General Electric Company

Frederick Martin Miller

Christopher Charles Glynn

Roger C Walker

Poul D Pedersen

Larry W Plemmons

Dean Thomas Lenahan

William Lee Herron

Curtis Walton Stover

Martin C Hemsworth

Sang Yeng Park

William Gary Klump

Clifford C May

In a compressor rotor assembly including a plurality of rotor disks affixed to a rotor body, and wherein at least one radially directed cooling tube is supported from a radially outer end within a rotor shaft, with an opposite, radially inner free end extending toward a longitudinal axis of the rotor, an improvement comprising a ring member loosely secured to the tube at the free end.

Cooling air tube vibration damper

Stacked wheels of the rotor of a rotary machine are axially coupled to one another by tie bolt assemblies. Each tie bolt assembly includes a stud having externally threaded opposite ends. A forward end of each stud is threaded into a non-rotatable windage nut. The aft end of each stud is secured by a primary nut having a plurality of facets, a jam nut locked against the primary nut and an anti-rotation cover between the jam nut and primary nut. The anti-rotation cover includes wings engaged against a next-adjacent wheel, preventing rotation of the cover relative to the rotor. Internal surfaces of the cover have facets greater in number than the number of facets on the primary nut whereby fine clock orientation of the cover relative to the adjacent wheel is obtained. The cover and primary nut are thus locked against rotation, thereby locking the stud/nut assembly against rotation relative to the rotor.

Tie bolt and stacked wheel assembly for the rotor of a rotary machine

One form of a retention system includes a pair of aft segments of 180.degree. in length disposed in annular grooves about a compressor spool, the segments having radial projections against which the aft end faces of the base portions of rotor blades abut. The blade base portions are shaped and are received in complementary-shaped slots of the spool. The forward retention system includes a plurality of arcuate segments approximately 30.degree. in length disposed in grooves adjacent the forward end faces of the blades. With the exception of the final pair of blades, the blade base portions thereof are located in the axial complementary slots in pairs, with each forward arcuate segment, except the final segment, being disposed in the groove at a circumferentially spaced location and displaced circumferentially to abut the forward end faces. The final arcuate segment is radially reduced and disposed in the remaining portion of the groove to lie flush with the spool. The base portions of the final blades are axially inserted over the final segments and the latter is displaced radially outwardly and pinned to abut the forward end faces of the final blade base portions. In another form, tabs project forwardly or rearwardly from the base portions of the blades. The tabs have holes in registry with corresponding holes in the blade slot for receiving pins thereby preventing axial movement of the blades relative to the spool.

Retention system for the blades of a rotary machine

In a gas turbine including a compressor having a bore and a rotor comprised of multiple stages extending between a first stage at a forward end of the compressor and a last stage at an aft end of the compressor, each stage including a rotor disk having a peripheral rim and multiple blades secured to the peripheral rim, a combustion system comprising a plurality of combustors utilizing discharge air from the compressor for combustion, and multiple turbine stages driven by combustion gases from the combustion system, the improvement comprising means for supplying cooling air at least to a peripheral rim of the last stage of the compressor.

Compressor rotor cooling system for a gas turbine

Growing community of inventors

Cincinnati, OH, United States of America

Frederick Martin Miller