Abstract: The present invention provides a gas turbine engine blade having a dovetail, a shank extending radially outward from the dovetail, and a platform joined to the shank. An inner surface of the platform faces radially inwardly and an opposite outer surface of the platform faces radially outwardly. An airfoil extends radially outwardly from the platform and has pressure and suction airfoil sides that define pressure and suction blade sides of the blade. The platform extends axially between leading and trailing platform edges and transversely between pressure and suction side platform edges of the platform. At least one transversely extending bracing rib is in a corner of the shank and the platform between one of the blade sides and the inner surface of the platform. The preferred embodiment further includes the bracing rib, the shank, and the platform being integrally cast. The bracing rib is preferably wider along the platform and the shank than at a distal edge of the rib.

Abstract: A rotor blade for a rotor of a gas turbine engine having an axis of rotation including a root portion, a platform portion connected to the root portion and having a damper pocket formed therein, an airfoil portion connected to the platform portion, a generally bar-shaped damping member loosely arranged in the damper pocket having at least one scrubbing surface, and at least one leg extending from the bar-shaped damping member for retaining the bar-shaped damping member in the damper pocket. The bar-shaped damping member is slidably displaceable and rotatable within the damper pocket during rotation of the rotor. The damper pocket in the platform portion has a rear surface with an upper portion and a lower portion at an angle to the upper portion, a pair of spaced side surfaces, and a pair of spaced lower surfaces extending from the rear surface lower portion which are substantially coplanar.

Abstract: A shroud panel for a turbine shroud includes forward and aft hooks which are used to support the panel radially above a plurality of turbine rotor blades. The panel forward hook has radially outer and inner lands, with the outer land being defined by a plurality of pads circumferentially spaced apart from each other by a respective recess. The panel forward hook is sized to engage the complementary forward slot of the turbine shroud substantially concentrically therein. The pads and recess restrict flow leakage around the panel forward hook for maintaining backflow margin and improving clearance control.

Abstract: A turbine shroud includes an annular outer casing having first and second radial flanges between which are suspended an adjoining annular shroud support and an annular shroud hanger. A plurality of shroud panels are joined to the shroud hanger and are positionable radially above turbine rotor blades to define a tip clearance therebetween. The four flanges are disposed in abutting contact with each other, and respective pluralities of circumferentially spaced apart first, second, and third recesses are disposed respectively between the casing first flange and the shroud flange, between the shroud flange and the hanger flange, and between the hanger flange and the casing second flange for providing radial flowpaths therebetween.

Abstract: A turbine shroud hanger is supported from an annular outer casing and includes an annular radial flange and integral forward and aft legs at a radially inner end thereof. The legs extend axially oppositely to each other and include respective distal ends configured for supporting a plurality of arcuate shroud panels radially above a plurality of turbine rotor blades to define a tip clearance therebetween. The legs include circumferentially spaced apart forward and aft slots extending axially from the distal ends thereof toward the radial flange, and completely radially therethrough to bifurcate the legs into circumferential segments for reducing transient thermal expansion of the hanger to reduce in turn expansion of the tip clearance.

Abstract: A turbine shroud includes an annular shroud support joined to an annular outer casing and spaced radially inwardly therefrom to define an annular flow duct for receiving compressor bleed air. A plurality of shroud panels are joined to the shroud support and have a radially inner surface positionable radially above turbine rotor blades to define a tip clearance therebetween. An isolation shield is joined to the shroud support radially above the panels and includes a plurality of open-ended cells facing radially outwardly in the duct toward the outer casing for inducing drag in the bleed air flowable axially through the duct to thermally isolate the shroud support from the bleed air for controlling the tip clearance.

Abstract: A turbine shroud hanger includes forward and aft radially outer hooks for mounting the hanger to an annular shroud support, and forward and aft radially inner hooks for supporting a shroud panel radially above a plurality of turbine rotor blades for controlling tip clearance therebetween. The hanger forward outer hook has a radially outer land defined by a pair of pads at distal ends of the hook, with a ridge extending circumferentially therebetween. The outer land is interrupted by a central recess extending between the pads and aft from the ridge to a distal edge of the hook. The forward outer hook has a predetermined radial height which is predeterminedly larger than the radial height of the corresponding forward slot in the shroud support for effecting an interference fit at least in part at the pair of pads to provide a seal against leakage of bleed air.