Abstract: A support and alignment assembly for supporting and aligning a vane segment is provided. The support and alignment assembly comprises a torque plate which defines an opening for receiving an eccentric pin and a locking end member for receiving a lock socket member. An eccentric pin adjustably supported by the torque plate opening for supporting and aligning a vane segment is provided. A lock socket member adapted to securely receive the eccentric pin and rotated therewith, and adjustably engage the torque plate locking end is provided. The lock socket member receives the eccentric pin, such that when the eccentric pin is adjusted to align the vane segment, the lock socket member engages the torque plate locking end to secure the vane segment in the desired position.

Abstract: A cooling manifold assembly for cooling combustion turbine components is provided. The manifold assembly comprises at least a first and second connector box. Each one of the first and second two connector boxes comprises a housing. A fluid supply conduit and return conduit are securely coupled with the housing. The fluid supply conduit is adapted to be in fluid communication with a cooling fluid for cooling a hot turbine part. The return conduit is adapted to be in fluid communication with a cooling fluid that has extracted heat from a turbine hot part. A cooling fluid supply pipe for supplying a cooling fluid to the first and second connector boxes is provided. The supply pipe comprises a side wall that defines a coolant flow channel with a first opening at a first end, and a second opening at a second end. The first end of the fluid supply pipe is mechanically coupled in fluid communication with the fluid supply conduit of the first connector box.

Abstract: A gas turbine rotor has an essentially closed loop cooling air scheme in which cooling air drawn from the compressor discharge air that is supplied to the combustion chamber is further compressed, cooled, and then directed to the aft end of the turbine rotor. Downstream seal rings attached to the downstream face of each rotor disc direct the cooling air over the downstream disc face, thereby cooling it, and then to cooling air passages formed in the rotating blades. Upstream seal rings attached to the upstream face of each disc direct the heated cooling air away from the blade root while keeping the disc thermally isolated from the heated cooling air. From each upstream seal ring, the heated cooling air flows through passages in the upstream discs and is then combined and returned to the combustion chamber from which it was drawn.