In An AC generator for a vehicle in which a bearing is inserted into a bearing box formed in a bracket and the bearing is fixed and retained by a retainer, the retainer has a cylindrical shape and a threaded portion is formed on the cylindrical section thereof, a threaded portion is formed on the bearing box, and the threaded portion of the retainer is directly screwed to the threaded portion of the bearing box in order to fix and retain the bearing, so that the gap between the outer circumference surface of the bearing box or the outer circumference surface of the retainer and the opposing side of a cooling fan is made uniform.

Ac generator for vehicle

A gas turbine engine assembly (10), includes a core gas turbine engine (12), a low-pressure turbine (14) coupled to the core turbine engine, a counter-rotating fan assembly (16) coupled to the low-pressure turbine, and a booster compressor (24) coupled directly to the low-pressure turbine such that the booster compressor and the low-pressure turbine rotate in the same direction.

Gas turbine engine assembly and methods of assembling same

Dirt removal means for an internally air cooled blade for a gas turbine engine of the type that includes multi passes some of which are serpentine as made in situ by casting the ribs so as to be angularly disposed at the root of the blade and a straight through passageway with an opening at the tip. The velocity of the airstream in the straight through passageway being sufficiently high to carry the dirt through the opening and the angularly disposed ribs overlying the entrance to the other passageway so as to divert the dirt entrained airstream into the straight through passageway while allowing relatively dirt-free air to turn the angle of the rib to enter the serpentine passes.

Dirt removal means for air cooled blades

A method enables a gas turbine engine (10) to be assembled. The method comprises forming at least one substantially elliptically-shaped opening (80) within a flange (72) extending from a fan disk (40), inserting a fastener (120) including a first body portion (122), a second body portion (124), and an anti-rotation stop (126) extending therebetween, at least partially through the at least one flange opening, and coupling the fastener to the flange such that the fastener stop is positioned within the at least one flange opening.

Methods and apparatus for assembling gas turbine engines

A fluid dampened support for a bearing such as a tilt pad bearing or a rolling element (13) bearing such as a ball bearing, needle bearing, roller bearing and the like. The fluid dampened support (20) includes a network of closely spaced beams (24, 26, 28), which act as structural springs which support the outer race of the roller bearing for movement in any direction. The spring rate or constant of these structural springs can be caused to change after a selected amount of deflection. The amount of deflection needed to cause the change in spring rate can be adjusted to suit the particular application. A liquid is provided in the spaces between the beams (24, 26, 28) to dampen movement of the pads. The damping rate can be made to change with movement of the pads (32).

Fluid dampened support having variable stiffness and damping

Stator vane assembly having composite sectors

An improved bearing assembly is provided for supporting a rotating shaft. The improvement is comprised of utilizing a resilient support means in combination with a multiple squeeze film damper apparatus. The damper apparatus provides a large damping force to suppress large vibrations and excessive radial shaft deflections in the event of operation with an abnormally high unbalanced shaft. The resilient support provides a soft spring system as a means for establishing and maintaining the critical rotor speed at a low speed condition, for centering the shaft during normal operation, and for allowing radial deflection during operation with an unbalanced shaft.

Bearing assembly with multiple squeeze film damper apparatus

Segmented nozzle diaphragm for high temperature turbine

1,177,577. Turbine bladed rotors. GENERAL ELECTRIC CO. Oct.30, 1967, No.49189/67. Heading F1T. The invention relates to a multistage turbine rotor comprising first and second axially spaced rotor discs having blades mounted at their peripheries, the blades of the first rotor disc having cooling passages extending therethrough. A cooling air chamber is formed between the rotor discs by a spacer member extending therebetween, and passageways extend from the chamber to the air passages in the blades, the passageways being disposed radially inwardly of the adjacent portion of the spacer member so that dirt particles entrained in the cooling air will be thrown past the passageways and collected against the spacer member. The gas turbine engine turbine rotor shown comprises first stage and second stage rotor discs 10, 12 having blades 20, 22 mounted at their peripheries, the first stage blades 20 having fir-tree roots 28 which engage in fir-tree slots (30) in the periphery of the disc 10. The blades 20 are formed with small diameter cooling air passages 38. The rotor discs are interconnected by a torque ring 14 secured thereto, and a spacer ring 25 extends between their peripheries, the rotor discs 10, 12 and rings 14, 25 defining a chamber 44 to which cooling air is supplied through openings 42 in the disc 10. The spacer disc 25 is formed with a flange 34, the flange 34 and a second flange member 32 being secured at opposite sides of the rotor disc 10 by means of bolt members 36 which extend through the fir-tree slots 30 beneath the blade roots 28. Passages 46 are formed through the flange 34 for flow of cooling air from the chamber 44 to the blade passages 38, the passages 46 being located radially inwardly of the inner surface 50 of the spacer disc 25 so that in operation dirt particles will be thrown outwardly and collected on the recessed surface 50. A circumferential groove 48 is formed on the outer surface of the flange 34 and defines an annular chamber into which the passages 46 discharge, any remaining dirt particles being thrown to the outer part of the chamber as shown.

Turbine rotor constructions

A turbomachine seal for reducing fluid flow through the gap between circumferentially adjacent blade platforms is disclosed. The seal comprises a pair of radially inwardly extending elastomeric members. Each member has an inwardly extending first face and is bonded at a second face to respective ones of adjacent platforms. Each elastomeric member is circumferentially deflectable under a centrifugal load so that respective first faces meet.

Bobo Melvin

Papers

Stator vane assembly having composite sectors

Bearing assembly with multiple squeeze film damper apparatus

Segmented nozzle diaphragm for high temperature turbine

Turbine rotor constructions

Fan blade platform seal