Westinghouse Electric Corporation

Siemens Westinghouse Power Corporation

Leroy D McLaurin

Kent Goran Hultgren

John P Donlan

Frank A Pisz

Oran Leroy Bertsch

David L Brown

Barton M Pepperman

Gregory Robert Gaul

George A Gergely

Perry Eugene Lowe

David Y Toy

John Derek Sizemore

Roland E Williams

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.

Vane segment support and alignment device

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. The second end of the cooling fluid supply pipe is mechanically coupled in fluid communication with the fluid supply conduit of the at least second connector box. A fluid return pipe for conducting a cooling fluid that has extracted heat from a hot turbine part is provided. The return pipe comprises a side wall defining a return flow channel with a first opening at a first end and second opening at a second end.

Cooling supply manifold assembly for cooling combustion turbine

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.

Turbomachine rotor with improved cooling

A turbine blade has a cooling air flow path specifically directed toward cooling the platform portion of the blade root. Two cooling air passages are formed in the blade root platform just below its upper surface. Each passage extends radially outward from an inlet that receives a flow of cooling air and then extend axially along almost the entire length of the platform. Each passage also has an outlet formed in the downstream face of the platform that allows the cooling air to exit the platform and enter the hot gas flow path. The passages are formed in portions of the platform that overhang the shank portion of root.

Gas turbine blade with cooled platform

An apparatus and method is provided for locking side entry blades, in a rotor, such as used in compressors, turbines and fans. The apparatus utilizes arcuate locking devices retained in a circumferential groove in the periphery of the rotor. Each locking device features a key which engages a keyway in the side of the blade root shank. Use of the locking devices does not require that the blades having abutting platforms.

Apparatus for locking side entry blades into a rotor

A fuel nozzle assembly having a fuel nozzle tip at one end of a fuel delivery tube and a supporting flange at the other end. An air delivery tube, also secured to the support flange, encloses the fuel delivery tube to define an annular air passage therebetween. An integral fuel nozzle/end cap engages the fuel and air tubes and provides passages for fuel flowing from the fuel delivery tube and air flowing from the air delivery tube. Biasing means exerts an axial force on the air delivery tube to tighten the engagement of the tubes into an air-tight fit.

Fuel nozzle assembly for a gas turbine engine

Methods and apparatus for vane segment alignment and support in a combustion turbine. The vane segment alignment device is comprised of a rotatable, eccentric bushing and pin which is inserted into a slot of the vane segment. The eccentric bushing is further comprised of a cover plate which is peened to a splined torque plate thus holding the eccentric bushing in place against the vane segment but allowing for fine adjustments of the alignment of the vane segments. The vane segment support and alignment device provides for efficient and economical adjustment of the vane segments especially in electric generating plants where combustion turbines undergo high peak load operation. Additionally, the vane segment support and alignment device transfers torques and moments generated by aerodynamic flow from the vane segments to an inner cylinder thereby reducing the amount of misalignment due to aerodynamic drag.

Method and apparatus for vane segment support and alignment in

The invention comprises a retrofit turbine blade cooling apparatus for replacing non-cooled turbine blades in presently existing combustion turbines. The cooling apparatus comprises a turbine blade structured for fluid cooling and a sealing apparatus structured to cooperate with a root portion of the turbine blade and a subadjacent portion of a turbine disc to force cooling fluid into the turbine blade. Use of the cooling apparatus requires no modification or disassembly of the rotor assembly.

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Winter Springs, FL, United States of America

Leroy D McLaurin