Abstract: A gas turbine engine comprises a shaft assembly including a hollow shaft of the gas turbine engine and a plug connected to the inlet end of the shaft. The hollow shaft has a shaft bore having a bore diameter. The hollow shaft has an inlet end for receiving a first portion of an incoming air flow. The plug has a plug bore therethrough, and an inlet end having an inlet diameter. The inlet diameter of the plug is smaller than the bore diameter. The plug includes a deflection surface adapted to deflect a second portion of the incoming air flow away from the shaft bore. A plug for connecting to an end of a hollow shaft of a gas turbine engine and s method of controlling a flow of fluid through a shaft having a bore therethrough of a gas turbine engine are also presented.

Abstract: A mid-turbine frame module comprises an outer structural ring, an inner structural ring and a plurality of circumferentially spaced-apart spokes structurally interconnecting the inner structural ring to the outer structural ring. The spokes are used as air feed pipe to provide cooling to different engine systems, such as an oil scupper line and a disc cavity of an adjacent turbine disc.

Abstract: A mid-turbine frame of a gas turbine engine has a structural ring assembly comprising an outer ring, an inner ring having a plurality of threaded bosses extending from a radially outer surface thereof, and a corresponding number of structural spokes interconnecting the inner ring to the outer ring. Each spoke has a radially inner threaded end threadably engaged in an associated one of the threaded bosses on the inner ring.

Abstract: A mid-turbine frame module comprises an outer structural ring, an inner structural ring and a plurality of circumferentially spaced-apart spokes structurally interconnecting the inner structural ring to the outer structural ring. At least one of the tubular spokes accommodates a service line. The remaining spokes with no service line have an internal architecture which mimics an air cooling scheme of the at least one spoke housing a service line in order to provide temperature uniformity across all spokes.

Abstract: A gas turbine engine comprises a shaft assembly including a hollow shaft of the gas turbine engine and a plug connected to the inlet end of the shaft. The hollow shaft has a shaft bore having a bore diameter. The hollow shaft has an inlet end for receiving a first portion of an incoming air flow. The plug has a plug bore therethrough, and an inlet end having an inlet diameter. The inlet diameter of the plug is smaller than the bore diameter. The plug includes a deflection surface adapted to deflect a second portion of the incoming air flow away from the shaft bore. A plug for connecting to an end of a hollow shaft of a gas turbine engine and s method of controlling a flow of fluid through a shaft having a bore therethrough of a gas turbine engine are also presented.

Abstract: A turbine blade for a gas turbine engine comprises a platform, a blade root, an airfoil portion defining pressure and suction sides, and a shroud provided at a tip of the airfoil portion opposite to the blade root. The shroud includes a body having a radially outer face opposite to the airfoil portion, upstream and downstream generally parallel fins extending outwardly from the outer face, and two ribs extending outwardly from the outer face. Each of the fins has an end disposed toward the pressure side and another end disposed toward the suction side. The ribs extend from and connecting the upstream fin to the downstream fin at locations other than the ends of the upstream and downstream fins. The ribs converge toward the downstream fin at an angle of between about 10 and about 45 degrees. A shroud for a blade is also presented.

Abstract: A segmented shroud ring surrounds a circumferential array of blades of a gas turbine engine rotor. The shroud ring has a plurality of shroud segments disposed circumferentially one adjacent to another. The circumferentially adjacent shroud segments have confronting sides defining an inter-segment gap therebetween. The inter-segment gaps are sealed by a sealing band mounted to the radially outer surface of the segmented shroud ring so as to extend across the inter-segment gaps around the full circumference of the shroud ring. Impingement jet holes may be defined in the sealing band for cooling the shroud segments.