Abstract: A hollow composite airfoil with an integral internal support rib of fluoroelastomer rubber is formed by bracketing the rib between two silicone rubber mandrels to form a core assembly having a desired aerodynamic shape, then building up on opposite sides of the core assembly separate stacks of laminae of a composite material of graphite (or carbon) and glass fibers impregnated with an epoxy resin, with the two stacks overlapping adjacent to the leading and trailing edges of the core assembly. Heat and pressure are then applied to the core assembly with the laminae thereon to bond together the laminae of each stack, then to bond the two stacks together along the overlapping portions thereof and to bond the two stacks to the rib to form a continuous shell around the core assembly. The mandrels are then removed. One open end of the resulting hollow airfoil is plugged and that end is inserted into a recess in a mounting platform with a predetermined clearance space therebetween.

Abstract: The present invention provides a method for constructing from fiber-composite material complex structures having two or more transversely disposed members. By way of example, a composite turbine blade 10 having an aerofoil 12 and an integrally formed footing 14 can be constructed using this new method, which method comprises the steps of forming from fiber-composite monotape a blank 40 in the general shape of aerofoil 12 with the fibers 18' of the monotape being oriented in a generally spanwise direction, exposing the fibers 18' at the root 42 of the aerofoil blank 40, inserting transversely between the exposed fibers 18' a plurality of foot-forming monotapes 17 to form a transversely meshed, tape and fiber structure 68, filling the voids in the transversely meshed structure with powdered matrix material and hot-pressing the filled-in structure 70 substantially according to the desired final shape of the fiber-composite turbine blade.

Abstract: In the manufacture of an article of ceramic material, for example a bladed turbine wheel of silicon nitride, there is first formed a plurality of article parts, at least one of which is a shaped powder body formed from powder of ceramic material mixed with a plasticizer, after which the plasticizer is driven off by a suitable heating operation. The article parts are then assembled together into a configuration conforming to that of the article to be manufactured, and the assembled article parts are surrounded with a gas-impermeable layer, for example a layer of glass. Finally, the assembled parts are isostatically pressed at elevated temperature to form the assembled article parts into a dense, homogeneous article.

Abstract: A gas turbine blade in which are provided inter alia two chambers for the circulation of cooling fluid, lying in proximity to the leading and trailing edges of the blade respectively, two conduits disposed respectively between the first chamber and the leading edge and between the second chamber and the trailing edge, and apertures connecting each conduit to the chamber nearest to it. The blade is produced by diffusion-brazing two half-blades together. The chambers are formed in part in one, and in part in the other, half blade. In order to produce the conduits and apertures by means of grooves engraved in the facing surface of the two half blades, the interface of the two half-blades divides said conduits and apertures in two.

Abstract: A blade for a fluid flow engine, especially a gas turbine, has a protective coating against injurious attack by the propellant or working medium. A metal blade having a diffusion layer or a sprayed coating for inhibiting corrosion is known. Such coating renders the blade highly resistant against heavily erosive and corrosive attack, especially by pulverized coal combustion gas or similar agents. The present blade is made of ceramic material, especially a dense ceramic material with a surface layer of at least one of the following materials: TiN, TiC, B.sub.4 C, BN and titanium carbon nitride. These materials are easy to apply and provide a good bond with the ceramic material. If the ceramic materials are silicon carbide (SiC) or silicon nitride (Si.sub.3 N.sub.4) an especially good bond is achieved. This coating strongly resists removal, as it does oxidation and heat. Local removal down to the ceramic material, as it may result from rather long service, is recognizable immediately.

Abstract: The top portion of a composite (boron filament/aluminum matrix) blade which is useable in a fluid flow machine is made more resistant to impact energy by forming a cavity in the boron filament layer of the tip portion of each laminate (or ply) of the blade, then filling each cavity with a resin, and then bonding together the laminates with the resin-filled cavities therein.

Abstract: A rotor blade, for example for a windmill, comprises a plurality of blade ctions between a blade root and a tip. The sections are interconnected by tensioning members such as steel cables or the like, preferably extending through the blade sections. Thus, each section may be manufactured individually and all components may be assembled at the construction site, whereby relatively large windmill rotors may be constructed.

Abstract: A turbofan engine fan blade made of composite material, and a method of making the fan, are taught. The fan blade essentially comprises an airfoil section having a root end and made of a plurality of bonded plies of composite material which are splayed and which are in a staggered condition at the root end; a two-piece platform section made of titanium or of aluminum, with one piece of the platform on each side of the airfoil section; and a steel outsert section which holds and secures the platform section to the airfoil section, with the outsert section having a triangular shaped cavity located at the root end of the airfoil section, between the splayed and staggered plies of the airfoil section. Among other advantages, the cavity eliminates the "insert plies" (or wedge) used in the prior art and the inherent disadvantages associated with such use.

Abstract: A considerable increase of the life time of metallic members, particularly the blades of fans or turbines, which are exposed to air-borne abrasive particles is obtained by providing such members with a wear-resisting attachment comprising at least two wear-resisting layers consisting of materials having complementary relationships of the erosion caused by said abrasive particles to the impact angle of the particles, said attachment being applied to surface portions of the members to be protected.

Abstract: A blade or vane for a gas turbine has a cambered aerofoil made up of a plurality of single crystals of an alloy. Each crystal extends longitudinally of the aerofoil and has a predetermined three-dimensional orientation different from that of the other crystals such that it has an optimum value of a chosen property in directions longitudinal and transverse of the aerofoil.

Abstract: Improved structure and method for an internally cooled, laminated stator or turbine blade for turbomachinery includes internal cooling passage configurations within each lamina which promote different forms of cooling of the internal or external surfaces of the blade.

Abstract: A power producing constant speed rotary turbine in which an elongate shaft is rotatably supported in longitudinally spaced, axially aligned first and second housings that have a housing assembly disposed thereinbetween. The first housing rotatably supports a power take-off that is driven by a series of reduction gears operatively connected to the shaft. The second housing envelops an output power turbine rotor defined by a series of thin, circular, coaxially aligned, laterally spaced discs of high temperature metals or high temperature ceramic such as hot pressed silicon nitride that are operatively connected to the shaft.A compressor rotor is mounted in an intermediate position on the shaft and rotates within the housing assembly, which assembly has an air inlet therein. As the compressor rotor rotates in the housing assembly, air is discharged to first and second groups of diffuser tubes that extend to first and second volute casings.

Abstract: A design technique, method and apparatus for containing failure of the rotors of axial flow fluid machines. A rotor disk is constructed of at least three disk sections. Each disk section is shaped such that the loading on that section will be distributed in an optimum manner from the rim to the hub of the disk. To prevent crack propagation from one disk section to another, and to minimize structural weaknesses in the disk sections, the live disk sections are bolted together in a single bolt circle. In order to reduce overall disk weight while maintaining a maximum level of failure containment, the inner disc sections are made thicker than the outer disk sections. Embodiments for the fan, compressor and turbine rotor sections of a gas turbine engine are disclosed.

Abstract: The subject rotor comprises a disklike body having hub and rim sections joined by a web section. The body is cast, molded or otherwise suitably formed of powdered silicon (and a binder, if necessary, to make it retain its shape until finally treated) which is reaction bonded to convert the silicon particles into a unitary mass. During the casting, molding or other forming step, one or more reinforcing rings of hot pressed silicon nitride or other suitable ceramic are embedded in the body. The ceramic selected must be one which will unite with the silicon during the reaction bonding operation to make a unitary mass. The reinforcing ring or rings are located in regions exposed to unusual stress in the use of the rotor to achieve the required strength.

Abstract: An axial flow elastic fluid turbine apparatus includes a rotor having an annular array of circumferentially spaced blades. A casing encircles the rotor and an annular array of circumferentially spaced stationary nozzle blades is fastened the casing and arranged to direct the elastic fluid against the blades of the rotor. An outer covering is disposed over the radially outermost half of at least one blade of the stationary array and a thermal insulating member is disposed between the surface of the blade and the outer covering. Electric heating means are provided for raising the temperature of the outer covering to the Leidenfrost point, i.e., the point at which the temperature of the covering exceeds the vaporization temperature of the elastic fluid corresponding to the prevailing ambient pressure by more than 200.degree. C., to evaporate water droplets which collect on the stationary blade and to prevent the accumulation of relatively smaller water droplets on the stationary blade.

Abstract: A turbine blade having a porous hollow sheet metal airfoil and a base defining a platform, stalk, and root. The airfoil portion is integral with an extension which lies within the blade stalk, the base being cast around this extension. The cast metal lies around the blade wall and also through tubes welded from wall to wall of the extension. The stalk also includes an opening to admit air to the interior of the blade for transpiration through the blade wall.