Abstract: An integral structure comprised of inner and outer coaxial shells mutually supported so as to define an annular passageway between the shells. The integral structure may be an air inlet housing for a gas turbine engine and the inner shell may be a hub member having a generally cylindrical passage extending therethrough for rotatably receiving a drive shaft. The inner shell has an outer surface of revolution. A plurality of duct preforms each include an inner duct surface shaped to congruently mate with said outer surface of said inner member, an outer duct surface spaced from said inner duct surface, and first and second lateral walls having opposed lateral surfaces. The duct member preforms are mounted onto the outer surface of the inner member in side-by-side relationship such that the first and second lateral walls on adjacent pairs of duct member preforms are coextensive and engaged. A coaxial outer shell preform is spaced from the inner member.

Abstract: A ducted fan gas turbine engine nacelle assembly comprises an aerodynamic nacelle within which is enclosed a ducted fan gas turbine engine. The nacelle includes an annular containment structure which surrounds the engine fan and fan casing to contain any detached fan blade or blade parts.

Abstract: Woven fiber ballistic fabric (22) of multiple layers surrounds an isogrid support structure (20). A cuff portion (38) has shorter warp threads than the major portion (3) and also is impregnated with epoxy resin. A diameter restrains the fabric from aft movement during a blade ejection event.

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 ducted fan gas turbine engine is provided with a fan casing provided with a portion adapted to provide fan blade containment in the event of fan blade failure. The containment portion comprises three layers: a wall adjacent the fan blades, a plurality off metallic tubes attached to the radially outer surface of the wall and a layer of strong woven fibrous containment material surrounding the metallic tubes.

Abstract: A turbine nozzle vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine nozzle vane assembly. The turbine nozzle vane assembly includes an outer shroud and an inner shroud having a plurality of horizontally segmented vanes therebetween being positioned by a connecting member positioning segmented vanes in functional relationship one to another. The turbine nozzle vane assembly provides an economical, reliable and effective ceramic component having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the other component.

Abstract: Stator vanes located between compressor stages in a gas turbine engine are fabricated with a composite outer shell made of graphite fibers in an epoxy binder that is laid-up over a core of felt-like material selected to have an elongation velocity that is greater than the elongation velocity of the shell.

Abstract: A turbine wheel assembly includes a disk having a plurality of blades therearound. A ceramic ring is mounted to the housing of the turbine wheel assembly. A labyrinth rim seal mounted on the disk cooperates with the ceramic ring to seal the hot gases acting on the blades from the disk. The ceramic ring permits a tighter clearance between the labyrinth rim seal and the ceramic ring.

Abstract: A thermal load relief ring is disposed between the mating surfaces of adjacent cases of a gas turbine engine and secured thereto by a dowel pin or bolt to assure the concentricity of the cases. The bolt and dowel pin are configured to assure the concentric fit of the components. These configurations allow the cases to be fabricated from different materials to allow a lighter and less expensive case.

Abstract: Turbomachinery rotor components having a metallic body with at least a portion of the body subject to a tensile stress field due to centrifugal and thermal growth induced forces generated by the rotor when the rotor is rotating, at least one stress riser in the stress field portion that causes stress concentration when the rotor is rotating, and at least one region of the component around the stress riser having deep compressive residual stresses imparted by laser shock peening (LSP).

Abstract: A gas turbine engine's nozzle structure includes a nozzle support ring, a plurality of shroud segments, and a plurality of airfoil vanes. The plurality of shroud segments are distributed around the nozzle support ring. Each airfoil vane is connected to a corresponding shroud segment so that the airfoil vanes are also distributed around the nozzle support ring. Each shroud segment has a hook engaging the nozzle support ring so that the shroud segments and corresponding airfoil vanes are supported by the nozzle support ring. The nozzle support ring, the shroud segments, and the airfoil vanes may be ceramic.

Abstract: A light weight isogrid containment structure has minor concessions to weight in order to achieve efficient manufacture oversize flanges are permitted in skin thickness interface zones so that manufacture may be accomplished with fewer milling tools and tool changes.

Abstract: A heat shield which is adapted to be formed on an article which must operate in an environment in which the article is subject to thermal radiation while at an elevated service temperature. The heat shield is composed of a barrier layer formed or deposited on the surface of the article, and a reflective layer on the barrier layer. The reflective layer serves to reflect a majority of the thermal radiation which is incident on the article. The barrier layer serves to substantially prevent degradation of the reflective layer at the elevated service temperature, so as to prevent the reflectivity of the reflective layer from being degraded while the article is in service. The reflective layer is preferably a noble metal, a noble metal alloy or aluminum, while the barrier layer is preferably a nitride, aluminum oxide, yttria-stabilized zirconia, or an oxide which can be grown by oxidation of the article's surface.

Abstract: The inner shroud of the vane of a vane assembly for the compressor section of a gas turbine engine is fabricate from a composite material preferably imide resin reinforced with carbon fibers and is formed into an open ended box-like member segment supporting no less than two vanes or airfoils. The segments are interlocked by a necked down edge adapted to slip into the open end of the adjacent inner shroud of the stator vane that serve to seal the gas path and provide damping. Rub strips are integrally formed on the bottom surface of the inner shroud.

Abstract: A Ni-base superalloy consisting essentially of, by weight: 0.05 to 0.20% C, 20 to 25% Co, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0% Ti, 1.0 to 3.0% Nb, 5 to 10% W, and at least 55% Ni, the combination of the [Al+Ti] and tungsten contents being determined as shown in FIG. 5. This superalloy has a high thermal-fatigue resistance, a great high-temperature strength, particularly, a great creep rupture strength, and a good weldability. The superalloy is used to form gas turbine nozzles, which are employed in a gas turbine. Using such a gas turbine, a combined power generating system is built.

Abstract: A method and apparatus for increasing blade fatigue strength in a turbine engine. The blades in the turbine engine are configured so as to reduce stress at the tip of the blades during operation of the turbine engine, thus increasing blade fatigue strength. This stress reduction helps to counteract the detrimental effect of abrasive tip coatings on blade fatigue strength. In one embodiment, the tip of the blade is chamfered in order to reduce the stress on the tip of the blade. An abrasive coating is then applied to the tip of the blade to assist the blade in seating into an abradable outer air seal. In another embodiment, an abrasive coating is applied to a center portion of the tip of the blade, with the periphery of the abrasive coating being set back from the opposing surfaces of the blade.

Abstract: An abradable coating is provided for use on a composite substrate which has a coefficient of thermal expansion substantially similar to that of the substrate and which is formed with a matrix resin of the same type of resin used to form the substrate. In particular, with a composite substrate formed from carbon or graphite fibers impregnated with a polyimide resin, an abradable coating formed from carbon or glass microballoons in a polyimide resin matrix has been found to avoid delamination as a result of thermal cycling between -65.degree. F. and 500.degree. F. Accordingly, that abradable coating is particularly suitable for use with composite compressor shrouds in gas turbine engines and aircraft auxiliary power units.

Abstract: A molten metal pump including a vaned impeller having a larger outlet area than inlet area which demonstrates prolonged high effectiveness and reduces the likelihood of catastrophic failure.

Abstract: A turbine engine stator has a metal casing surrounding an envelope carrying bearings for the pivots of pivoting blades. A control mechanism for setting the position of the blades includes a radial spindle to which are transmitted the thrust forces of the gases, the envelope being advantageously formed from angular sectors of axially juxtaposed flanges or rings and which are not loaded. Therefore, the bearings are not subject to wear giving rise to gas leaks and efficiency losses. Advantageously, the envelope is made from a composite material.

Abstract: A turbine housing of a turbocharger made of ductile iron and a self-diffused Ni--Cr alloy including C, B and Si fusion-coated to at least the surface of the main portion of the turbine housing. The turbine housing is not likely to be oxidized and deteriorated, and it has durability.

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: The present invention provides a ceramic nozzle guide assembly with an apparatus for mounting it to a metal nozzle case that includes an intermediate ceramic mounting ring. The mounting ring includes a plurality of projections that are received within a plurality of receptacles formed in the nozzle case. The projections of the mounting ring are secured within the receptacles by a ceramic retainer that allows contact between the two components only along arcuate surfaces thus eliminating sliding contact between the components.

Abstract: A method for fabricating a hard faced fan blade containment system for turbofan aircraft engines, and the product resulting from that method. The product combines a hard facing material, a high strength fiber and an elastomeric binder to form a fan blade containment system which is lightweight and effectively retains fan blade fragments. The method consists of lightly bonding layers of high strength fibers together with a small amount of elastomeric binder so that they work in unison as a composite to contain a failed fan blade rather than as individual layers which are subject to sequential failure. In addition, a hard material such as ceramic or heat treated steel is encapsulated in an elastomer and bonded to the impact face of the containment system to blunt sharp edges of failed blade fragments and to spread the impact energy of the blade fragments over a larger area of the high strength fiber backing.

Abstract: A turbine shroud segment includes a substrate and a coating layer having varying thickness. Various construction details are developed that provide minimal spalling of the coating layer during use of the shroud segment. In a particular embodiment, a shroud segment includes a coating layer that tapers towards the edges. The thickness tapers to a minimum thickness along the leading and trailing edges. Within the blade passing region of the shroud segment, the coating layer tapers towards the lateral edges to a thickness determined by the minimum thickness required for abrasive contact between the shroud segment and rotor blades. In another particular embodiment, the varying thickness of the coating layer is produced by forming the substrate with a concave surface, applying the coating, and subsequently machining back the coating layer to the desired dimensions.

Abstract: An improved blade containment structure including a projectile shield having a braided ballistic fabric is disclosed. The braided fabric includes ballistic strands arranged in a preferred orientation and is effective for increasing the ability of the fabric to contain projectiles and absorb energy therefrom. The braided ballistic fabric provides substantial improvement in performance over conventional woven ballistic fabrics.

Abstract: A torque converter stator has a plurality of blades integrally molded between inner and outer rim portions. The inner rim portion has an outer race of a one-way torque transmitting device integrally molded therewith. The outer race includes a plurality of cam surfaces and spring abutment surfaces for the one-way device which cooperate with roller, springs and an inner race which are later assembled therewith to complete the one-way torque transmitting device.

Abstract: A multistage pump of the type including a jacket, a shaft which is coaxial to the jacket and connected to an electric motor, and active pumping stages rigidly coupled to the shaft; each stage is formed by an impeller with a front ring and by a distribution element facing the ring with the interposition of an annular supporting element shaped like an inverted bowl; the radial-vane impellers and their distribution elements are rigidly coupled to the jacket made of a highly wearproof material, and the impellers are mounted on the shaft and can move axially or float with a preset stroke with respect to the associated bowl-shaped element, whereas at least one annular supporting and sealing element for the impeller is interposed between the front ring of each impeller and the associated bowl-shaped element, is made of a material which is more wearproof than the impellers, and is suitable to withstand the axial thrusts of the various stages and prevent any fluid seepage during pump operation.

Abstract: Isogrid structure (20) forms case (14) surrounding the fan blades. In the zones where blade penetration is anticipated, the ribs (38) of the lattice do not run circumferentially. The skin segments (48) are of different thickness in different zones, but do not differ more than 30% from the thickness of an adjoining segment.

Abstract: A stator vane assembly for a gas turbine engine that includes a plurality of circumferentially spaced ceramic vanes, each of which has an inner and outer ceramic shroud, and a ceramic post extending from one of the shrouds, and a metallic platform having a plurality of circumferentially spaced recesses. The posts are inserted into a metallic sleeve and then brazed. The brazed sleeves are then mounted in the recesses. A method for assembling these components to form the stator assembly is also described.

Abstract: Isogrid structure (20) forms case (14) surrounding the fan blades (12) of the turbofan. A ballistic fabric (22) surrounds the case. Containment zones (30, 32, 34) at the forward end have isogrid ribs (38) extending other than circumferentially. In the rear support zone ribs (76) extend circumferentially stiffening the case against collapse.

Abstract: A fluid pump has an integral filament-wound housing bonded to internal parts of the pump. The pump housing is made of composite material (such as fiberglass strands coated with epoxy resin) wound about an adapter, pumping members and an output flange. Once hardened, the housing, adapter, pumping members and output flange are permanently bonded together to form a unitary structure. Pump efficiency is greatly enhanced because the pump housing forms a fluid-tight seal between (a) pumping members and (b) between pumping members and the housing and further prevents rotation of the pumping members in response to torque forces during pump operation.

Abstract: Variable phase vane provided with a composite pivot having a joining piece for receiving the control pieces. The joining piece is made of a material less dense than the actual pivot. These two elements are force-fitted without using any weld or mechanical linking device.

Abstract: An improved containment casing for use with turbomachinery, such as turbofan engines. The containment casing is provided with a ballistic barrier composed of ceramic composite tiles which promotes the ability of the containment casing to withstand an impact from a fan blade which is released within the casing. The barrier is sufficiently hard so as to resist the cutting action of the fan blade, as well as to dull the edge of the fan blade so as to minimize subsequent damage to the containment casing and engine. The barrier serves to distribute the impact of the fan blade, so as to reduce the likelihood of piercing or severing the containment casing.

Abstract: A pump casing made of sheet metal has a substantially cylindrical cup-shaped sheet-metal pump casing having a bottom on one axial and thereof and an opening defined in an opposite axial end thereof. The interior of the pump casing is divided by a partition wall disposed therein into a suction chamber and a hydrocasing chamber with an impeller rotatably housed therein. A suction nozzle is mounted on a cylindrical side wall of the pump casing and communicates with the suction chamber. The partition wall is joined to the bottom of the pump casing. The suction nozzle is positioned over the suction and hydrocasing chambers.

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: A guide vane for an axial guide baffle of an axial flow engine, such as a jet engine, is adjustable in its position about a guide vane adjustment axis extending radially to a rotational engine axis. The guide vane has a vane body and an adjustment lever extending at an angle of about 90.degree. away from the adjustment axis. The vane body, the adjustment lever, and at least one bearing journal form an integral one piece construction either of molded fiber composite material or of forged, e.g. drop forged, metal.

Abstract: A nozzle guide vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The nozzle guide vane assembly includes an outer shroud having a mounting leg with an opening defined therein, a tip shoe ring having a mounting member with an opening defined therein, a nozzle support ring having a plurality of holes therein and a pin positioned in the corresponding opening in the outer shroud, opening in the tip shoe ring and the hole in the nozzle support ring. A rolling joint is provided between metallic components of the gas turbine engine and the nozzle guide vane assembly. The nozzle guide vane assembly is positioned radially about a central axis of the gas turbine engine and axially aligned with a combustor of the gas turbine engine.

Abstract: A Ni-base superalloy consisting essentially of, by weight: 0.05 to 0.20% C, 20 to 25% Co, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0% Ti, 1.0 to 3.0% Nb, 5 to 10% W, and at least 42.5% Ni, the combination of the [Al+Ti] and tungsten contents being determined as shown in FIG. 5. This superalloy has a high thermal-fatigue resistance, a great high-temperature strength, particularly, a great creep rupture strength, and a good weldability. The superalloy is used to form gas turbine nozzles, which are employed in a gas turbine. Using such a gas turbine, a combined power generating system is built.

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 pump casing made of sheet metal comprises a casing jacket having a cylindrical cup shape, an end plate formed at one side of the casing jacket, a casing flange formed at the other side of the casing jacket and a projecting portion radially outwardly bulged so as to have a volute shape. The end plate is axially outwardly bulged so as to have an arcuately curved surface, and the base portion of the projecting portion is located on the extension of the arcuately curved surface of the end plate so as to provide continuity from the end plate to the projecting portion. With the above structure, there is no portion where a great deal of bending stress caused by stress concentration is generated, and the pump casing has a sufficient strength and rigidity against not only piping forces but also internal pressure.

Abstract: A turbomolecular pump comprises a casing having an inlet port at one end portion and an outlet port at another end portion, a rotor supported rotatably within the casing, and a stator fixed on an inner wall of the casing. The rotor has rotor vanes which coact with stator vanes on the stator to pump gas molecules from the inlet port to the outlet port. The rotor and stator vanes are arranged in multi-steps and have ceramic surfaces at the steps near the outlet port of the casing and have metallic surface at all other steps, so as to promote the baking efficiency and obtain extremely high vacuums.

Abstract: A small, compact, relatively low cost, long life and very high speed hydraulic turbine drive. Typical power of this turbine is in the range of 5 to 20 horsepower with operating speeds of 50,000 to 200,000 RPM. The turbine blades are produced at low cost as a part of a thermoplastic turbine wheel and the strength needed for very high centrifugal forces is provided by compressing substantially all of the plastic turbine wheel, except for the blades, within a metal sleeve. A preferred embodiment is driven by a hydraulic pump geared mechanically to a motor vehicle engine and drives a compressor for supercharging the engine.

Abstract: A composite article includes a plurality of laminates each having structural fibers bonded in a matrix, and an adhesive film disposed between and bonding together adjacent ones of the laminates. In an exemplary embodiment, the laminates and the interleaved adhesive films form a facesheet which is joined to a core for forming an impact resistant fan case impact liner for a gas turbine engine. The impact liner may be integrated with a sound suppression liner.

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 high-strength, thin-wall ceramic cylinder partially closed at one end, with radial-inflow turbine blades ground into the partially closed end thereof, provides the rotational drive, surface protection, and burst strength necessary to contain and spin a low strength, disposable soft ceramic capsule, loaded with a sample for NMR experiments, at high rotational speeds inside an NMR receiver/transmitter coil. An improved radial inflow turbine design results in higher efficiency for micro-turbines. A cylindrical air journal bearing at both ends provides radial stability and support. An axial thrust air bearing is formed at the end opposite the turbine blades between the sacrificial bottom of the soft capsule and a thrust ring. The high-strength ceramic is typically of a partially stabilized zirconia or hot pressed silicon nitride. The disposable capsule is typically of hexagonal boron nitride.

Abstract: The present invention is the use of stellite material for all contact surfaces between moving parts and a metering pump pumping silver photographic emulsion. All parts that are in contact with the solutions containing silver made of stellite will prevent failure of rotating assemblies due to metallic silver plateout between rotating parts. Prior art pumps exhibited silver plateout after very few hours of operation.

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 disclosure discloses a method for constructing a pumping installation which includes a prefabricated concrete pump house and a prefabricated concrete suction box. The pump house and suction box are then placed on and coupled to a workfloor manufactured at the building site. A pump is then installed in the pump house.

Abstract: An uncooled turbine outer air is comprised of a combination of monolithic ceramics with high temperature capability and oxidation and creep resistance, and a fiber reinforced ceramic composite with high fracture toughness. In a preferred embodiment of the invention, a fiber reinforced ceramic composite of silicon carbide and aluminum borosilicate is infiltrated by chemically vapor deposited silicon carbide. The infiltration process is continued until the composite develops a monolithic layer of silicon carbide. An additional layer is deposited on the monolithic ceramic to provide additional thermal protection.

Abstract: A turbine engine having an interior housing and one or more annular abradable seals for the turbine blades. The abradable seal comprises a resin having fractured hollow inorganic non-metallic microspheres forming nooks, crannies and undercuts in the resin and a solid lubricant in the resin and in the nooks and crannies and undercuts formed by the fractured hollow non-metallic inorganic microspheres.