Abstract: A seal system between a row of buckets supported on a machine rotor and a surrounding stationary casing or stator includes a tip shroud secured at radially outer tips of each of the buckets, the tip shroud formed with a radially-projecting rail. A cellular seal structure is supported in the stationary stator in radial opposition to the tip shroud and the rail. The seal structure has an annular array of individual cells formed to provide continuous, substantially horizontal flow passages devoid of any radial obstruction along substantially an entire axial length dimension of the cellular seal structure to prevent flow about the tip shroud from turning radially inwardly.

Abstract: A MCrAlY alloy, methods to produce a MCrAlY layer and a honeycomb seal are provided. The MCrAlY alloy includes chromium, aluminum, yttrium and iron and optionally titanium, hafnium or silicon. The honeycomb seal includes a substrate, honeycomb cells and a protective coating on side walls of the honeycomb cells or a diffusion area inside side walls of the honeycomb cells, the protective coating or the diffusion area including the MCrAlY alloy.

Abstract: A method and composition are provided for coating honeycomb seals and, more specifically, to a method and slurry for applying an aluminide coating onto honeycomb seals. The method includes preparing a slurry of a powder containing a metallic aluminum alloy having a melting temperature higher than aluminum, an activator capable of forming a reactive halide vapor with the metallic aluminum, and a binder containing an organic polymer. The slurry is applied to surfaces of the honeycomb seal, which is then heated to remove or burn off the binder, vaporize and react the activator with the metallic aluminum to form the halide vapor, react the halide vapor at the substrate surfaces to deposit aluminum on the surfaces of the seal, and diffuse the deposited aluminum into the surfaces to form a diffusion aluminide coating.

Abstract: Disclosed is a honeycomb structure for non-hermetic rotor-stator and rotor-rotor seals in turbo machines. Said honeycomb structure comprises a plurality of at least predominantly radially oriented honeycomb cells which are separated by cell walls, are open on one side, cooperate with at least one sharp sealing edge that rotates relative to the honeycomb structure, and can yield relative to the sharp sealing edge by being deformed and/or material being removed therefrom when being touched. The walls of the honeycomb cells have holes according to a defined perforation pattern.

Abstract: The instant invention provides a torodial internal combustion engine with lengthened pistons that move through three perpendicularly intersecting torodial cylinders. The engine includes one central power ring and a pair of charge rings which intersect opposite quadrants of the power ring at right angles to supply a fuel/air mixture to the power ring for combustion. The charge rotors are connected to the power rotor, through a gear-train, so that all of the rotors rotate at the same rate. The fuel/air mixture is combusted within a combustion chamber formed entirely within the power ring.

Abstract: A seal system for an intersection between a turbine stator and a turbine rotor to seal cooling fluids. The seal system may be formed from a seal base extending from the turbine stator, an arm extending radially outward from the turbine rotor and toward the seal base but terminating short of the seal base thereby creating a gap between the seal base and the arm. The seal system may include a honeycomb shaped seal attached to the seal base and extending radially inward from the seal base toward the arm. An outer sealing surface of the seal may be nonparallel with a longitudinal axis about which the turbine rotor rotates thereby enabling the distance of the gap to be reduced with axial movement of the turbine rotor.

Abstract: The rim seal is positioned in an annular space between blades and a non-rotating adjacent structure in a gas turbine engine. The rim seal is connectable to the non-rotating structure and is made of an abradable material.

Abstract: A seal assembly (52, 54) for a gas turbine engine (10). The seal assembly (52, 54) includes a first seal member (40) including an abradable structure having at least first and second seal portions (58, 64) radially spaced from each other, and a second seal member (44) including first and second seal surfaces (56, 62) located in facing relationship to the first and second seal portions (58, 64), respectively. The first seal member (40) is formed of a honeycomb structure, and the first seal portion (58) of the first seal member (40) is a thin fin-like structure having a width in the axial direction of the turbine engine (10) that is less than the width of the second seal portion (64) in the axial direction.

Abstract: An anti-rotation device for preventing rotation of a damper spring and an inner air seal in a stator assembly is provided. The anti-rotation device is formed by a lug positioned within a slot at a center of an inner air seal arc segment. The lug engages a slot in the damper spring and a cutout in a stator segment so as to prevent rotation of the damper spring and the inner air seal in either direction relative to the stator assembly.

Abstract: An anti-rotation device for preventing rotation of a damper spring and an inner air seal in a stator assembly is provided. The anti-rotation device is formed by a lug positioned within a slot at a center of an inner air seal arc segment. The lug engages a slot in the damper spring and a cutout in a stator segment so as to prevent rotation of the damper spring and the inner air seal in either direction relative to the stator assembly.

Abstract: In fluid machines frequently gaps between movable and stationary structural parts have been sealed off. Frequently so-called labyrinth packings are used, whereby sealing strips brush against the opposite structural part. To this end, a brush layer is configured as a porous coating that can be detached from the opposite structural part. The inventive system can be advantageously used in virtually any fluid machines.

Abstract: A shroud segment for being incorporated in a gas turbine engine having a turbine case and a rear turbine case connected with a rear end of the turbine case so as to suppress influence of hot combustion gas on the turbine case and the rear turbine case, is provided with a back plate formed in an arc shape and supported by the turbine case, a touching member integrally formed on an inner surface of the back plate for touching with a rotating turbine blade; and a jet shield extended from a rear end of the back plate and slanted radially inward so as to shield the rear turbine case from a jet of the hot combustion gas.

Abstract: A steam gland includes a steam inlet scroll and an extraction scroll axially spaced from one another defining high and low pressure regions. A seal body is disposed between the regions and includes a pair of brush seals axially spaced from one another. Intermediate the brush seals is a honeycomb seal. The hybrid brush seal/honeycomb seal combination minimizes steam leakage between the high and low pressure regions and eliminates the possibility of heat induced damage to the rotor while optimizing seal leakage performance.

Abstract: A seal between the inner ring of a diaphragm nozzle segment and the periphery of a rotor in a steam turbine includes a honeycomb structure brazed onto the radial inner surface of the inner ring segment. The labyrinth teeth on the rotor cut or rub into the surface of the honeycomb structure, forming a seal. The honeycomb structure is preferably a cobalt-based nickel alloy brazed to the inner ring having multi-sided cells opening radially inwardly toward the rotor. The seal precludes or minimizes steam leakage flow between the high pressure upstream flow region and the downstream lower pressure region on opposite sides of the nozzle/rotor interface.

Abstract: A device for reducing the sealing gap between a rotating component and a stationary component inside a rotary turbo-engine through which a flow passes axially and in which the rotating component and the stationary component each have a surface portion arranged separated by a sealing gap and providing sealing structures on at least one of the two surface portions, one of the sealing structures being an abradable planar sealing structure. The surface portion opposite the abradable planar sealing structure likewise has an abradable planar sealing structure, and the two sealing structures bound the sealing gap in a planar manner.

Abstract: The invention provides a brush seal assembly, and method of using, for reducing adverse fluid flow effects to a brush seal,.the brush seal assembly comprising a support housing having a passage; a rotating shaft disposed in the passage of the support housing, the rotating shaft including a shaft body having a periphery and an annular tooth extending around the periphery of the shaft body; and an annular brush seal including a plurality of bristles extending around the shaft body, each of the plurality of bristles attached to and extending from the support housing in the passage towards the rotating shaft.

Abstract: An abradable turbine seal having a novel honeycomb cellular structure fabricated from metal foils or sheets showing good manufacturability, optimized brazeability and especially good structural integrity and oxidation resistance after brazing to metal support structures. MCrAlY (M=Ni, Fe, Co or combinations thereof) foil and sheet metals are particularly suitable to produce such a structure.

Abstract: The present invention provides for a method to reduce the strength of the honeycomb of a jet turbine stator, increasing its machinability, with a resultant reduction in measured peak tooth temperature, while maintaining or even improving its high temperature capability, so as not to limit its operating environment. The air seal functionality is unaffected, and even improved in some instances. The machinability of the honeycomb is increased by using a light element diffused into the honeycomb ribbon to produce the effect of reducing its strength and ductility while maintaining the environmental resistance needed. The present invention also includes the stator honeycomb produced by the foregoing method.

Abstract: A honeycomb structure seal is provided for the casing of a turbine, particularly a gas turbine, having a base plate facing the casing wall as well as a brush-against section facing the tips of the turbine rotor blades. The seal includes a multi-layered construction such that the base plate is adjoined by an air-evacuated honeycomb structure section which is therefore insulating in partial areas by a vacuum and which is covered by an intermediate plate, on whose side facing away from the honeycomb structure section the brush-against section is arranged. The intermediate plate is soldered to the honeycomb structure section under vacuum conditions. The brush-against section can also be constructed as a honeycomb seal, in which case the honeycomb cells of the honeycomb structure section have a significantly larger partial surface than the honeycomb cells of the brush-against section.

Abstract: A gas turbine seal structure provided between end portions of a moving blade platform and a stationary blade inside shroud. The sealing performance of the seal structure is improved by increasing the resistance to the flow of air. A seal plate (21, 31) is mounted to an end portion of a platform (2, 2′) of the moving blade (1) and a seal portion is formed by seal fins (22, 32) and a honeycomb seal (16, 17) disposed on a lower surface of an end portion (12a, 12b) of an inside shroud (12) of a stationary blade (11). Sealing air from the stationary blade (11) produces a high temperature in a cavity (14) and flows into a space (18, 19), and also air leaking from the cooling air of the moving blade (1) is able to escape into a high temperature combustion gas passage through a seal portion. However, since the seal plate has three seal fins (22, 32) that are inclined in a direction so as to oppose the air flow, air resistance is increased and the flow of air into the combustion gas passage is prevented.

Abstract: A rotatable seal element 38 is formed of at least two circumferentially continuous rings 48,50. The rings have decreased thickness T.sub.2, T.sub.3 in the outward direction. Various construction details are developed which effect the level of cyclic fatigue life. In one particular embodiment, the seal element has a flat surface 74 extending inwardly from the sides at the interface between the rings.

Abstract: A rotatable seal element 38 is formed of at least two circumferentially continuous rings 48,50. The rings have decreased thickness T.sub.2, T.sub.3 in the outward direction. Various construction details are developed which effect the level of cyclic fatigue life. In one particular embodiment, the seal element has a flat surface 74 extending inwardly from the sides at the interface between the rings.

Abstract: In order to realize a seal device of a gas turbine interstage portion which is excellent in a sealing ability during regular operation of the gas turbine, a gas turbine interstage portion seal device is constructed comprising a honeycomb seal (2) of a ring shape provided to an inner side of a turbine stationary blade inner ring (1) and a plurality of seal fins (5) of a ring shape provided to an outer side of a turbine disc seal arm portion (4). Also, an inner side surface of the honeycomb seal and outer peripheries of the plurality of seal fins, comprise large diameters and small diameters, and convex and concave portions formed thereby respectively are mated with each other.

Abstract: A method for designing bearings, of improved performance, the load-bearing surfaces of which feature micropores about 2 to 10 microns deep and, preferably, aspect ratios on the order of 7 to 20. The hydrodynamic pressure distribution of a suite of bearing surfaces with different micropore geometries and densities is modeled numerically. The load-bearing surfaces of the bearings are fabricated with micropores having the optimal density and geometry determined by the numerical modeling. Conical micropores may be created by single laser pulses, with the pore size and shape controlled by controlling the laser beam profile, the laser beam power, and the optical parameters of the focusing system.

Abstract: A method for designing bearings, of improved performance, the load-bearing surfaces of which feature micropores about 2 to 10 microns deep and, preferably, aspect ratios on the order of 7 to 20. The hydrodynamic pressure distribution of a suite of bearing surfaces with different micropore geometries and densities is modeled numerically. The load-bearing surfaces of the bearings are fabricated with micropores having the optimal density and geometry determined by the numerical modeling. Conical micropores may be created by single laser pulses, with the pore size and shape controlled by controlling the laser beam profile, the laser beam power, and the optical parameters of the focusing system.