United Technologies Corporation

Edward C Hill

Thomas A Auxier

George P Liang

Wesley D Brown

Douglas L Kisling

Peter T Vercellone

Ronald D Delahoussaye

Leon R Anderson

Damping of a turbine rotor is attained by a weighted member trapped between pockets formed in the neck of adjacent blades at one end and a space between the disk and TOBI rotor seal and forward extending blade lug at the other end. The feather seal which is a curved plate fits over the top of the weighted member and is trapped between nubs formed on the front and rear underside of the blade platform. The front face of the rim of the disk at the disk cavity is open ended and blocked off at the rear face. This assembly allows for individual blade removal and viewing from the rear face by removing a single rim cavity cover without disturbing the remaining components of the assembly. The inverted ring supports take up the axial loads alleviating the loads heretofore taken up by the TOBI rotor seal, allowing for a lighter weight installation.

Turbine rotor retention system

The wall of a hollow airfoil has a longitudinally extending slot in its external surface which is intersected, at its base, by a plurality of coolant passages in a longitudinally extending row. Each coolant passage has a metering portion at its inner end which communicates with a coolant compartment within the hollow airfoil. Each passage includes a pair of walls downstream of the metering portion which diverge from each other in the longitudinal direction and intersect with the base of the slot to form an outlet for the passage. The diverging walls of adjacent passages substantially meet each other at the base of the slot, wherein coolant fluid from the metering portions of the passages diffuses in the longitudinal direction as it flows toward and into the slot, filling the entire slot and forming a thin, continuous film of coolant downstream of and along the entire length of the slot over the external surface of the airfoil.

Coolant passages with full coverage film cooling slot

A turbine airfoil for high temperature applications has a spanwise trailing edge slot and a cut back pressure side wall. The pressure side wall has a thickness t at its downstream end. The slot is divided into channels which discharge a film of cooling air over the exposed back surface of the suction side wall downstream of the cut back pressure side wall. Each channel tapers from a throat at its upstream end (which meters the flow of cooling air) to the slot outlet of width s. The airfoil is designed with a ratio t/s of no more than 0.7 which significantly improves cooling of the trailing edge, reduces required cooling air flow, and permits greater cut back distances.

Airfoil trailing edge cooling arrangement

A device for securing an annular blade retaining plate to a rotor disk includes an annular groove around the disk for receiving an off-set annular flange on the inner end of said blade retaining plate. A split retainer ring extends from a second groove intersecting said first groove to fix the blade retainer ring to the disk. A locking ring is positioned between said split retainer ring and said blade retaining plate to maintain said split retainer ring in its groove.

Rotor disk cover plate attachment

A sheet metal seal for sealing the gap between adjacent blade platforms in a rotor assembly fits within a pair of spaced apart slots on the underside of one of the platforms and is trapped in position by a lug disposed between the slots and which passes through a hole in the seal. The seal is attached to the blade prior to its assembly in the disk. A portion of the seal overhangs the edge of the platform to which it is attached and, when the blade is inserted into the disk, the extended portion of the seal overlies the underside surface of the adjacent blade platform. This seal is preliminarily shaped to the contour of those portions of the underside surfaces of the platforms against which they are to bear during rotation of the assembly. ,

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Tequesta, FL, United States of America

Edward C Hill