Abstract: A fan assembly 10 is provided including at least one impeller blade 12, a rotating ring element 14 having a flared inner discharge surface 22, and a shroud element 20 having a shroud exit surface 32 substantially coincident with the flared inner discharge surface 22.

Abstract: A rotating blade with reduced noise for use, for example, in a fan or other fluid pumping structure, is disclosed. The structure includes a housing, a hub rotatably coupled to the housing, a plurality of blades, each with an inner edge attached to the hub, and a plurality of end-pieces. Each end-piece is attached to an outer edge of a corresponding one of the blades. Each end-piece extends in the axial direction beyond the surface of the outer edge of the corresponding blade. The advantage is that less turbulence is created by the blades, resulting in reduced noise and greater efficiency.

Abstract: A fan assembly 10 is provided including at least one impeller blade 12, a rotating ring element 14 having a flared inner discharge surface 22, and a shroud element 20 having a shroud exit surface 32 substantially coincident with the flared inner discharge surface 22.

Abstract: A turbomachine for moving air includes a shroud 12 disposed about an axis A. The shroud 12 has a pair of opposing faces 14 and 16 defining a gap 18 therebetween. The opposing faces are disposed generally transversely with respect to the axis. A rotor assembly 13 is mounted for rotation about the axis. The rotor assembly has a plurality of blades 22 with tips of the blades being coupled to an annular band 30. At least a portion 32 of the annular band is disposed in the gap 18. Seal structure 36 extends from each opposing face of the shroud and into the gap to reduce swirl and minimize air leakage across the gap.

Abstract: An improved gas turbine blade is disclosed that utilizes a blade tip shroud with tapered shroud pockets to remove excess weight from the shroud while not compromising shroud bending stresses. Excess shroud weight removed by the tapered pockets reduces overall blade pull while maintaining material necessary to increase shroud stiffness. The resulting rib created between the tapered pockets provides a surface, away from possible areas of stress concentration, for drilling radial cooling holes.

Abstract: A turbomachine for moving air includes a shroud 12 disposed about an axis A. The shroud 12 has a pair of opposing faces 14 and 16 defining a gap 18 therebetween. The opposing faces are disposed generally transversely with respect to the axis. A rotor assembly 13 is mounted for rotation about the axis. The rotor assembly has a plurality of blades 22 with tips of the blades being coupled to an annular band 30. At least a portion 32 of the annular band is disposed in the gap 18. Seal structure 36 extends from each opposing face of the shroud and into the gap to reduce swirl and minimize air leakage across the gap.

Abstract: A turbomachine for moving air comprising includes a shroud disposed about a longitudinal axis and a rotor assembly mounted for rotation about the longitudinal axis. The rotor assembly has a plurality of blades and tips of the blades are coupled to an annular band. The annular band is disposed with respect to the shroud so as to define a gap extending continuously between an outer surface of the annular band and an inner surface of the shroud. A seal structure extends from the inner surface of the shroud and into the gap. The seal structure has a density sufficient to reduce swirl in recirculating airflow and to minimize air leakage across the gap.

Abstract: A curved section (12) is provided at a proximal end of a fan (10), so that a rotation locus thereof is configured in a shape conforming to a flow of a cooling air such as center-dented. Accordingly, the cooling air can be smoothly sucked in by the fan (10) as well as fan shroud along an arcuate section on an inlet side. Further, since natural flow toward radially outward flow of the cooling air can be guided by an arcuate section on an outlet side, thus smoothly discharging the cooling air. Therefore, the flow of the cooling air can be made smooth entirely from upstream to downstream, thus increasing flow rate and reducing noise.

Abstract: The adjoining edges of bucket covers are sealed one to the other. A brush seal projecting from a stationary shroud overlies the bucket covers. A joint at which the adjacent covers sealingly engage each other precludes radial outflow of high pressure fluid into bristles of the brush seal, preventing radial and axial deflection of the bristles and consequent failure of the bristles. The joints between the covers may comprise lap or tongue-and-groove joints.

Abstract: A split ring is disposed on an inner wall of a gas turbine casing. The split ring is composed of a plurality of split segments that are arranged on the inner wall of the casing in circumferential direction. A predetermined clearance is formed between the inner face of a split segment and the rotor blade tips. The split segments are arranged so that a predetermined circumferential clearance is formed between the split segments in order to allow the thermal expansion of the segments. A circumferential end face located upstream side of the segments with respect to the direction of the rotor blade rotation is connected to the inner face by a transition face having a surface formed as an inclined plane. The inclined plane prevents the swirl flow caused by the rotating rotor blade from impinging the upstream end face and, thereby, suppresses a temperature rise of the split segment at the upstream end face.

Abstract: The shroud (26) of a shrouded turbine blade (22) has a convex leading edge (30) the apex of which extends towards the trailing edge of the shroud (24) of an adjacent, preceding guide vane. The extension enables the containment of a reverse flow of high pressure gas from the juncture of the blade aerofoil and shroud, until the pressure has dropped sufficiently to avoid nullifying gas flow from the corresponding portion of the guide vane (20) and thereby reduces excessive hot gas leakage from between the opposing shrouds edges.

Abstract: The adjoining edges of bucket covers are sealed one to the other. A brush seal projecting from a stationary shroud overlies the bucket covers. A joint at which the adjacent covers sealingly engage each other precludes radial outflow of high pressure fluid into bristles of the brush seal, preventing radial and axial deflection of the bristles and consequent failure of the bristles. The joints between the covers may comprise lap or tongue-and-groove joints.

Abstract: An air seal for use in a gas turbine engine is disclosed. The seal includes a seal substrate, and an abradable layer on the substrate, with the abradable including a thermoset polymer and a thermoplastic polymer. The abradable may also include a filler to add porosity, or provide lubrication, to enhance abradability.

Abstract: A cooling structure 10 for cooling an engine includes an axial flow fan 16 having a plurality of blades 14. A shroud 12 is spaced from and is generally adjacent to the blades 14. A plurality of Helmholtz resonators 24 and 24′ is carried by the shroud 12. Each of the resonators 24 and 24′ has an opening disposed substantially perpendicular with respect to a direction of air flow resulting from rotation of the fan 16. The resonators 24 and 24′ are disposed at locations on the shroud 12 which are generally adjacent to tips 32 of the blades 14. The resonators 24 and 24′ are tuned to reduce blade passing tone of the fan 14.

Abstract: In a centrifugal type blower unit, a diameter of an air suction port is set to be larger than a minimum inner diameter of a centrifugal fan, and a slanting portion is formed in each blade of the centrifugal fan at a side of the air suction port so that an inner radius dimension of the centrifugal fan is increased toward the air suction port. Therefore, it can prevent sub-flow air which is sucked into the centrifugal fan from an end side of the blades in an axial direction from interfering with main-flow air which is sucked into the centrifugal fan from an inner radius side of the blades. Thus, the blower unit can reduce second noise generated therefrom without greatly reducing air-blowing capacity.

Abstract: A rotatable assembly for use with a gas turbine engine comprises a rotatable disk, and a plurality of blades for affecting a flow of air passing thereover during use. The blades are attached to the rotatable disk, and each one of the plurality of blades has a blade root and a blade tip disposed opposite said blade root. A first ring self supporting is disposed adjacent a first portion of each of the blade tips, the first ring being in interfering contact with the first portion of each blade tip when the rotatable disk is stationary. The interfering contact is preferably between about 0.01 inches and about 0.1 inches. The first ring can be provided over a portion of the blade tips or can extend from about the leading edge of each blade to about its trailing edge. A second ring in interfering contact with the blade tips can also be provided.