Abstract: A method and a coating are provided for attaining protection of a substrate being formed of chromium steel for a component of a turbomachine, against at least one of corrosive and erosive attack at a temperature up to approximately 500.degree. C. An aluminum-containing metal coating is applied to the substrate. At least the surface of the metal coating is hardened or age-hardened to form a protective coating containing aluminum.

Abstract: This invention relates to a single crystal casting to be used under high stress, high temperature conditions up to about 2030.degree. F., characterized by an increased resistance to creep under such conditions. The casting is made from a nickel-based superalloy consisting essentially of the following elements in percent by weight: from 6.2 to 6.8 percent rhenium, from 1.8 to 2.5 percent chromium, from 1.5 to 2.5 percent cobalt, from 8 to 9 percent tantalum, from 3.5 to 6 percent tungsten, from 5.5 to 6.1 percent aluminum, from 0.1 to 0.5 percent titanium, from 0.01 to 0.1 percent columbium, from 0.25 to 0.60 percent molybdenum, from 0 to 0.05 percent hafnium, from 0 to 0.04 percent carbon, from 0 to 0.01 percent boron, from 0 to 0.01 percent yttrium, from 0 to 0.01 percent cerium, from 0 to 0.01 percent lanthanum, from 0 to 0.04 percent manganese, from 0 to 0.05 percent silicon, form 0 to 0.01 percent zirconium, from 0 to 0.001 percent sulfur, from 0 to 0.

Abstract: The present invention relates to a steam turbine comprising a rotor shaft integrating high and low pressure portions provided with blades at the final stage thereof having a length not less than 30 inches, wherein a steam temperature at first stage blades is 530.degree. C., a ratio (L/D) of a length (L) defined between bearings of the rotor shaft to a diameter (D) measured between the terminal ends of final stage blades is 1.4 to 2.3. This rotor shaft is composed of heat resisting steel containing by weight 0.15 to 0.4% C, not more than 0.1% Si, 0.05 to 0.25% Mn, 1.5 to 2.5% Ni, 0.8 to 2.5% Cr, 0.8 to 2.5% Mo and 0.15 to 0.35% V and, further, the heat resisting steel may contain at least one of Nb, Ta, W, Ti, Al, Zr, B, Ca, and rare earth elements.

Abstract: To manufacture a turbine wheel having blades made of a ceramic or composite material and inserted into a metal hub, firstly blades (16) are manufactured that are right cylindrical, each blade having a base (18) through which a hole is formed; a cylindrical ring (20) is formed, the ring being provided with orifices through which the bases (18) of the respective blades (16) are inserted; the blade bases (18) are successively threaded onto an open annular rigid metal wire (30); the resulting assembly (16, 20, 30) is disposed inside a sealed housing (161); hot isostatic compaction is performed so as to compact a metal alloy in powder form (41) inside the sealed housing (161) so as to make the hub of the turbine wheel (100) while embedding the blade bases (18) and the metal wire (30) by using the powder metallurgy technique; and the outside portion of the sealed housing (161) delimiting the hub of the turbine wheel (101) is machined. Application, in particular, to the field of aeronautical or space engineering.

Abstract: A method for counteracting distortion of the airfoil caused by laser shock peening a gas turbine engine compressor metallic airfoil along its leading and/or trailing edge to form laser shock peened surfaces extending radially along at least a portion of the edges with a region having deep compressive residual stresses imparted by laser shock peening (LSP) extending into the airfoil from the laser shock peened surfaces.

Abstract: A rotating blade or stationary vane of a gas turbine which is made of a nickel alloy containing Cr, Co, Mo, W, Ta, Al, Ti, C, B, Zr, and one or both of Mg and Ca. Additionally, the alloy may contain Hf, Pt, Rh and Re.

Abstract: A NiAl intermetallic alloy and article is provided with improved high temperature strength, particularly stress rupture strength, through the generation of a multiphase microstructure comprising a beta matrix and at least one precipitate phase. The strength properties and microstructure are the result of alloying with at least two elements selected from Ga, Hf, and optionally Ti, Zr, Ta, Nb, and V, in defined ranges. Preferred are at least two of the elements Ga, Hf, and Ti, and specifically preferred are all three. A specifically preferred form of the invention, in atomic percent, is about 45-59% Ni, about 0.02-0.5% Ga, about 0.2 to less than 1% Hf, about 0.1-10% Ti, with the balance A1 and incidental impurities.

Abstract: A metallic component of a gas-turbine installation is formed of a nickel-based base material and at least two coating layers superimposed on the base material for improving corrosion-resistance thereof. The coating layers include a first layer having a composition and/or thickness for resisting corrosive attack of the nickel-based base material at temperatures of 600.degree. C. to 800.degree. C. (HTCII), and a second coating layer having a composition and/or thickness for resisting corrosive attack of the base material at temperatures of 800.degree. C. to 900.degree. C. (HTCI).

Abstract: Gas-cleaning equipment is disclosed, which comprises a housing having an intake vent and an exhaust vent and having disposed between the two vents a fan having at least one rotating blade. Air pollutant-removing system using the gas-cleaning equipment is also disclosed. This gas-cleaning equipment can effectively clean a gas through the action of plasma produced by glow discharge caused by rotation of said fan. When a metal layer having a catalytic activity is fixed onto the surface of said rotating blade, this metal layer also functions to effectively clean the gas. In the case where both the plasma and the metal layer function to clean the gas, there can be obtained synergistic effects. Cleaning of the gas can be conducted with more efficiency by bringing the intake gas into contact with the fan in an oxygen-free state. A magnet provided as an outer wall of the housing serves to generate plasma with higher density, leading to more effective cleaning of the gas.

Abstract: Metal alloy fan blades reinforced with a metal matrix composite for enhancing stiffness of the fan blades without a significant weight penalty, and which are suitable for use in high bypass turbofan engines. The metal matrix composite is bonded to each fan blade near its root so as to increase stiffness and thereby provide frequency and stability control to the fan blades. As a result, a lower engine weight can be realized by using more fan blades without the need for a part span shroud.

Abstract: A heavy-duty gas turbine includes a compressor; a combustion liner; a turbine blade in a single stage or multi-stages; and a turbine nozzle provided in correspondence to the turbine blade. The turbine blade has a dovetail secured to a turbine disk and has an overall length of not less than 180 mm, and it is made of a single-crystal Ni-base alloy whose .gamma. phase is a single crystal. Operating gas temperature is not less than 1400.degree. C., and metal temperature of a first blade is not less than 1000.degree. C. under working stress.

Abstract: A rotary seal member, such as a gas turbine engine blade, is provided with an improved surface layer which has an elastic modulus matched with the elastic modulus of a substrate of the member. Also, the surface layer does not form a brittle intermetallic with the substrate at an intended operating temperature. In one form, the surface layer includes abrasive particles adapted to inhibit chemical reaction with the layer material. One specific example is a Ti-alloy substrate having a metallurgically bonded layer based on Nb, and including cubic boron nitride abrasive particles coated with cobalt entrapped in the layer.

Abstract: An impeller for a high-temperature gas blower suitable for a floating conveyor furnace, having vanes each formed of a dispersion-strengthened alloy which includes as a disperse or internal phase 0.1-2.0% by weight of finely divided particles of an oxide of a high melting-point metal, such as Y.sub.2 O.sub.3, Ce.sub.2 O.sub.3, ZrO.sub.2, Al.sub.2 O.sub.3 and Gd.sub.2 O.sub.3, preferably dispersed in an austenite matrix or external phase of Cr, Fe, Al, Ti and Ni. A gas blower having such impeller, and a furnace using such gas blower are also disclosed.

Abstract: A form having a base, a tip, and a major surface, an adhesive layer carried on the major surface and a protective sheet removably covering the adhesive layer, forming a decoratable fan blade removably mountable on a ceiling fan.

Abstract: Blades for use in modern gas turbine engines are described and are characterized by a thin zone of fine grains of a high strength composition on the surface of the blade root.

Abstract: An improved nickel-based single crystal superalloy has both an extremely low sulphur content and a very low lanthanum, cerium, or lanthanum plus yttrium, or cerium plus yttrium, or content, whereby the amount while very low, is sufficient to react with the remaining available sulphur in the alloy and with sulphur from the fuel used in engine operation, such that the very thin, protective scale layer of aluminum oxide formed on the surfaces of the nickel-based alloy parts exposed to the very high temperatures incident in high efficiency turbine engines, will afford effective, long-life protection for the surfaces of these engine components, through the virtual elimination of spalling of the aluminum oxide scale during cyclic engine operations.

Abstract: An internally reinforced hollow structure is described which comprises a layer of titanium metal matrix composite applied to the internal surfaces of structural segments comprising the hollow structure, the segments then being joined to form the desired hollow structure.

Abstract: A coated article comprises a base article having a substrate made of a material selected from the group consisting of a nickel-base alloy and a cobalt-base alloy, an intermediate metallic coating structure, and a thermal barrier coating. The intermediate metallic coating structure may be a protective layer of platinum, rhodium, or palladium on the base article, with no bond coat. The intermediate metallic coating may also be a bond coat, either oxidized or unoxidized, with a protective layer of platinum, rhodium, or palladium thereon. The protective layer typically partially interdiffuses with the underlying metallic structure.

Abstract: A separate inter-blade platform for a turbomachine rotor comprises a structural rectilinear longitudinal member formed by a foam core, plies of a carbon/epoxy type material in bidirectional layers of crossed fibres oriented at 45.degree. laid around the core and around an insert at each end of the longitudinal member, each insert being made of juxtaposed radial plies of a carbon/epoxy type material in bidirectional layers of fibres crossed at .+-.45 degrees, and further plies of a carbon/epoxy type material in unidirectional layers oriented in the direction of the major axis of the longitudinal member covering the upper and lower faces of the member, the platform further comprising lateral packing cores made of a foam material, plies of a glass/epoxy type material covering the lateral faces of the longitudinal member and connecting it to the lateral foam cores, and peripheral plies of a glass/epoxy type material covering the assembly formed by the longitudinal member and the lateral cores connected thereto.

Abstract: A nickel-based superalloy suitable for directed solidification, in particular for industrial gas turbine parts, having the following composition by weight:Co: 0 to 5%Cr: 13 to 16%W: 0 to 2%Mo: 2 to 3.5%Al: 3.5 to 4%Ti: 3.5%Ta: 3.

Abstract: The present invention relates to a steam turbine comprising a rotor shaft integrating high and low pressure portions provided with blades at the final stage thereof having a length not less than 30 inches, wherein a steam temperature at first stage blades is 530.degree. C., a ratio (L/D) of a length (L) defined between bearings of the rotor shaft to a diameter (D) measured between the terminal ends of final stage blades is 1.4 to 2.3. This rotor shaft is composed of heat resisting steel containing by weight 0.15 to 0.4% C, not more than 0.1% Si, 0.05 to 0.25% Mn, 1.5 to 2.5% Ni, 0.8 to 2.5% Cr, 0.8 to 2.5% Mo and 0.15 to 0.35% V and, further, the heat resisting steel may contain at least one of Nb, Ta, W, Ti, Al, Zr, B, Ca, and rare earth elements.

Abstract: An impeller for a high-temperature gas blower suitable for a floating conveyor furnace, having vanes each formed of a dispersion-strengthened alloy which includes as a disperse or internal phase 0.1-2.0% by weight of finely divided particles of an oxide of a high melting-point metal, such as Y.sub.2 O.sub.3, Ce.sub.2 O.sub.3, ZrO.sub.2, Al.sub.2 O.sub.3 and Cd.sub.2 O.sub.3, preferably dispersed in an austenite matrix or external phase of Cr, Fe, Al, Ti and Ni. A gas blower having such impeller, and a furnace using such gas blower are also disclosed.

Abstract: This invention relates to a nickel-based superalloy comprising the following elements in percent by weight: from about 5.0 to about 7.0 percent rhenium, from about 1.8 to about 4.0 percent chromium, from about 1.5 to about 9.0 percent cobalt, from about 7.0 to about 10.0 percent tantalum, from about 3.5 to about 7.5 percent tungsten, from about 5.0 to about 7.0 percent aluminum, from about 0.1 to about 1.2 percent titanium, from about 0 to about 0.5 percent columbium, from about 0.25 to about 2.0 percent molybdenum, from about 0 to about 0.15 percent hafnium, and the balance nickel+incidental impurities, the superalloy having a phasial stability number N.sub.v3B less than about 2.10.

Abstract: A turbine blade, preferably used in the low pressure stages of a steam turbine, is formed from a basic titanium alloy. Near the blade tip, it has a region, including the blade leading edge with a surface of a material which is more resistant to erosion than the basic titanium alloy.This turbine blade should be simple to manufacture and should have a long life even under difficult operating conditions.This is achieved in that the region including the blade leading edge has a protective layer formed by surface treatment of the basic titanium alloy by means of a high-power energy source, such as, in particular, a laser.

Abstract: An airfoil for a gas turbine engine is constructed from a core body formed of a conventional nickel-based superalloy and leading and trailing edge components and squealer tip formed of a nickel aluminide alloy. The nickel aluminide components exhibit a high degree of thermal conductivity and efficiently transfer heat into the core body by direct conduction.

Abstract: To improve the precision of the cooling fine holes of a large-sized and complex-shaped ceramic gas-turbine nozzle with fine cooling holes, a ceramic gas-turbine nozzle with fine cooling holes has a profile degree of 1.0% or less relative to the blade length, a roundness of the fine cooling holes of 0.3 mm or less, and a straightness of the fine cooling fine holes of 1% or less relative to the blade length. This nozzle is prepared by a method in which two compacts of shroud portions and at least one compact of a blade portion and separately molded are joined by isotropic press molding to be calcined, and the predetermined positions of the resulting calcined compact are subjected to supersonic processing to bore cooling fine holes, the resulting compact is then fired.

Abstract: A superalloy article has a nickel-based superalloy substrate containing TCP-phase forming elements such as rhenium, chromium, tantalum and tungsten. A carbide precipitate-containing region is formed within the substrate extending to a carbide depth below a surface of the substrate, preferably by depositing carbon on the surface of the substrate and diffusing the carbon into the substrate. An aluminum-rich diffusion layer extends from the surface of the substrate to an aluminide depth below the surface of the substrate. Preferably, the carbide depth is about the same as the aluminide depth. The presence of the carbide precipitates inhibits the formation of the deleterious TCP-phase.

Abstract: A method is taught for protecting fuel contacting surfaces of a gas turbine engine from carbon deposition by the application of a coating of alumina and silica thereto from a sol gel specifically formulated for this purpose.

Abstract: A turbine blade comprises an airfoil/shank having a shank region and an airfoil region extending upwardly therefrom and two dovetail/platforms bonded thereto. The first dovetail/platform has a first dovetail region bonded to a first side of the shank region of the airfoil/shank, with a first platform region extending outwardly from the first dovetail region. The second dovetail/platform has a second dovetail region bonded to a second side of the shank region of the airfoil/shank and a second platform region extending outwardly from the second dovetail region in a direction generally opposite to that of the first platform region.

Abstract: A turbine or compressor blade designed for deliberate, controlled failure in a gas turbine engine during testing of the engines, includes a lower-strength tubular insert in an axial through bore in the root portion of the blade, which insert fails at preselected conditions to induce blade failure.

Abstract: A flow directing element for the turbine section of a rotary machine includes various construction details which are developed which increase the aerodynamic efficiency of the flow directing element. In one embodiment, the flow directing element is a rotor blade having a roughened surface which approximates the critical roughness characteristic of the airfoil. In one particular embodiment, the roughness average of the surface lies between 120 to 200 AA microinches.

Abstract: A method is taught for protecting the surface of a nickel, cobalt, or titanium alloy from fretting wear by coating said surface with a copper-aluminum alloy.

Abstract: An auger shaped, fluid medium engaging member is disclosed which includes a helically or auger shaped outer region disposed about a longitudinal axis which passes through a central region of the member. The auger shaped outer region establishes at least one auger or helically shaped fluid medium engaging surface, which intercepts the flow of a fluid medium such as air or water, for effecting rotational movement of the fluid medium engaging member about its longitudinal axis. The auger shaped, fluid medium engaging member may be coupled to an electrical generator, for generating electrical energy upon rotational movement.

Abstract: A turbine or compressor blade designed for deliberate, controlled failure in a gas turbine engine during testing of the engines, includes a lower-strength tubular insert in an axial through bore in the root portion of the blade, which insert fails at preselected conditions to induce blade failure.

Abstract: A rotor for a rotary screw machine has helical lobes (12) and grooves (14). A shell structure (18) forming the external surface of the rotor is made of pressed metal power. The rotor is manufactured by cold isostatic pressing of a powder in a vessel having a surface shaping rotor. The pressure is applied radially by means of a cast bag in which high pressure liquids acts. After the pressing process, the rotor blank is sintered and attached to a shaft (16).

Abstract: A system for protecting against erosion the surface of a body which is subjected to an airflow and consists essentially of a fibrous material or a fiber-reinforced plastic material, such as a rotor blade, has a metallic coating which, in the respective area to be protected, covers the surface in several layers. The primary layer of the coating consists of aluminum or a similar material with a modulus of elasticity that is approximately identical to that of the material on the surface of the body. The primary layer, in the form of a sheet glued to the surface, is coated with a two-phase material, in which particles of metallic oxide and/or metallic carbide and/or metallic nitride compounds are embedded in a finely distributed manner in a ductile, solid-solution-hardened matrix of a metallic but non-ferrous material.

Abstract: An extension is provided on an end of an article having a directionally oriented microstructure by using the article end as a growth seed in a molten material compatible with material from which the article end is made. The extension is directionally solidified as integral with and as an extension of the article end and with a microstructure compatible with that of the article end.

Abstract: The turbine blade contains a casting having a blade leaf (1), blade foot (2) and, if appropriate, blade cover strip (3) and composed of an alloy based on a dopant-containing gamma-titanium aluminide.This turbine blade is to be distinguished by a long lifetime, when used in a turbine operated at medium and high temperatures, and, at the same time, be capable of being produced in a simple way suitable for mass production. This is achieved in that, at least in parts of the blade leaf (1), the alloy is in the form of a material of coarse-grained structure and with a texture resulting in high tensile and creep strength and, at least in parts of the blade foot (2) and/or of the blade cover strip (3), provided if appropriate, is in the form of a material of fine-grained structure and with a ductility increased in relation to the material contained in the blade leaf (1).

Abstract: A turbine rotor is formed from a turbine disk having a rim with a circumferential direction, and a plurality of turbine blade segments each fixed to the turbine disk around a circumference of the rim of the turbine disk. The turbine blade segments are oriented such that the elastic modulus of the turbine blade segments parallel to the circumferential direction is less than that of the rim of the turbine disk parallel to the circumferential direction. This arrangement is preferably achieved using single crystal turbine blade segments made of an an alloy having a cubic crystal structure, such as a nickel-based superalloy, with a <010> direction oriented radially and a <001> direction oriented circumferentially.

Abstract: A coating of india-stabilized zirconia protects a self-supporting substrate from high temperatures, as well as vanadate and sulfate corrosion. In one method of making such a protected substrate, a coating of india-stabilized zirconia is applied to the substrate. The substrate can be a metal or ceramic surface of a gas turbine or other type of engine.

Abstract: A method for forming a hollow, internally-ribbed airfoil having a complex geometry. The process forms airfoil halves from alloy members in essentially final machined form. The airfoil halves optionally include a gasket around their periphery and optionally, a gasket around the internal sequence of ribs and cavities. Because the airfoil halves are in final form before joining, important interior airfoil dimensions such as skin thickness, cavity size, rib location and gasket location as well as exterior dimensions such as camber and twist may be verified prior to joining. The airfoil halves are then joined by welding, thereby sealing their interiors and diffusion bonding at relatively low pressures. The gaskets eliminate the use of high pressures and associated skin buckling and permit a concentration of the loads at key locations despite the low pressures. After diffusion bonding, any voids are removed by hot isostatically pressing the airfoil in the superplastic temperature range of the alloy.

Abstract: A structural spar is provided that provides beneficial flexural-torsional coupling to an airfoil so that flexural excursions of the airfoil induces torsion in the spar so as to change the pitch angle of the airfoil in such a manner as to the oppose the flexure, thereby ameliorating the excursion.

Abstract: Provided are molded adsorbents comprising a mixture of adsorbent particles, fine plastic particles and a reinforcing fiber, the mixture having been molded utilizing the fine plastic particles and, as required, the reinforcing fiber as binder. They have features, as compared with conventional molded adsorbents utilizing a latex binder, having an adsorptive capacity having been decreased to a smaller extent from those of the raw material adsorbent particles used and higher adsorption rate owing to well-maintained porosity. They have good mechanical properties at normal temperature and can hence be processed by cutting or like machinings into various machine parts, including blades of fans having both adsorptive capacity and high mechanical properties. Also provided are a process for producing the above molded adsorbents and their use as deodorizing units.

Abstract: A component is provided with a relative undersize in an area to be subjected to increased stress, for instance, through temperature. The component is made of a hardenable steel. The undersize is overlaid with a non-hardenable steel thereby to provide the full size. A second layer on top of the first layer can be provided. When the second layer is metallurgically bonded in a manner that generates heat, it does not cause a heat affected zone in the base hardenable steel. Blades for steam turbines benefit from this procedure.

Abstract: The disclosure is concerned with a thermal land machine which comprises a heat resistant wall for confining a chamber; a heat resistant composite structure disposed in the chamber and in contact with a hot flowing gas; and an apparatus for introducing the hot gas toward the surface of the composite structure. The composite structure including a heat resistant substrate and a continuous refractory coating formed on the substrate and made of a ceramic material. The refractory coating includes at least two layers in a laminated structure each having fine cracks substantially extended in the direction of the thickness of each of the layers and filled with a refractory material in such a manner that the filled cracks in one layer are disconnected with the filled cracks in the adjacent layer. Therefore, the hot gas cannot permeate into the surface of the substrate.

Abstract: A hollow core fan blade for a gas turbine engine, having a continuous leading edge, is fabricated using a four-sheet superplastic forming/diffusion bonding process which results in a cost-efficient and lightweight, yet strong, structure. The rotor blade is comprised of a face sheet which has a 180 degree bend therein so that the two face sheet ends are aligned. Bonded to opposing sides of the face sheet are first and second core sheets, between which is the hollow core. To fabricate the blade, a core sheet assembly is inserted inside the prepared face sheet, thereby forming a Ti-Pack (titanium pack) assembly having a plurality of pressure-tight cells. The Ti-Pack is inserted into a cavity within a die, after which the rotor blade, having predetermined design characteristics, is superplastically formed by heating the die and selectively pressurizing the plurality of cells.

Abstract: An integral covered blading for a turbine is achieved by cutting a short arc cover spanning tips of multiple adjacent blades. Adjacent cover portions are formed for adjacent blades, each portion having facing sides. A material buildup between the facing sides of cover portions is effected and selective machining of the material buildup develops an interface between adjacent cover portions of adjacent blades. Short group blading is thereby converted to equivalent integral covered blading.

Abstract: A structural component made of a base metal composition on a nickel or cobalt basis is provided with a protective coating against oxidation, corrosion, and thermal fatigue. The protective coating and the base metal are made of chemically the same or identical material, whereby the bonding of the protective coating is increased, the tendency to crack is reduced, and the resistance to thermal fatigue is improved. The grain size of the coating is substantially smaller than the grain size of the base metal composition.

Abstract: A beta phase nickel aluminide microalloyed with iron having improved ductility. Nickel aluminide intermetallics alloyed with no more than about 0.5 atomic percent iron have significantly improved room temperature ductility over conventional unalloyed beta phase nickel aluminides or beta phase nickel aluminides alloyed with higher percentages of iron.

Abstract: A flow directing element (such as a rotor blade 34 or a stator vane 44) for the turbine section 16 of a rotary machine is disclosed. Various construction details are developed which increase the aerodynamic efficiency of the flow directing element. In one embodiment, the flow directing element is a rotor blade 34 having a roughened surface which approximates the critical roughness characteristic of the airfoil. In one particular embodiment, the roughness average of the surface lies between 120 to 200 AA microinches.