Westinghouse Electric Corporation

John P Donlan

Leroy D McLaurin

William E North

Kent Goran Hultgren

Frank A Pisz

Jeffrey C Eddy

Alfred R Krauss

George A Gergely

David T Entenmann

Roland E Williams

A fuel nozzle assembly is provided having the capability of burning either gaseous or liquid fuel, or both simultaneously, along with steam injection. The nozzle has a nozzle body that is attached to a nozzle cap by inner, outer and middle sleeves. The sleeves form inner and outer concentric annular conduits between themselves for directing the flow of gaseous fuel and steam from the fuel and steam inlet ports to the outlet ports. In addition, the inner sleeve forms a central chamber in which an oil fuel nozzle is disposed. Radial passages in the nozzle body allow cooling air to flow over the oil nozzle and through the oil outlet port, thereby preventing coking at the nozzle tip. The fuel nozzle assembly is originally built, and the nozzle cap is replaced, by sliding the sleeves forward and aft on the assembly so as to gain access to the next innermost sleeve.

Gas turbine dual fuel nozzle assembly with steam injection capability

A gas turbine fuel nozzle assembly having a replaceable nozzle cap. The nozzle assembly is comprised of a base portion and a nozzle cap. The nozzle base is secured to a combustion system and contains inlet ports for receiving either gas and oil fuel or gas fuel and steam, depending on the nozzle assembly configuration. The nozzle cap has outlet ports for injecting either gas and oil fuel or gas fuel and steam. The nozzle cap is connected to the nozzle base by inner and outer sleeves that form an annular conduit by which the gas flows from an inlet port in the base to an outlet port in the cap. In addition, the inner sleeve, which has an expansion joint formed therein, forms a central cavity that either holds an oil spray nozzle or forms a steam passage, depending on the nozzle assembly configuration. The nozzle cap is detachably coupled to the base by first and second threaded joints formed in the inner and outer sleeves, respectively. A locknut presses a front portion of the outer sleeve against a rear portion of the outer sleeve to form a first secure, but detachable, joint. A lock tube pulls a front portion of the inner sleeve against a rear portion of the inner sleeve to form a second secure, but detachable, joint. Anti-rotation pins and seals are disposed in both the first and second joints.

Gas turbine fuel nozzle with replaceable cap

An apparatus and method are provided for aligning and supporting vane segments in the turbine section of a gas turbine. According to the invention, the vane segments are supported and aligned to an inner cylinder. The apparatus features a plate, having threaded holes, which is fixed to the inner cylinder. A threaded plug, having an eccentric hole, is threaded into each threaded hole in the plate. A pin, having flats and a chamfer formed at one end, is inserted into the eccentric hole in the plug. At assembly, the plug is rotated in the threaded hole and the pin is rotated in the eccentric hole until the pin enters a slot in the inner shroud of the vane segment. The pin supports and aligns the vane segment by bearing against a side of the slot. The plug is locked in place by a nut threaded onto the plug.

Apparatus and method for supporting a vane segment in a gas turbine

A seal is provided to prevent the recirculation of hot gas through an annular cavity formed between the outer flow liner of a diffuser and an exhaust cylinder in the exhaust section of a gas turbine. The seal is formed from a high temperature cloth, such as fiber glass, which is sandwiched between two layers of a fine wire mesh. The seal is comprised of a plurality of arcuate segments. Although the cloth has a rectangular shape when in its undeformed state, it takes an arcuate shape as a result of being crimped within inner and outer arcuate channels. The seal is retained by sliding the channels into circumferential grooves in the exhaust cylinder and outer flow liner. An expansion loop is formed in the seal to allow for differential expansion between the exhaust cylinder and the outer liner.

Recirculation seal for a gas turbine exhaust diffuser

A cooled turbine vane in a multistage gas turbine is cooled with a fluid and a major portion of the fluid is dissipated into the gas flow path. A minor portion is supplied to a seal housing and seal for cooling the seal housing and for providing sufficiently cool fluid to the seal. The vane has a hollow airfoil body fixedly attached to the seal housing via an inner shroud and to a blade ring via an outer shroud. An inlet inot the hollow interior of the airfoil body through the outer shroud is in flow communication with a source of coolant fluid. An outlet in the inner shroud is in flow communication with the seal and its housing. Ports in the airfoil body extending from its hollow interior are in flow communication with the gas flow path. In a preferred cooled turbine vane, the coolant fluid in the airfoil body flows through return bends with reduced stagnant zons and flow resistance for increasing the heat transfer across the surfaces of the airfoil body around the bends and for reducing the pressure drop in the bend areas. A bend at the inner shroud is adjacent the outlet and a bend adjacent the outer shroud is adjacent a port for flowing the coolant fluid out of the stagnant zones in the bends.

Cooled turbine vane

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

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

Locking structure for maintaining a set position in assembling an annular seal ring housing to a stationary inner shroud of an annular array of vane segments of a combustion turbine engine. This permits an adjustable assembly for obtaining concentricity between the seal and the adjacent rotor structure. Thus, the seal ring is mounted to the vane segments through an adjustable mounting arrangement that, upon assembly of the two, permits the seal ring to be aligned concentrically about the rotor. Once concentricity is obtained, the mounting components must be locked in such position to maintain such concentricity. The present invention provides a bracket attached to the adjustable mounting structure to lock it in the set position.

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Oviedo, FL, United States of America

John P Donlan