form an annular shroud within the turbine support case. Slots are provided in each of the adjacent ends of adjacent shroud segments, and seals are provided for insertion in the slots for sealing the gaps between the adjacent ends of adjacent shroud segments. The seals further include extensions which cooperate with the turbine support case to prevent rotation of the shroud segments relative to the turbine support case.

Abstract: A seal for stator vane segments within a gas turbine engine is provided which includes an axial member and an end member. The axial member includes a central portion and at least one axial joint element extending out from the central portion. The central portion has across-section which includes a pair of substantially u-shaped circumferential ends connected by an arcuate midsection. The axial joint element transitions from the arcuate midsection to a substantially flat end. The end member includes an end joint element attached to a radial portion. The axial and end joint elements contact each other to prevent leakage therebetween, and also sidably cooperate with each other to accommodate misalignment between the axial member and the end member.

Abstract: A baffle plate (12A) is constructed such that two belt-like elements, bent in a warped arc, are joined by spot welding (13) or brazing (14) at a central portion thereof along a central circumferential portion. Thus, even if there is a difference in a radial directional deflection of grooves (11) between adjacent discs (9), the baffle plate (12A) will maintain close contact with the inner surfaces of the grooves (11) due to a spring effect and gas leakage is thereby prevented.

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 seal assembly for a turbine blade tip shroud including a one-piece bent metallic sheet intersegment seal having an axial component and a vertical component adapted to fit in a groove formed in the end walls of each shroud segment, wherein the shroud segment has a platform and radially extending ribs, and the seal fits tightly in the groove providing an axial and a radial component to the seal. A ring seal is also provided for sealing a joint between the shroud and a mounting structure where an annular gap is formed having an "L" shaped cross-section, the ring seal having a "C" shaped configuration and one of the legs of the "C" extending within an axial component of the "L" shaped gap. The leg has a wave pattern with the peaks of the wave in contact with opposite radial walls of the axial component of the gap for creating a gas seal at the joint.

Abstract: An improved heat insulation assembly for a thermal turbo-engine having hollow spaces, is provided with the assembly including a heat-insulating material enclosed within a heat-resistant cover that is formed such that it permits an increase in the inner volume, and the heat-insulating material being a heat-insulating material which increases its volume upon heating to such an extent that the cover is expandable until contact with the inner side of a corresponding hollow space.

Abstract: While remaining in one piece and unsectored, a nozzle permits a slight radial expansion of an assembly. The nozzle is formed by an inner platform mounted in a sliding manner with respect to a stator and an outer platform mounted in a free manner with respect to the case of the stator. Rods are fitted in a pivoting manner so as to radially guide and axially block upper parts of vanes, which are mounted in a sliding manner in the inner platform. The assembly is advantageously completed by gaskets. The nozzle can be used in high pressure turbines of turbojets.

Abstract: A shroud for a rotor assembly disposed within a case is provided. The shroud includes suspension apparatus, a control ring, and a blade outer air seal. The suspension apparatus is disposed between the control ring and the case. The control ring includes a body and a first attachment mechanism. The blade outer air seal includes a second attachment mechanism. The first and second attachment mechanisms cooperate to secure the blade outer air seal to the control ring.

Abstract: A turbine frame includes annular outer and inner bands with circumferentially spaced apart struts extending therebetween. Annular outer and inner liners adjoin the outer and inner bands, and a plurality of fairings surround respective ones of the struts and are joined to the liners. A plurality of circumferentially spaced apart telescopic outer and inner joints support the liners to the bands, and allow unrestrained differential thermal radial movement therebetween.

Abstract: A turbine nozzle includes outer and inner bands having respective mounting holes therein. A plurality of vanes extends through respective pairs of outer and inner holes in the bands. The vane outer and inner ends are resiliently supported to the bands to allow differential thermal movement therebetween so that the individual vanes float relative to the outer and inner bands to prevent thermal stress failure thereof.

Abstract: A rotor cooling circuit includes a cooling medium supply reservoir for supplying cooling medium to a plurality of axial passages through the turbine wheel and spacer disc rims. A passageway communicates cooling medium from the reservoir for flow in series and in a serpentine manner in and about the cavities between the wheels and discs. The flows are reunited at a plenum for flowing the cooling medium into first and second stage buckets. Return passages through the rims of the wheels and spacer discs return spent cooling medium from the buckets to a return location external of the rotor. Transition elements between the buckets and spacer plates in the rotor rim accommodate any thermal mismatch between the adjoining buckets and spacer plates to prevent cooling medium leakage at the joints.

Abstract: A turbine nozzle support assembly includes nozzle segments each having an inner band with an integral retention flange extending radially inwardly therefrom. A plurality of retention tabs extend radially inwardly and are spaced axially aft of the retention flange to define a capture slot therebetween. A nozzle support includes a radially outwardly extending upper flange having a plurality of support pins extending axially, forwardly therefrom and disposed in complementary retention apertures in the retention flanges of the nozzle segments. A retention key is disposed in the capture slot axially between the upper flange and the retention tabs for axially retaining the nozzle segments on the nozzle support.

Abstract: A guide vane ring having guide vanes is provided on two rings which are arranged coaxially and radially at a distance from one another. These two rings are held on assigned housing sections which are subjected to thermally different expansions. One ring is rigidly connected with the guide vanes, and the other ring is connected with the free ends of the guide vanes by the compressive force of a tensioning element. In addition, the other ring is divided into several piston-ring-type elements which axially follow one another and which are each slotted approximately axially and form a cylindrical sliding surface for the whole free ends of the vanes. The tensioning element is arranged on the one group of assigned housing sections while forming a radial compressive force distributed uniformly on the elements.

Abstract: A nozzle seal arrangement, for a turbine nozzle of a gas turbine engine, which impedes leakage of high pressure cooling air past the nozzle inner bands into the flow path to the outside thereof. The nozzle seal arrangement includes an annular nozzle support flange attached to and extending along the stationary support structure adjacent to the nozzle, a band flange attached to and extending along the inner band of each nozzle segment and disposed adjacent to the support flange, a continuous seal member having a W-shaped configuration in cross-section which extends circumferentially about the central axis, and an annular recess defined in the forward face of the nozzle support flange which extends circumferentially about the central axis and receives and seats the seal member at the aft side thereof.

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: A compressor discharge flowpath for a gas turbine engine includes flowpath outer and inner walls joined to a plurality of circumferentially spaced flowpath dividers extending therebetween. An inner support extends from the inner wall and is joined to a turbine nozzle, and an outer support extends from the outer wall and is joined to an engine casing. The outer support preferably includes a plurality of circumferentially spaced beams being sized and configured for carrying both axial force and torque transmitted therethrough from the turbine nozzle to the casing while allowing the beams to bend radially for accommodating differential thermal movement between the casing and the outer wall.

Abstract: The stator blades (10) are made of a thermostructural composite material and have asymmetric inner and outer roots (14, 16) such that at least one of the roots of an a blade presses against the outer side (12b) or inner side (12b) of a neighboring blade. Also, each root (14, 16) of each blade presses against the adjacent ring by a part only of its external surface, thereby allowing some flexing of the root under the effect of differential expansion between the blade and the ring.

Abstract: The transition piece seal spring includes a pair of integrally formed spring clips folded at one end to define a support slot, the spring clips being disposed in back-to-back relation one to the other. Each spring clip includes a pair of elongated, arcuately disposed spring segments spaced one from the other defining a slot for receiving the outwardly directed flange of the transition piece edge. A flat leaf spring is received in the support slot and mounts the spring clip to the first-stage turbine outer nozzle support ring such that the spring clips depend radially between the flanges of adjacent edges of the transition pieces. The spring clips enable radial, circumferential and axial vibratory movement of the adjacent transition pieces whereby motion is taken up in high cycle fatigue rather than wear.

Abstract: An apparatus for effecting a seal between two structural components of a turbo machine or similar device comprises a leaf seal located in the space between the two components and a spring which continuously biases the leaf seal into a sealing position against the components regardless of the pressure differential across the leaf seal.

Abstract: The invention concerns a connector, in an aircraft engine, for mounting a ring to a turbine rotor which the ring surrounds. The ring carries propeller blades, and the connector transmits both thrust and torque loads between the ring and the rotor, without significant deformation. However, the connector does deform in order to accommodate differential thermal growth between the ring and the rotor.

Abstract: Clearance control is provided by circumferentially segmented cooling manifolds having spray bars located radially outside selected components of the stator casing. Cooling air is directed onto stator components and returns immediately through circuitous paths to improve uniformity of cooling. The spray bars extend through limited circumferential angles to limit distortion due to uneven heating.

Abstract: A compressor casing in a gas turbine engine includes an inner jacket formed by two half-shells connected by coupling flanges having cylindrical bellows fitted therebetween and arranged to expand and contract to control the inner diameter of the casing depending on the pressure within the bellows as provided by a supply of air taken from the downstream end of the compressor. The two half-shells are also interconnected by an additional flexible connection.

Abstract: A steam turbine including a casing structure which has an outer cylinder and the inner cylinder, a blade support ring, a plurality of stationary blades arranged in a number of annularly-shaped rows along the length of the turbine on the ring, and a rotor with a plurality of rotating blades arranged in a number of annularly-shaped rows along the length thereof and attached thereto, also includes improved structure providing integrated casing alignment and steam extraction. The improved structure, in combination with the conventional extraction steam piping that exits from the inner cylinder, includes a load plate arranged perpendicularly to the extraction steam piping, one or more flex plates attached between the load plate and the inner cylinder, a plurality of alignment lugs attached in predetermined positions about the load plate, and a plurality of stiffening gussets attached both to the alignment lugs and the load plate.

Abstract: A nozzle vane assembly for a gas turbine exhibits a number of circumferentially spaced vanes connected to a shroud. A second, concentric shroud is arranged separately and urged axially against the unrestrained ends of the vanes through a spring loaded clamping device. This arrangement serves to alleviate thermal stresses and thermal fatigue in the vane assembly.

Abstract: An annular cast inner support member is concentrically mounted within an annual cast outer support member for mounting a plurality of radially extending outlet guide vanes within the flowpath of a gas turbine engine. The outlet guide vanes are resiliently connected to the inner and outer support members to control and limit the compressive loading of the outlet guide vanes caused by thermal stresses during engine operation. A resilient clamped interconnection which is particularly suitable for use with ceramic outlet guide vanes includes a bolted and clamped socket assembly which maintains both radial and circumferential compressive forces on the outlet guide vanes at all times, notwithstanding the differences in thermal growth rates between metal and ceramic materials.