Abstract: A platform cooling arrangement in a turbine rotor blade having a platform that includes an interior cooling passage formed therein. The platform cooling arrangement may include: a main plenum residing just inboard of the planar topside and extending from an aft position to a forward position within one of the pressure side and the suction side of the platform, the main plenum having a longitudinal axis that is approximately parallel to the planar topside; a supply plenum that extends between the main plenum and the interior cooling passage; and a plurality of cooling apertures, each cooling aperture extending from one of the pressure side and the suction side slashface to a connection with the main plenum.

Abstract: A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage that in operation, includes at least a high-pressure coolant region and a low-pressure coolant region, and wherein the platform includes a platform underside. The platform cooling arrangement may include: a plate that comprises a plate topside; a channel formed on the plate topside, the channel comprising an upstream end and a downstream end, and being open through the plate topside such that, upon attaching the plate to the platform, the platform underside comprises a channel ceiling; a high-pressure connector that connects the upstream end of the channel to the high-pressure coolant region of the interior cooling passage; and a low-pressure connector that connects the downstream end of the channel to the low-pressure coolant region of the interior cooling passage.

Abstract: A platform cooling arrangement in a turbine rotor blade having a platform, wherein the rotor blade includes an interior cooling passage, and wherein, in operation, the interior cooling passage comprises a high-pressure coolant region and a low-pressure coolant region, and wherein the platform includes a platform underside. The platform cooling arrangement may include: a first plate that resides inboard and in spaced relation to the platform underside and forming a first plenum; a second plate that resides inboard and in spaced relation to the first plate, the second plate forming a second plenum. The second plenum includes an inlet channel that connects to the high-pressure coolant region of the interior cooling passage, and the first plenum includes an outlet channel that connects to the low-pressure coolant region of the interior cooling passage.

Abstract: A platform cooling configuration in a turbine rotor blade that includes platform slot formed through at least one of the pressure side slashface and the suction side slashface; a removably-engaged impingement insert that separates the platform into two radially stacked plenums, a first plenum that resides inboard of a second plenum; a high-pressure connector that connects the first plenum to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the second plenum to the low-pressure coolant region of the interior cooling passage.

Abstract: A gas turbine inner flow path cover piece for a gas turbine a first turbine wheel and a second turbine wheel is provided is provided. The gas turbine inner flow path cover piece can include a main body having an first surface and a second surface, side pieces disposed on the first surface of the main body and mating pairs disposed on the second surface of the main body.

Abstract: A machine and a seal assembly for a machine having a rotating shaft, a wheel coupled to the rotating shaft, the wheel including a bucket coupled to the wheel comprising a seal that extends along a side of the bucket and the wheel, covering an interface there between.

Abstract: A gas turbine and a seal assembly for a machine having a rotating shaft, a wheel coupled to the rotating shaft, the wheel including a bucket coupled to the wheel comprising a coverplate that is fastened to the wheel and the bucket and a seal positioned between the coverplate and the wheel and the bucket.

Abstract: In one embodiment, a coverplate may be configured to axially overlay a plurality of blade retaining slots within a wheel post of a rotor wheel. The coverplate may include a tab for radially securing the coverplate within a complementary groove of the rotor wheel and an aperture configured to align with a corresponding aperture of the turbine wheel to receive a fastener for axially securing the coverplate to the rotor wheel.