Abstract: A multiple number of rotatable, axial flow turbine blades having a common platform and shroud portion from which two arcuately separated, axially extending, side entry roots protrude radially inwardly toward the axis of rotation of a rotatable shaft.

Abstract: A rotor blade for a gas turbine engine comprises an aerofoil, an inner platform and a root portion. In order to restrain the movement of the blade should it become detached from its rotor, the platform has an indentation in that edge adjacent the convex flank. If the blade detaches, this indentation engages with the leading edge of the next adjacent blade in the row, tending to restrict motion of the detached blade to the radial plane.

Abstract: The present invention provides an assembly for mounting a row of ceramic rotor blades in the metal rotor disc of a gas turbine engine. The major components of the assembly comprise a well known ferritic metal rotor disc in which is mounted, in a conventional fir-tree root configuration, a plurality of high temperature metal alloy or super alloy intermediate members forming an annular array thereof and defining "dog-bone" shaped axial grooves in the annular face for receipt of a complementary "dog-bone" or single serration root of a ceramic blade for mounting an annular array of ceramic blades. The root shank portion and the air foil portion of the blade are separated by a platform and centrifugal-force pins are inserted between adjacent platforms to fix the blade against low frequency vibration and to seal the gap therebetween against leakage of the motive fluid into the root area.

Abstract: An interblade seal and vibration damper to be positioned in the damper cavity defined between a rotor disc, adjacent blades and adjacent blade platforms so as to seal across an interplatform gap by providing line contact between the damper and the platforms on opposite sides thereof for the full axial dimension of the cavity and with the damper shaped so as to have a low center of gravity for operational stability and which damper also responds to centrifugal force during rotor operation to establish damping friction between said damper and said platforms when the platforms move circumferentially.

Abstract: Improved attachment structure for connecting ceramic blades to the rotor disk of a gas turbine rotor. The structure includes a plurality of metallic attachment pieces having roots inserted into respective grooves in the outer periphery of the rotor disk. Each attachment piece has an outer peripheral groove for receiving the root of a corresponding turbine blade formed of ceramic material. Specific embodiments of an attachment piece and a blade are disclosed, the blade having a base which engages the outer peripheral face of the corresponding attachment piece. The blade base and the corresponding attachment piece have aligned, spaced grooves at the opposed ends thereof for receiving ceramic plates which cover the adjacent parts of the attachment piece. Certain ends of the ceramic plates define recesses for receiving metallic plates which extend radially of the rotor disk and transmit torque from the blade to the attachment piece and thereby to the rotor disk.

Abstract: A turbine rotor having a number of metallic attachment pieces for coupling a plurality of ceramic blades to a metallic rotor disk. The blades have roots which are received within grooves formed in the attachment pieces. Each attachment piece has passage means therethrough cooperating with passages in the rotor disk for receiving a coolant for cooling the attachment pieces without causing the coolant to contact the ceramic blades. The attachment pieces keep the rotor disk isolated from the hot gases which contact the ceramic blades.

Abstract: A coverplate damping arrangement is provided for a turbine assembly wherein a sealing and damping pin which extends between and under adjacent bucket platforms is formed with one or more eccentric masses which cause the pin, under the urging of centrifugal force, to rotate into abutment with the coverplate.

Abstract: An improved rotor for a gas turbine engine wherein the rotor has a plurality of ceramic turbine blades coupled by attachment pieces of high-temperature metal to a rotor disk. Each attachment piece has a root received in a corresponding groove in the outer periphery of the rotor disk. Also, each attachment piece is made to couple a pair of turbine blades to the rotor disk, the attachment piece having a pair of axially spaced, radially extending walls, each wall having a hole therethrough and the holes of the walls being aligned with each other. The roots of the two blades for each attachment piece are positioned between its spaced wall and the roots have cooperating projecting parts which engage each other and form a recess through which a pin extends when the ends of the pin are in the holes of the end walls. The roots of the blades of adjacent attachment pieces abut each other to keep the blades from moving laterally relative to respective attachment pieces.

Abstract: A turbine wheel including blades and rim made in one piece, a notch in the peripheral surface of the rim between each two successive blades, and a through-hole in the rim radially inwardly of and parallel to each notch. The through-holes permit cooling air to flow from one side of the turbine wheel to the other. Each through hole is spaced closely to its respective notch to define a narrow rated breaking point between the two. The through-holes may be of circular, oval, or elliptical cross-sectional shape. A tubular baffle is arranged in each through-hole, the baffle being open at one end to receive cooling air, but the other end of the baffle being blocked. The wall of the baffle is perforated. Longitudinally-extending webs may support each baffle in spaced relation to the wall of the through hole. Annular plates may be arranged over opposite sides of the wheel to define air flow openings to and exhaust openings from the through-holes.

Abstract: A rotor apparatus comprising a blade having a root adapted to swing laterally within a supporting spindle under impact loading is provided with a flow path defining platform. The platform comprises an inner shroud extending generally laterally of the blade airfoil portion and adapted to swing laterally therewith. In one embodiment wherein the blade primarily comprises a laminate of composite filament plies, the inner shroud is bonded to the laminate. An outer shroud, fixed with respect to the supporting spindle, forms a lateral extension of the inner shroud with the blade in its normal operating position. The inner and outer shrouds are provided with a pair of complementary adjacent surfaces contoured to pass in relatively close-fitting relationship to each other when the blade swings under impact loadings.

Abstract: The disclosure of this invention pertains to a bladed rotor for gas turbine engines wherein each blade has a root portion connected to a blade support element spaced radially outwardly from the rim of a single disc and being of greater axial extent than the rim. The element is connected to the rim by a web extending in part radially outside the rim and in part at the sides of the rim.

Abstract: A bladed rotor having blade slots in the periphery and peripheral lands between the slots, has a row of blades positioned in the slots with laterally extending platforms on the blades overlying the lands, the circumferential space between the outer edges of adjacent platforms, which space is radially outward of the associated lands, is closed by a flexible thin seal held axially and circumferentially in position under the space between the platforms.

Abstract: A turbomachinery blade platform comprising a pair of complementary platform halves, each having an outer flow path defining shroud adapted to extend generally laterally of the blade. An inner flange on each platform half, also extending generally laterally of the blade, is retained in a cooperating slot formed within the support structure retaining the blade. A structural member extending between the shroud and the flange is contoured to conform to an overlapping wedging surface disposed about the blade airfoil surface. The platform is thus provided with redundant retention by both the blade and by the blade support structure.

Abstract: A turbine blade has a hole through the blade stalk and a controlled area in the stalk cross section on each side of the hole to assure that the blade will separate at the stalk upon overspeed of the turbine wheel. The hole is drilled and reamed and the hole surface is finally machined by chemical milling to eliminate stress risers while maintaining a controlled cross-sectional area to ensure that with selected wheel and blade materials, the blades will separate and reduce the speed of the turbine wheel.

Abstract: A rotor for an axial flow, elastic fluid turbine apparatus. The rotor has a rotating shaft having a plurality of circumferentially spaced rotating blades thereon. Each blade has a platform portion having a convex arcuate surface and a concave arcuate surface. The convex arcuate surface has a radius greater than the radius of the concave arcuate surface.

Abstract: In an axial flow compressor rotor stage having a tangential slot in the periphery of the rotor to receive the blade roots, a seal is positioned below the blade platforms to seal these platforms against air recirculation. The seal extends under the platforms of several blades and is ladder shaped with the rungs sealing the platform spaces and the struts serving to interconnect and hold the rungs in place.

Abstract: A locking mechanism for preventing axial movement of side entry buckets mounted upon a rotor disc. The locking mechanism includes a pin loosely supported within a disc tang, the pin having a recessed shoulder arranged to abut against the platform of a first bucket and an extended section arranged to be received in a complementary slot formed in the platform of the next adjacent bucket. A further mechanism is provided for preloading the pin against the buckets whereby the dampening characteristics of the system are enhanced and balancing of the buckets is facilitated.