Abstract: Blading for a turbo machine which facilitates manufacturing thereof.

Abstract: A circular array of rotatable blades formed from blades having an integral shroud with a leading planar surface and a trailing planar surface, the leading planar surface being generally parallel to an axial radial plane passing through the center of the root of the blade and the trailing planar surface, if extended, intersecting the axial radial plane passing through the center of the root of the blade to form an angle generally equal in degrees to 360 divided by the number of blades forming the circular array.

Abstract: A plurality of rotatable turbine blades are formed integral with a shroud and platform and a plurality of arcuate plate root portions which are received by circumferential grooves in a rotor and are fastened to the rotor by three pins extending axially through the root portions and the rotor, the shroud and platform portions having a protrusion on one corner to support the trailing edge of one of the blade portions and a notch in the shroud and the platform on the corner opposite the protrusion whereby the protrusions on one group of blades register with the notch on an adjacent group of blades when the groups of blades are disposed in a circular array on the rotor.

Abstract: There is described a fluid flow concentrating device suitable, for example, for concentrating the flow of tidal waters or of wind, which comprises a hollow body closed at one end and open at the other. The body has a fixed circumferential wall composed of a plurality of fixed spaced vanes and a nozzle located at the open end of the wall. Fluid moving from outside the device through the vanes to the inside of the body creates a vortex within the body and a fluid flow axially of the body through the nozzle. In certain preferred embodiments a turbine is located for rotation in a direction opposite to the direction of rotation of the vortex about a vertical axis, centrally within the nozzle downstream of the fluid flow. The turbine can be used to drive a generator or a motor to, for example, propel a marine craft, or, the augmentor can be used on a aircraft to assist the lift of a wing, or, in another application, can be used with a jet turbine engine to improve both the intake to and the thrust from the engine.

Abstract: An improved blade rotor structure for an axial flow turbine substantially reduces vibratory stress at resonant frequencies by rigidly connecting the blades to each other in groups equal in number to an integer multiple of the resonant frequency of the blades (i.e. a harmonic frequency) divided by the rotor running speed. Flexible tie means are used for connecting adjacent groups of blades together for substantially reducing axial-torsional vibration of the blades.

Abstract: Improved process and device for extracting energy present in a flowing fluid medium wherein a supported hub with propellers or blades is placed in said medium and the blades are provided with a wing or vane at the tip. The wing is of such a form that it generates a "venturi effect" in the flowing medium by which a part of the fluid which should normally pass outside the propeller disc area, is drawn into the propeller. The improvement consists of mixing of fluid which normally should pass outside the venturi with fluid which has flowed through the blades by provisions on blades and/or wing or vanes.

Abstract: A turbomachinery blade, which includes an airfoil and a projection from the airfoil for the purpose of abutting contact with the surface of an adjacent member is provided with a surface means having an improved combination of adhesive wear resistance and impact toughness through the attachment to the contact surface of a discreet wear pad. The pad comprises a substantially fully dense, compacted, sintered member of a material selected from carbides, nitrides and borides, with or without a suitable binder, the pad being of a thickness of at least about 0.01 inches and having thermal expansion characteristics compatible with the projection over the range of intended operating temperature.

Abstract: A device for interconnecting turbine blades comprises a pair of projections extending towards each other from the opposing sides of the tips of adjacent blades, having an inclined inward surface, and having a radially extending perforation. A cover piece has a pair of inclined outward surfaces conforming to the inward surfaces of the projections. The cover piece also has lugs extending through the perforations in the projections. One of the lugs has its end peened to form an overhang for abutting the projection. The perforation of the opposite projection is elongated to permit untwist of the turbine blades.

Abstract: A cantilevered structure comprises two cantilevers of unequal length adapted to span a gap (L) and overlap at their free ends so that load transfer may take place from the longer to the shorter cantilever. The cantilevers have the same Youngs Modulus, cross-sectional shape and same load per unit length applied to them, and the line of action of the load transfer between the cantilevers is up to 34% of the distance (L) between their encastres. The sum of the leading moments at the encastres of such cantilevers is lower than is the case with overlapping cantilevers where the line of action of load transfer between them is more than 34% of the distance between their encastres.

Abstract: A fan for use as a front fan or in the lift fan system with aircraft jet engines having blades supported by a segmented hub platform and a segmented tip platform which are supported by hub support hoops and tip support hoops. The blades are secured to the hub platform segments and tip platform segments by composite pre-preg pin stock which is inserted in holes in the tip platform, the hub platform and fan blades. The pins are placed under axial compression to expand the pin diameter to provide a precise fit. Channel members are provided between the tip hoops and the blades. Some of the channels have extensions which form seals.

Abstract: A blade structure for use in a fluid flow rotary machine wherein the blade profile is thickened within the head region and a cover plate is connected to the head end within the thickened region by means of a substantially loop-shaped welded joint which is made by use of a high-energy beam such as an electron beam applied to the surface of the cover plate. The starting and end portions of the welding run can be overlapped, and the intensity of the welding beam is gradually increased from the starting point of the run to eliminate any swelling effect and is gradually reduced towards the end of the run to prevent crater formation.

Abstract: A sealing bar is provided for each gap between adjacent shroud plates to form part of the coolant recovery system of an open-circuit, liquid-cooled gas turbine. The undersides of the edges of the shroud plates at each gap are chamfered and a small cylindrical bar is supported in the recess provided thereby. Centrifugal force urges the bar into sealing engagement with the chamfered surfaces.

Abstract: A blade or vane for a gas turbine engine has a cooled shroud made of two pieces, one of which is integral with the aerofoil and has formed on its surface distant from the aerofoil a plurality of convoluted grooves. The second piece overlays the first and closes the open faces of the grooves to form convoluted passages which are fed with cooling fluid from duct means.

Abstract: A propeller for a wind mill comprising a rotable supported hub with at least one mainly radially extending blade having a cross section in the shape of a "wing profile", each blade being provided with at least one auxiliary blade with a cross section in the shape of wing profile and being positioned such that said auxiliary blade will generate a "ventury effect" by which a part of the fluid, which normally should pass outside the propeller disc area, is drawn into the propeller.

Abstract: A rotor blade system which is adapted for long term reliable operation in a gas turbine engine is disclosed. Techniques for altering the natural frequency of the blade system to reduce the detrimental combined effects of external excitation and self-excitation are developed. One structure shown utilizes a shroud for the control of self-excitation in combination with a pin root to lower the fundamental first natural bending frequency of the blade system below the level of the 2E frequency at idle.

Abstract: A rotor for a turbine apparatus and method for fabricating the same. The rotor has a plurality of rotating blades mounted thereon subtended by a substantially annular shroud member. The shroud member is comprised of two axial segments joined along a circumferential seam. The segments have openings on their adjoining edges which are sized to accept a stem portion of a tenon integrally disposed on the radially outward tip of each rotating blade. The tenon stem has integral therewith a bulbous cap portion which, in the assembled state, simultaneously overlap circumferentially and axially the adjoined shroud segments. A circumferential groove is defined between the shroud segments and a suitable securing arrangement is provided in the groove to maintain the relationship between the axial shroud segments.

Abstract: A plurality of turbine buckets annularly arranged around a rotor are each provided with a ledge disposed at right angles to the outer surface of each bucket. Each ledge includes a leading end portion and a trailing end portion each formed therein with a vertical hole, leading and trailing end portions of the ledge of each turbine bucket extending in opposite directions on both sides of the bucket. There are provided cover pieces each interposed between ends of the adjacent two turbine buckets and formed on the upper surface with a plurality or cylindrical projections adapted to be loosely received in the vertical holes formed in the ledges of the adjacent two turbine buckets.

Abstract: A turbo machine rotor assembly which includes a turbine wheel having moving blade covers or connecting pieces connected to adjacent moving turbine blades. Each of the moving turbine blades includes a first ledge and second ledge at a leading edge and trailing edge side portions, respectively, of the tip of the blade with the first and second ledge portions extending substantially in tangential directions of the turbine wheel but in opposite directions to each other. One of the first and second ledges is provided with a through hole or aperture extending radially of the turbine wheel. The moving blade cover or connecting piece is provided with a pair of spaced pins receivable in the apertures of the first and second ledges for connecting the first ledge of one moving turbine blade and the second ledge of an adjacent moving turbine blade in such a manner that the upper surface of the cover contacts with the lower surfaces of the first and second ledges.

Abstract: A vibration, damper, or snubber device is disposed on the radially outward surface of a shroud member mounted on a turbine rotor. The rotor has an annular array of twisted blades connected together to form blade groups by a first and a second shroud member. The vibration damper, or snubber, is mounted on the first shroud member and extends therefrom across a gap between the shroud members to circumferentially overlap a portion of the second shroud member. A predetermined axial gap is defined between a portion of the second shroud and the snubber. When an untwist motion is imposed upon the blades due to rotation of the rotor, the axial gap closes and an abutment between the snubber and the second shroud occurs to inhibit further untwist motion and to simultaneously provide a friction interface to inhibit circumferential motion between the second shroud and the vibration damper.

Abstract: Continuous connection device for the mobile turbine blades of a turbo-mace, characterized in that the caps of the turbine blades comprise recesses accomodating clamping blades whose ends press against the neighbouring caps, becoming deformed elastically. The invention applies more particularly to elastic fluid turbines.