Abstract: A rotor blade for a gas turbine engine including a tip region that facilitates reducing operating temperatures of the rotor blade is described. The tip region includes a first tip wall and a second tip wall extending radially outward from a tip plate of an airfoil. The tip walls extend from adjacent a leading edge of the airfoil to connect at a trailing edge of the airfoil. A notch is defined between the first and second tip walls at the airfoil leading edge. At least a portion of the second tip wall is recessed to define a tip shelf.

Abstract: A rotor blade for a gas turbine engine including a tip region that facilitates reducing operating temperatures of the rotor blade is described. The tip region includes a first tip wall and a second tip wall extending radially outward from a tip plate of an airfoil. The tip walls extend from adjacent a leading edge of the airfoil to connect at a trailing edge of the airfoil. A portion of the second tip wall is recessed to define a tip shelf that extends from the airfoil leading edge to the airfoil trailing edge.

Abstract: A gas turbine engine rotor blade includes an airfoil having first and second sidewalls joined together at leading and trailing edges. First and second tip walls extend from adjacent the leading edge along the respective first and second sidewalls to adjacent the trailing edge and are spaced apart to define a tip cavity therebetween. A first notch is disposed in the first tip wall adjacent to the leading edge for channeling into the tip cavity a portion of combustion gases flowable over the airfoil for reducing the heating effect of the gases on the blade tip. In a preferred embodiment, a second notch is disposed adjacent to the trailing edge for promoting flow through the tip cavity from the first notch.

Abstract: A wall adapted for use in a gas turbine engine between a first fluid and a second hotter fluid includes a first side over which is flowable the first fluid, and an opposite second side over which is flowable the second fluid. An elongate slot extends partly inwardly and perpendicularly from the second side toward the first side and is provided with the first fluid through a plurality of longitudinally spaced apart holes. The holes are aligned coplanar with the slot and longitudinally inclined to effect longitudinal overlapping of the first fluid inside the slot prior to discharge therefrom as a substantially continuous film.

Abstract: The cageless thrust bearing with unguided cylindrical rollers comprises a pair of thrust bearing races with axially separated flat thrust raceways. Cylindrical rollers all having the same diameter are located between the separated flat thrust raceways. The spacing of the rollers is such that the rollers become radially aligned in the bearing under a rotating thrust load, without side or end guidance of the rollers.

Abstract: The roller thrust bearing cage and roller assembly includes an annular cage with a plurality of circumferentially spaced pockets. Each of the pockets is shaped to give proper guidance to the roller when the extended center line of the roller passes through the axis of the annular cage. Preferably each pocket has two radially, inwardly converging sides and preferably, the pockets are trapezoidal. A cylindrical roller is preferably located in each of the pockets.

Abstract: The separator ring to be used with thrust bearings is an annular member with a plurality of circumferentially separated roller engaging portions. The rollers have outer ends constructed to mate with the roller end engaging portions of the annular member. The roller engaging portions on the annular member may be protrusions extending radially inwardly toward the axis of the bearing with the rollers having depressions on the outer ends for receiving the protrusions or alternatively, the roller engaging portions may be radially outwardly extending depressions with the rollers having outer surfaces which fit into the depressions.