Abstract: A blocker and swirl inducer hole configuration for use in connection with a high pressure turbine is described. In one embodiment, the blocker holes are oriented to a 45-degree tangential angle with respect to the direction of rotation of the seal, which results in pre-swirling the air before being injected into the swirl cavity. In addition, the number of blocker holes is reduced by as much as 50% of the number of blocker holes used in the known CFM56 turbine. Further, rather than injecting the air into the first swirl cavity as is known, the air is injected into a second swirl cavity. The combined effect of orienting the holes to the 45-degree tangential angle with respect to the direction of rotation of the seal, locating the holes to open into the second swirl cavity, and reducing the flow area by about 50%, results in an increase in blocker hole pressure ratio. Increasing the blocker hole pressure ratio results in a higher hole exit velocity which maximizes the cavity inlet swirl.

Abstract: A turbine rotor includes a rotor disk having a plurality of dovetail slots defining therebetween respective disk posts. Each post has a top land and a plurality of tangs spaced radially therebelow inside adjacent ones of the slots. A plurality of turbine blades each having a dovetail are mounted in respective ones of the dovetail slots for radially retaining the blades. A platform is joined integrally with the dovetail and extends circumferentially to adjoin adjacent ones of the platforms to define a radially inner flowpath. An airfoil extends integrally from the platform for extracting energy from combustion gases flowable thereover. A thermal barrier coating is fixedly bonded to each of the disk post top lands for providing thermal insulation between the platforms and the disk posts for reducing disk post temperature.

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 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 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 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.