Abstract: A rotor disk for a gas turbine engine having an axis of rotation and an axial centerline is provided which includes a rim, forward and aft hubs, and forward and aft webs. The forward web extends between the rim and the forward hub, and the aft web extends between the rim and the aft hub. The forward and aft hubs are separated. Each web is skewed from the axial centerline. A circumferentially extending cavity is formed between the webs and the hubs.

Abstract: A turbine engine rotor assembly disk is provided which includes a forward web, an aft web, a plurality of first stub shafts, and a plurality of second stub shafts. The first and second stub shafts have axial ends and web ends. The stub shafts are attached to the respective forward or aft web, at the web end. The first and second stub shafts are equal in number, similarly spaced around the axial centerline, and attached to one another by fasteners.

Abstract: A blade support includes first and second abutting disks, with the first disk having a plurality of axial dovetail slots at one end thereof, and a circumferential dovetail first half-slot at an opposite end thereof, with the second disk having a circumferential dovetail second half-slot therein. A plurality of rotor blades have axial dovetails disposed in respective ones of the axial dovetail slots, and circumferential dovetails disposed in part in each of the first and second half-slots. The first and second disks are retained together so that the first and second half-slots collectively support the circumferential dovetails.

Abstract: A refrigerant or coolant compressor of the radial type with an impeller hng a plurality of vane elements can be used for compressing water vapor as a refrigerant or coolant under vacuum conditions. The impeller of the compressor is constructed to produce a high volume flow rate at the required compression ratio, in view of the low density of water vapor as the preferred flow medium. The impeller has sufficient strength to operate at the required high circumferential velocities. The impeller includes vane elements, disk elements, vane support elements and a hub. The vane elements are individually connected to the hub by the support elements. The support elements may be either ring-shaped elements connecting a rear surface of the disk elements to the hub, or may be pin-shaped insert members connecting the root of each vane element to the hub. The components of the impeller are made of a polymer composite material reinforced preferably with carbon fibers.

Abstract: A turbomachine rotor includes a disk having a plurality of annular ribs projecting from its periphery to define a plurality of annular grooves, and a plurality of blades, preferably made of composite material, evenly distributed around the periphery of the disk, each blade having a notched root defining heels which fit into the grooves of the disk and which are divided into two groups, one group being offset on the pressure side of the blade and the other group being offset on the suction side so that the heels of the second group align with the heels of the first group of an adjacent blade, the blades being fixed to the disk by pins which extend through the aligned heels of adjacent blades and the ribs of the disk. Each blade is thus secured by two pins, and each pin helps to secure two blades.

Abstract: A retainer ring is arranged to mount turbine blades to a turbine disk so that aerodynamic forces produced by a gas turbine engine are transferred from the turbine blades to the turbine disk to cause the turbine blades and turbine disk to rotate, but so that centrifugal forces of the turbine blades resulting from the rotation of the turbine blades and turbine disk are not transferred from the turbine blades to the turbine disk.

Abstract: Each of a pair of axially spaced turbine disks (12,14) has a plurality of blade retention fingers (20) at the periphery. Each blade has a pair of chevrons (64,66), one engaging a contiguous chevron (70) on a corresponding disk finger. The interacting chevron surfaces are located on the center plane (74) of a corresponding disk. Each finger is shaped to have a linear locus (75) of neutral axis (77) from the body of the disk to the chevron location. Each blade has a hollow platform structure (24), structural members (86,88,92,94) associated with a chevron (70), an airfoil extension (63) extending through the platform (28). High temperature cooling air (34) is directed into the blades (32,26,22) while being baffled away (42) from the turbine disks (12,14). Low temperature cooling air (48) bathes the live disks.

Abstract: The invention relates to a connection system for connecting a ring which carries aircraft propeller blades to a turbine which the ring surrounds. Brackets extend between the ring and the turbine and accommodate thermal expansion of the turbine without significant deformation.

Abstract: The present invention relates to a fastening spindle and a method of attaching the rotor elements together utilizing the spindle. The system according to the invention reliably permits the visual inspection of the rotor assembly and to determine if it is properly tightened without the need for any additional post assembly inspection. The fastening spindle according to the invention has a central portion having a generally oblong cross-section with a first, major transverse dimension d.sub.1 which is greater than a second, minor transverse dimension d.sub.2 ; a first cylindrical portion which extends from the central portion in a first direction, the first cylindrical portion having a threaded distal end and a diameter d.sub.3 such the d.sub.3 is less than d.sub.2 ; and a second cylindrical portion extending from the central portion in a second direction, the second cylindrical portion having a threaded distal end and a diameter d.sub.4 such that d.sub.4 is less than d.sub.2.

Abstract: A turbine plant compressor disc is formed from two halves which are welded together near the rim and define an internal cavity in which a centripetal accelerator is mounted for inducing cooling air to flow from the compressor through inclined passages in the rim on the downstream side of the blades carried by the rim, through the cavity of the disc, and towards the turbine to be cooled in the vicinity of the turbine shaft. The centripetal accelerator is composed of sectors which are removably mounted in the cavity of the disc, the sectors forming a perforated ring disposed in the central bore of the disc and each sector having a flat web extending radially outwards in the inner cavity of the disc to form radial centripetal channels communicating with the air passages in the rim.

Abstract: A rotor blade 14 having a spar 138 and shell 134 is disclosed. Various construction details are developed for efficiently transferring rotational loads on the rotor blade to the root section 28 of the spar. The spar has a projection 139 over which extends a portion 100 of the shell and a platform 36 of the rotor blade.

Abstract: An improved rotor for fluid flow meters having a rotor hub with a vane hub mounted thereon including spaced inner and outer cylindrical walls. These inner and outer cylindrical walls are provided with grooves and slot respectively that are radially aligned and which are inclined relative to the direction of fluid flow and provide adjacent support surfaces for a plurality of vanes. A cap element assembled on one end of the rotor hub in engagement with the outer cylindrical wall maintains the vanes in operating position and provides a means whereby the vanes can be readily removed or replaced when desired.

Abstract: A rotor for axial-flow turbomachines with a locking pin connection for the blade roots. The blade roots are suspended in fiber-reinforced retaining rings and evidence cylindrical circumferential surfaces at their lower side. These cylindrical surfaces contact a correspondingly conformed circumferential surface on the metallic rotor disc.

Abstract: A centripetal turbine rotor has ceramic blades with integral blade roots of arcuate axial section which are clamped axially between two supporting elements mounted on a common shaft so that the ceramic blade roots are maintained in compressive stress along their arcuate, radially inwardly convex, profiles, opposing centrifugal strain in the blade roots.Cooling air may be supplied along axial channels in one hub to an internal chamber within the blade roots and may thence flow outwardly into the gases flowing through the turbine.

Abstract: A hub assembly for a centrifugal fan subjected to large transient thermal stresses is provided in which a pair of opposed hubs sandwich the inner peripheral margin of a disc-shaped fan plate, with the inner peripheral margin of the plate including a thickened ring portion to provide oppositely projecting annular shoulders at the outer periphery of the thickened ring portion, with the opposing hubs having annular recesses to receive the thickened ring portion and with the outer peripheries of the recesses in closely abutting relation with the shoulders to provide a shoulder-recess bearing area and with a plurality of fastener means extending through the hubs and through the thickened ring portion so that the shoulder-recess bearing area, which is located radially outwardly from the bearing stress areas at the bolt holes, largely receives the transient thermal stresses and therefore reduces the stress in the bolts and plate.

Abstract: A radial turbine wheel for a gas turbine which consists of two parts and more particularly of a first part adjoining the turbine inlet which includes the outer sections of the blades and of a second part leading to the turbine outlet which includes the inner essentially curved section of the blades whereby the two parts are made of materials having different properties.

Abstract: A rotor-shaft assembly comprising a ceramic turbine rotor, a metal shaft and a metal connector disposed between the rotor and the shaft. The metal connector is fixed to the rotor by some suitable means and coupled with the metal shaft by mutual engagement of teeth provided at the ends of the connector and the shaft.

Abstract: A rotatable disc comprising a plurality of generally parallel plates tightly joined together for rotation about a hub. Each plate is provided with a plurality of angularly spaced lands projecting from a face thereof, the lands of each plate interposed in alternating relationship between the lands of the next adjacent plate. In this manner, circumferential displacement of adjacent sectors in any one plate is prevented in the event that a crack develops therein. Each plate is redundantly sized such that, in event of structural failure of one plate, the remaining plates can support a proportionate share of the load of the failed plate. In one embodiment, the plates are prevented from separating laterally through the inclusion of generally radially extending splines which are inserted to interlock cooperating, circumferentially adjacent lands.

Abstract: A device for the torque-transmissive securing of a disc which is formed of a brittle material, in particular a turbine wheel constituted of a ceramic material, onto a shaft. The disc is centered through the intermediary of two cone pairs with axial prestressing and the torque is transmitted to the shaft through a cylindrical extension of the wheel hub with longitudinal grooves formed on the outer circumference thereof; furthermore transmitted by means of a cylindrical bellshaped cover with symmetrically profiled longitudinal connectors in an inner bore which are conformed to the longitudinal grooves, and finally by rollers located between the concave side edges or slopes and the side walls of the longitudinal grooves in radial and tangential contact therewith, by means of the bell-shaped cover which is rigidly fixed on the shaft.

Abstract: A rotor wheel including a hub in the form of a thin-walled shell. Rotor blades are arranged in an annular pattern around the axis of the hub, each blade having at least one blade root formed with a hole. A pin extends through the hole in each blade root, and at least one retaining ring coaxial with the hub axis surrounds all the pins and absorbs radial forces produced by the blades on the pins when the rotor wheel rotates. The retaining rings and blades are fixed against axial and circumferential movement with respect to the hub. A segment between each pin and retaining ring distributes the forces of the pin to the retaining ring. The pins are mounted for radial movement with respect to the hub, and one of the mounting parts for said pins may be detachable from the hub. The hub may be dish shaped, and the pins secured at only one end to the peripheral wall of the hub, that wall having axial slots so that it may expand radially.

Abstract: A bore vane assembly is adapted to be received within the annular passage formed between two axially displaced turbine disc halves so as to provide axial columnar support therebetween during high centrifugal loading. The bore vane assembly includes a plurality of axially extending vanes which provide the required support and which also serve to pump cooling fluid from a plenum into the turbine disc.

Abstract: A runner hub for a propeller type hydraulic turbine wherein the hub is constructed of at least a pair of arcuate segments. When the arcuate segments are assembled together, they form a hollow hub. Turnbuckles are provided within the hub attached to opposite hub segments and are adjustable to forcibly hold the hub segments in the assembled position.

Abstract: A fan blade and root assembly is disclosed for use in a hot gas engine requiring low weight and high efficiency. The root construction facilitates simple sheet metal stamping fabrication throughout the blade, root, and hub while permitting an air foil shape to be imported to the blade.

Abstract: The parts of a gas turbine plant exposed to the highest temperature are made of ceramic material and are mounted by resilient clamping members permitting freedom for thermal movements. These clamping members are located in passages between spaces containing air and gas, respectively, with the air having the higher pressure. The clamping members are slotted to permit the flow of air through the passages in which they are mounted and will thus be effectively cooled.

Abstract: In a rotor assembly, first and second annular discs are axially spaced apart on a rotatable shaft so as to be rotatable with the shaft. A plurality of rotor blades are located between the discs and are angularly spaced around the axis of the shaft, and means urges the discs against the blades so that a root portion of each blade is trapped between the discs with the remainder of the blade projecting from the discs. Each root portion is shaped so as to be non-complementary with the portions of the discs between which it is trapped, and each disc is shaped so as to present to each root portion first and second surfaces which, when the shaft is rotated in use, engage respective spaced regions of the root portion so that the root portion is held against axial movement relative to the shaft and against movement radially outwardly relative to the axis of the shaft.