Abstract: A fan rotor assembly (30) for a gas turbine engine (10) comprises a fan rotor (32) and a plurality of radially extending fan blades (34). Each fan blade (34) has a root (64) which is retained in a corresponding groove (54) in the periphery of the hub (54) of the fan rotor (32). Each fan blade root (64) comprises four axially spaced root portions (66, 68, 70 and 72) which locate in a corresponding number of axially spaced groove portions (56, 58, 60 and 62). The flanks (94, 98) of two of the root portions (66, 70) are arranged at an angle to the axis of the fan rotor (32) and the flanks (96, 100) of the other two root portions (68, 72) are arranged at an angle in the opposite sense. The flanks (74, 76, 78 and 80) of the groove portions (56, 58, 60 and 62) are arranged at the same angle as the flanks (94, 96, 98 and 100) of the corresponding root portions (66, 68, 70 and 72). The arrangement provides improved retention of the fan blades (34) and reduces the weight of the fan blades (34) and fan rotor (32).

Abstract: A steam turbine different material welded rotor, constructed by rotors of different materials being jointed together by welding has the strength of a jointed portion increased and inspection of the jointed portion facilitated. A bearing portion rotor 1 and high temperature portion rotor 2 are jointed at weld portion A, the high temperature portion rotor 2 and low temperature portion rotor 3 at weld portion B and the low temperature portion rotor 3 and bearing portion rotor 4 at weld portion C. Cavity portions 5, 6 are formed in the weld portions B, C, respectively. Inspection holes 7, 8 are also provided in the weld portions B, C. The high temperature portion rotor 2 is made of high heat resistant 12Cr steel and other rotors are made of low alloy steel, wherein the rotor 1 is of 2.multidot.1/4 CrMoV steel and the rotors 3, 4 are of 3.multidot.1/2 NiCrMoV steel.

Abstract: In a turbine rotor, a thermal mismatch between various component parts of the rotor occurs particularly during transient operations such as shutdown and startup. A thermal medium flows past and heats or cools one part of the turbine which may have a deleterious thermal mismatch with another part. By passively controlling the flow of cooling medium past the one part in response to relative movement of thermally responsive parts of the turbine, the flow of thermal medium along the flow path can be regulated to increase or reduce the flow, thereby to regulate the temperature of the one part to maintain the thermal mismatch within predetermined limits.

Abstract: An integrated fan and low pressure compressor rotor having a hub with a circumferential array of primary blades. Each primary blade has a forward fan blade portion housed in the engine inlet radially extending from the hub to the fan case and a rearward compressor blade portion housed in the core duct radially extending from the hub to the intermediate case. The fan blade portion and compressor blade portion have aerodynamically aligned lateral airfoil surfaces and platforms such that the fan blade portion and compressor blade portion have continuously merged lateral airfoil surfaces and platforms. The integrated rotor replaces two conventional rotors resulting in cost savings.

Abstract: A seal device between a fastening bolt and a bolthole in a gas turbine disc reduces cooling steam leaking from a gap between the fastening bolt and the bolthole. A gas turbine disc 31 carrying moving blades, a fastening bolt 33 for fixing the disc 31 passes through a bolthole 32. On a low pressure side of the disc 31, a bolthole diameter enlarged portion 39 having a larger diameter than that of the bolthole 32 is provided. Fastening bolt 33 is provided with a shaft diameter enlarged portion 33a. Seal piece 1 is fitted at one end around the shaft diameter enlarged portion 33a and is engaged at the other end with a stepped portion of the bolthole diameter enlarged portion 39. In operation of the gas turbine, the bolt 33 is biased outwardly be centrifugal force, and the gap between the bolt 33 and the bolthole 32 deforms. Nevertheless, the seal piece 1, having flexibility, deforms at bent portions R.sub.1 and R.sub.

Abstract: This invention provides a compact, flat axial fan which is not limited by the shape of an incorporated rotor magnet and ensures a sufficiently large air flow and wind pressure, wherein the slide (under) piece of a mold that forms the under-molding portions of the vanes of the impeller of the axial fan is pulled out while being twisted (while performing a helical motion) in the direction of central axis of the base portion of the impeller, so that the mold can be formed simple to realize a multi-cavity mold, and the vanes can be formed into an ideal form by setting vane angles depending on different rotating peripheral velocities of the vanes, so that air can be supplied form the under-molding portions of the vanes to the vanes on the outer circumferential side during rotation of the impeller and a method of manufacturing an impeller for the axial fan.

Abstract: A turbine 400 has a central duct 410 which accelerates fluid passing through it and a blade configuration which retards the flow of fluid near the tips of the turbine. This structure results in a vortex having a higher fluid pressure behind the tips of the turbine blades 408 and a lower fluid pressure behind the duct. In the present invention, this vortex is enhanced by (1) an increased acceleration of the fluid passing through the duct 410 and a deceleration of the fluid passing through the blades 408; and/or (2) by a fluid redirection device 850 for directing the fluid passing through the duct towards the outer diameter of the turbine.

Abstract: A compressor for a gas turbine, comprises a rotor including a plurality of rotor parts, and blades for a plurality of stages, e.g., twelve stages, implanted in the rotor parts, the rotor part in which the blades for at least two of the stages are implanted is made of a Ni--Cr--Mo--V low alloy steel, and the Ni--Cr--Mo--V low alloy steel has substantially an entire bainite microstructure comprising, in weight percent, C of 0.15-0.40%, Si not more than 0.1%, Mn not more than 0.5%, Ni of 1.5-2.5%, Cr of 0.8-2.5%, Mo of 0.8-2.0%, V of 0.1-0.35% and the balance being substantially Fe. Blades for at least two of the stages are implanted in one of the rotor parts.

Abstract: A baffle plate (12A) is constructed such that two belt-like elements, bent in a warped arc, are joined by spot welding (13) or brazing (14) at a central portion thereof along a central circumferential portion. Thus, even if there is a difference in a radial directional deflection of grooves (11) between adjacent discs (9), the baffle plate (12A) will maintain close contact with the inner surfaces of the grooves (11) due to a spring effect and gas leakage is thereby prevented.

Abstract: A gas turbine has a gas turbine rotor including a plurality of rotary disks each having an opening of a circular shape formed through its central portion, the rotary disk including a pair of hub portions formed respectively on opposite sides thereof, and a pair of in-low portions formed respectively at the opposite sides thereof. The gas turbine rotor also includes a plurality of spacers each having an opening of a circular shape formed through its central portion, the spacer having a pair of in-low portions formed respectively at opposite sides thereof. The rotary disks and the spacers are alternately stacked together in such a manner that the opposite sides of each of the spacers contact opposed side surfaces of the adjacent hub portions, respectively, and that the in-low portions of each of the spacers are engaged respectively with the in-low portions of the adjacent rotary disks. The stack of rotary disks and spacers are fastened together in an axial direction by stacking bolts.

Abstract: A fan blade assembly having a plurality of arranged about a central hub having an axis of rotation, the blades projecting from the hub radially outward from the axis of rotation. Each blade has a blade length, with a proximal end attached to the central hub and a distal end radially outward from the central hub. The assembly has at least one vane member with a plurality of vane segments, each vane segment joining a first blade with an adjacent second blade at a place along the blade length located radially inward from the distal end and radially outward from the proximal end of the blades. The assembly further having a plurality of recesses in the central hub adapted to receive the proximal end of blades of an adjacent blade assembly to permit stacking of like assemblies.

Abstract: Power generation turbines having different power outputs for different power grid frequency applications have modular second and third stages, rotors, bucket wheels for all stages and other ancillary parts. The first and second turbines have sizes not geometrically scaled according to speed. Four-stage turbines having different outputs for different power grid frequencies not geometrically scaled have an identical annulus through the first, second and third stages, different geometry in the first and fourth stages, and identical geometry in the second and third stages.

Abstract: The span of the overhung flanges at the rim of the disks of gas turbine engine's compressors are minimized by slotting the one of the adjacent flanges at the distal end to receive the bolt head of the attaching bolt and including an anti-rotational clip allowing the nut to be fastened without the necessity of holding the bolt head. The complementing flange of the adjacent rotor includes mating holes. The anti-rotational clip includes bendable tangs bent in situ to engage the flats of the bolt head and a bent tang to fit snugly into the when radially inserted therein slot.

Abstract: An HP module for a turbine having a drum rotor with admission for steam having very high pressure and temperature characteristics comprises zones of different designs that are suitable for different temperature and pressure levels. An anterior zone A is at the steam admission end and includes a rotor assembly, diaphragms, an internal body, and an admission baffle carrier all of which are fully isotrophic, without any break in a horizontal join plane. A posterior zone P situated at the exhaust end has its internal body implemented in the form of two portions which are coupled to the internal body of the zone A. The internal body of the zone P may be isotropic and banded or it may be non-isotropic or it may be bolted. In the zone A the blades are mounted either in axial grooves or else in circumferential grooves, whereas in the zone P, the grooves are selected to be circumferential for simplification purposes.

Abstract: An interstage thermal shield assembly for a gas turbine engine. The assembly includes an axially-extending thermal shield positioned between first and second stage disks to form a seal therebetween. The thermal shield includes complementary hook members shaped to engage slotted hook members formed on the first stage disk to form a bayonet connection, and complementary lip members for engaging lobe members formed on the second stage disk by means of split rings, thereby eliminating the need for a bolted connection between the thermal shield and disks and facilitating attachment and removal of the thermal shield. The thermal shield includes an annular impeller which is positioned rearwardly of the first stage disk, the impeller including bayonet connection with the disk which restrains the impeller from axial deflection, but permits radial deflection in response to thermal changes.

Abstract: A turbine assembly includes a unitary rotor spool having first and second rotor discs. A set of first blades having axial entry dovetails are joined to the first disc, and a set of second blades having axial entry dovetails are joined to the second disc. A unitary annular spacer is disposed axially between the first and second dovetails for preventing the first and second blades from sliding axially toward the spacer. The spacer has an inner diameter greater than an outer diameter of the first rotor disc for allowing the spacer to be assembled over the first rotor disc during assembly.

Abstract: To reduce engine exhaust gas pressure behind a motorboat propeller formed with a boss for educing engine exhaust gas therethrough, without forming a trumpet-shaped boss end and without allowing exhaust gas to flow upstream along the boss outer surface, a single or plural small subblades are provided between two adjacent large main blades at such a position that a positive pressure domain produced by the subblade reduces a negative pressure domain produced by the main blade. Since engine exhaust gas can be effectively educed, engine power increases and therefore motorboat acceleration performance can be improved.

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 fan rotor assembly having decreased susceptibility to vibratory damage is disclosed. In one embodiment described the rotor assembly includes a plurality of principal fan blades 22 and a plurality of secondary fan blades 36 associated therewith. The secondary blades are coextensive with the principal fan blades over the inner portion of the principal blade span.

Abstract: A turbine rotor has a shaft, a plurality of wheel discs shrunk-fit on said shaft along the axial direction thereof, said wheel discs being provided with blades on the outer circumference thereof. A plurality of coupling members are disposed between the wheel discs except the ones disposed most downstream, for coupling the wheel discs to each other. At least one coupling means is disposed between the wheel disc disposed most downstream of the shaft.

Abstract: A steam turbine rotor includes a plurality of turbine wheels secured to a shaft by an interference shrink fit between each wheel and a corresponding step surface on the shaft. The step surfaces have decreasing radii over a portion of the axial length of the shaft. Each wheel incudes a hub section proximate the shaft and each hub section has a shoulder portion of greater radial dimension than the radially innermost surface of the hub section. A member or finger protrudes from one shoulder and mates with a longitudinal slot on one of the step surfaces of the shaft. Relief grooves are also provided for on the shaft and hub section.

Abstract: A turbine rotor provided with a sealing member for preventing air leaks through a gap between the under side surface of a projection extending from one of discs of the rotor and the upper side surface of a outward end portion of the spacer interposed between the discs. The spacer is formed with an annular groove on the upper side surface of the outward end portion for receiving a sealing wire in its entirety. The sealing wire has its outer portion forced against the underside surface of the projection by centrifugal forces while its inner portion remains inside the groove during turbine operation, to thereby seal the gap to prevent leaks of air therethrough.

Abstract: A one-piece cylindrical drum of a drum rotor has a plurality of enlarged, axially spaced-apart, annular rim portions through which axial blade root slots are machined. The slots are curved along their length about an axis located radially outwardly of the rim. The rotor is preferably made from a plurality of bonded together cylinder-like sections. After bonding the sections together the curved blade root slots are machined using a circular broach.

Abstract: A turbine rotor structure is disclosed in which shrink-fitted turbine wheels are keyed to the turbine shaft to prevent rotation of the wheels with respect to the shaft in the event of any loosening of the shrink fit. In a preferred arrangement, the rotatable shaft of the turbine is provided with an integral flange, near one end, having two diametrically opposed, notched keyways formed at peripheral locations thereon. Each wheel of the set of wheels used to carry the turbine buckets includes an integral, central hub which extends axially to both sides of the wheel. Further, each hub has pairs of complementary keys and keyways whose members are axially opposite each other at peripheral locations on the wheel hubs. Thus, the key of the first wheel on the shaft mates with the keyway of the integral flange of the shaft and subsequently added wheels mate with each other.

Abstract: A stacked rotor of an axial-flow type machine having a plurality of discs stacked in the axial direction and united into one body by stacking bolts, each of the discs being provided on the periphery thereof with a plurality of rotor blades. The portions of bolt holes in adjacent discs at the juncture of these discs are provided with opposing tapered surfaces. Each stacking bolt is supported by the discs through bolt deformation resisting members having an outer peripheral surface making close contact with the tapered surfaces of the bolt holes and an inner peripheral surface fitting around the stacking bolt.

Abstract: A turbine arrangement for a gas turbine engine having a sloped gas flowpath through the turbine. The radial axes of the rotor blades and stator vanes in the sloped flowpath are tilted such that the axes are substantially normal to the mean flow streamline of the gases. This arrangement reduces tip losses and thereby increases engine efficiency.

Abstract: A rotor of an axial-flow machine including a plurality of spacer members arranged peripherally of the rotor for providing a channel on the surface of the rotor. The spacer members are located in a manner to straddle the forward stage disc section and the rearward stage disc section, to enable each rotor blade to be replaced individually with a new one by mounting and removing the rotor blade axially of the rotor. The rotor of the axial-flow machine has improved reliability and flow performance.

Abstract: A rotor for jet engines includes a drum formed by disks and carrying blad Between the blades of two adjacent stages, braces are interspaced, the braces being projections which engage in sockets provided for this purpose on the disks. Each disk has two series of sockets, one receiving the roots of the blades, and the other, interspaced between the preceding, the projections of the braces. The blades are immobilized in translation at the upstream end by one ring and downstream by another ring, against which the roots of the blades of the terminal stages abut. The invention is particularly applicable to the building of axial type compressor rotors having several stages.

Abstract: An improved windage nut for fastening components of a gas turbine rotor assembly is disclosed. The outer portion of the nut has two lateral extensions for meeting with similarly shaped nuts adjacent to said nut to prevent rotation of the nut, and in combination with a plurality of similarly shaped nuts forms a ring shaped member having a smooth outer surface whereby friction and stresses are reduced during rotation of the rotor.

Abstract: A rotor of a jet engine turbine or compressor includes a plurality of disks each carrying radially extending blades. An annular spacer having a substantially double-T-shaped cross-section is located between two successive disks. One end of the spacer and one of the disks define an annular space between them. A gap exists between the one disk and the spacer through which the region between the blades can communicate with the annular space. A sealing ring is arranged within the annular space with its width extending across the gap. Upon rotation of the rotor, centrifugal force presses the sealing ring against the radially outer wall of the annular space to seal the gap. The sealing ring may be an elongated strip bent into a ring shape with its ends overlapped. The side edges of the sealing ring may be bent generally toward the center of the annular space.

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: An interstage spacer for the turbine section of a gas turbine engine is provided with a flexible bellows which absorbs axial growth of the adjacent turbine stages to prevent seizing and binding.

Abstract: A runner for an hydrodynamic machine comprises fixed runner vanes mounted in a predominantly radially oriented part of an annular channel defined between a crown and a skirt ring, and a crown tip attached to the crown and defining with the skirt ring a predominantly axial portion of the channel. Fins attached to the crown tip deflect the flow leaving the runner vanes to eliminate essentially all vortex flow when the turbine operates above an optimum condition. The fins are substantially triangular in shape and are located with the apex portion nearest the runner vanes and the base portion remotest from the vanes. They are curved along their length, the apex being substantially aligned with the flow from the vanes and the base being aligned to deflect the flow in a direction generally with the axis of rotation of the runner.

Abstract: A compressor construction is shown, in combination with a jet engine, having a drum rotor with axially broached attachment slots therein. Blade sticks, each having an axial root shaped to fit the attachment slots and a platform which extends the length of the drum are positioned on said drum. Each blade stick has a plurality of blades located thereon, one for each stage of the compressor. A one-piece stator case with fixed cantilevered vanes is positioned over said drum rotor and blade sticks to form the completed compressor. A drum rotor has an integral shaft which is connected to a turbine. A method of assembling the compressor includes an assembly fixture on which the drum rotor can be positioned with the stator case and blade sticks being aligned so that they can be slid into place on the drum rotor.

Abstract: Rotor of disc construction for at least single-shaft gas turbines having compressor and turbine stages includes respective rotor disc packages for the compressor and turbine stages, a hollow shaft located between the compressor and turbine stages, and respective shaft stubs seated at the outer ends of the rotor disc packages at respective meshing centering ring gears secured against torsion, all strung together coaxially, and means for clamping the same together including a connecting rod extending centrally therethrough; and tubular intermediate members located between the outer periphery of the connecting rod and the inner periphery of the rotor discs for maintaining elastic contact between the connecting rod and the discs during operation of the turbine, the intermediate members being axially divided shells surrounding the connecting rod, and at least one clamping ring clamping the shells together and bracing them against the outer periphery of the connecting rod.