General Electric Company

Jonathan Munshi

Bernard Arthur Couture, Jr

Abdul-Azeez Mohammed-Fakir

Kamlesh Mundra

Daniel Ross Predmore

Gene David Palmer

John Cleland Lavash

Eric J Brambani

William David Moore

John Cao

A method and apparatus for assembling a steam turbine is provided. The method includes performing a finite element analysis to determine a cross-section of a sealing member, positioning the sealing member in a leakage path defined between an inner casing and an outer casing such that a leakage flow activates the sealing member. The apparatus includes a groove defined in a channel, a divider positioned in the channel such that a gap defined between the divider and the channel defines a leakage path, and a sealing member that extends at least partially within the groove and positioned to substantially prevent a flow though the leakage path.

Method and apparatus for rotating machine main fit seal

A turbine wheel including a male dovetail configuration about substantially an entire periphery of the wheel, interrupted by a notch formed by removal of portions of the male dovetail at a bucket loading location on the periphery of the wheel. A closure bucket adapted for loading onto the wheel includes a root portion, a platform and airfoil, the root portion formed with a pair of radially inwardly extending laterally spaced tangs, the tangs each formed with a pair of radially aligned retaining pin holes, the retaining pin holes located radially inwardly of the male dovetail configuration.

Steam turbine closure bucket attachment

Upper and lower diaphragms of a steam turbine have mating flanges forming a horizontal midline joint interface. Each flange has a groove which registers with a corresponding groove in the opposite flange. A composite woven tubular seal is provided in the mating grooves. The seal comprises an inner woven metal core surrounded by an annular silica fiber layer, in turn surrounded by a metal foil with an outer protective covering of a braided stainless steel. Upon joining the diaphragms to one another, the compliant seal generally conforms to a maximum to the shape of the grooves, maintaining a seal between the diaphragms along the horizontal midline joint.

Composite tubular woven seal for steam turbine diaphragm horizontal joint interfaces

An integral aft seal for sealing the interface between a gas turbine transition piece and first stage nozzle exhibits sufficient variable thickness to adjust for relative component movement. The seal comprises a contiguous material having opposing planar faces and stiffeners attached at each of the faces. The contiguous material has corrugations to provide variable thickness. The stiffeners are attached to the planar faces of the contiguous material and generally have the same planar shape as the seal. Flexibility in the thickness dimension due to the corrugations biases the stiffeners away from one another and into contact with the turbine components. The aft seal is affixed to the transition piece by an attachment structure that eliminates relative movement between the seal and the transition piece to thereby eliminate wear.

Integral aft seal for turbine applications

A fuel nozzle tip construction for a dual fuel gas turbine includes a centrally arranged metal liquid fuel tip having a liquid fuel flow passage therein; a radially outer ceramic atomizing air tip surrounding the liquid fuel tip in radially spaced and substantially concentric relationship such that an atomizing air passage is formed therebetween; a radially outermost metal gas fuel tip surrounding the atomizing air tip in radially spaced and substantially concentric relationship such that a gas fuel passage is formed therebetween; a metal retaining cup radially between the atomizing air tip and the gas fuel tip; and a pair of compliant interface elements, one interposed between the gas tip and the atomizing air tip at a forward end of the atomizing air tip, and the other interposed between the retaining cup and the atomizing air tip at a rearward end of the atomizing air tip.

Ceramic tip and compliant attachment interface for a gas turbine fuel

A fuel nozzle (10) for a gas turbine includes an annular nozzle body (12) having a forward end with interior and exterior surfaces; a gas tip (14) having a forward fuel discharge end and a rearward mounting end, the rearward mounting end at least partially receivable in the forward end of the nozzle body (12); a resilient seal (38) inserted between the nozzle body (12) and the gas tip (14); a seal ring (26) mounted on the rearward mounting end of the gas tip (14), adapted to axially compress the resilient seal (38) when the seal ring (26) is engaged with the nozzle body (12); and a locking sleeve (48) on the exterior surface of the nozzle body (12) for locking the seal ring ( 26 ) to the gas tip ( 14 ).

Gas turbine fuel nozzle seal

The liner stop assembly includes a flow sleeve stop, a liner stop, an adjuster, a lock plate and a bolt. The flow sleeve stop and liner stop have radial projections which axially butt one another upon insertion of the liner into the flow sleeve. The flow sleeve stop and liner stop have tapered surfaces which, in assembly, converge in a downstream axial direction for receiving complementary tapered surfaces on the adjuster. The adjuster includes lateral extensions for coarsely aligning the adjuster between the flow sleeve and liner stops. When bolt is screw-threaded in the tapped bore of the flow sleeve stop, the wedging action of the tapered surfaces of the adjuster and the flow sleeve and liner stops serves to radially adjust the liner relative to the flow sleeve.

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Scotia, NY, United States of America

Jonathan Munshi