Abstract: A seal for a dovetail joint in a turbomachine is provided. The seal includes an arcuate member having a first end, a middle portion and a second end. The seal also includes sealing means, which include at least one sealing member. The sealing member can comprise a first sealing member connected to the first end and/or a second sealing member connected to the second end. The dovetail joint is the interface between a bucket dovetail and a rotor dovetail groove, and the seal reduces the amount of cooling flow leakage from the dovetail joint.

Abstract: A seal for a dovetail joint in a turbomachine is provided. The seal includes an arcuate member having a first end, a middle portion and a second end. The seal also includes sealing means, which include at least one sealing member. The sealing member can comprise a first sealing member connected to the first end and/or a second sealing member connected to the second end. The dovetail joint is the interface between a bucket dovetail and a rotor dovetail groove, and the seal reduces the amount of cooling flow leakage from the dovetail joint.

Abstract: A bucket for a turbine includes a dovetail mounting portion, a shank portion defined at a radially outer end thereof by a platform, and an airfoil portion extending radially outward of the platform. The airfoil portion has a radially outer end closed by a tip cap having a non-planar shape that reduces stress in the tip cap during use. A related method of reducing stress in a tip cap of a turbine bucket includes providing an airfoil portion of the turbine bucket with a radially outer end; and closing the radially outer end with a tip cap having a non-planar shape that reduces stress in the tip cap during use.

Abstract: An annular disk side plate for a gas turbine engine rotor assembly includes an annular plate hub and an annular plate shaft extension extending axially forwardly from the plate hub. A plate web extends radially outwardly from the plate hub and a plate rim extends radially outwardly from the plate web. In the exemplary embodiments of the invention illustrated herein, the plate rim is canted aftwardly from the plate web. One or more annular sealing ridges extend aftwardly from the plate rim. The side plate further includes an anti-rotation means for preventing rotation of the disk side plate relative to the disk such as a circumferential row of radially extending circumferentially spaced apart tabs. Cooling air apertures or holes extend axially through the plate web. A rotor assembly further includes an annular rotor disk comprising a disk hub and an annular disk shaft extension extending axially forward from the disk hub.

Abstract: An annular disk side plate for a gas turbine engine rotor assembly includes an annular plate hub and an annular plate shaft extension extending axially forwardly from the plate hub. A plate web extends radially outwardly from the plate hub and a plate rim extends radially outwardly from the plate web. In the exemplary embodiments of the invention illustrated herein, the plate rim is canted aftwardly from the plate web. One or more annular sealing ridges extend aftwardly from the plate rim. The side plate further includes an anti-rotation means for preventing rotation of the disk side plate relative to the disk such as a circumferential row of radially extending circumferentially spaced apart tabs. Cooling air apertures or holes extend axially through the plate web. A rotor assembly further includes an annular rotor disk comprising a disk hub and an annular disk shaft extension extending axially forward from the disk hub.

Abstract: A seal includes a seal ring with a circumferential split defining a gap. An arcuate bridge extends across the gap and nests in the seal ring. The bridge includes an anchor end which engages the seal ring solely in friction to restrain differential circumferential movement therebetween. The bridge also includes a slip end engaging the seal ring on an opposite side of the gap with less friction than the anchor end to permit differential circumferential movement therebetween.

Abstract: A gas turbine engine airfoil is manufactured by forming an internal retention seat in two complementary airfoil parts. An insert is fabricated for retention in the seat. The two parts are assembled with the insert disposed in the seat therebetween. The parts are then bonded together to trap the insert therein to collectively define the airfoil. The insert and seat may be precisely fabricated for improving the efficiency of the airfoil.

Abstract: A gas turbine engine rotor blade 18 includes a dovetail 22 and integral airfoil 24. The airfoil includes a pair of sidewalls 28,30 extending between leading and trailing edges 32,34, and longitudinally between a root 36 and tip 38. The sidewalls are spaced laterally apart to define a flow channel 40 for channeling cooling air through the airfoil. The tip includes a floor 48 atop the flow channel, and a pair of ribs 50,52 laterally offset from respective sidewalls. The ribs are longitudinally tapered for increasing cooling conduction thereof.

Abstract: A turbine shroud includes a panel having a forward hook and an aft hook spaced therefrom. A primary cooling circuit extends through the panel adjacent the forward hook, and has a primary inlet for receiving primary air at a first pressure, and a primary outlet for discharging the primary air. A secondary cooling circuit extends through the panel adjacent the aft hook independently of the primary circuit. The secondary circuit includes a secondary inlet for receiving secondary air at a second pressure different than the first pressure, and a secondary outlet for discharging the secondary air. The dual cooled shroud accommodates differential gas pressure through the turbine.

Abstract: A rotor blade includes a dovetail and an airfoil joined thereto. The airfoil includes first and second spaced apart sides joined together laterally at opposite leading and trailing edges, and spanwise at a root and opposite tip. A serpentine cooling circuit extends inside the airfoil for channeling air therethrough for cooling the blade. The serpentine circuit includes first and second passes and a first bend therebetween for firstly receiving the cooling air in turn from the dovetail. A tip circuit is disposed between the tip and the serpentine circuit at the first bend for separating the tip from the first bend and providing cooling thereof near the trailing edge.

Abstract: Apparatus for statically determinant mounting of a vane assembly in a gas turbine engine includes means for assuring contact support of the vane assembly in a predetermined number of identified locations. The vane assembly includes at least one vane extending between a radially outer nozzle band and a radially inner nozzle band. The radially outer nozzle band has axially directed load bearing elements on distal ends. The radially inner nozzle band has a radially inwardly oriented flange depending therefrom. The engine includes a radially outer support member positioned to engage the load bearing elements in the radially outer nozzle band when the vane assembly is in an operative position. A radially inner support member is incorporated in the engine for engaging the flange to axially restrain the vane assembly. The inner support member includes means for releasably connecting the flange thereto for supporting the vane assembly in radially and circumferential directions.