Siemens Energy, Inc.

Siemens Power Generation, Inc.

James Michael Zborovsky

Andreas J Heilos

Raymond Scott Nordlund

Robert W Dawson

Ricardo Ferreira Moraes

Bradley T Youngblood

Johan Hsu

Maz Sutcu

Andrew G McQuiggan

Andreas Johannes Heilos

A gas turbine transition duct apparatus is provided comprising first and second turbine transition ducts and a strip seal. The strip seal may comprise a sealing element and a spring structure.

Turbine transition duct apparatus

A transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The transition duct support system includes a transition support frame formed from a body positioned around a transition duct body at an outlet transition section. The transition support frame may include a first inner surface aligned with and positioned proximate to portion of the outlet transition section that is positioned at an oblique angle relative to the outer wall of the transition duct body to limit linear movement of the transition duct body in a first direction. The transition support frame may also include a second inner surface positioned at an oblique angle to limit linear movement of the transition duct body in a second direction opposite the first direction.

Transition support system for combustion transition ducts for turbine engines

The present invention is directed to a seal for sealing a gap between transition sections of adjacent can annular combustors in a turbine engine such that the seal is usable in applications for sealing pressure drops of 0.5 bar or greater. The seal includes a plate configured to extend between adjacent transition sections and the plate may have at least one perforation extending from the front surface of the plate to the rear surface of plate. The seal further includes a porous matrix formed from materials capable of withstanding turbine combustion gas temperatures, wherein a portion of the porous matrix may be fixedly attached to a surface of the plate.

Gas turbine: seal between adjacent can annular combustors

One embodiment of a transition-to-turbine seal () comprises a transition exit seal () adapted for fixed attachment to an exit rail () of a transition (), and a stage-1 seal (). The stage-1 seal () comprises an axial seal slot () comprising parallel walls () adapted to slidingly engage a first male member () of the transition exit seal (). The stage-1 seal () also comprises a radial seal slot () comprising parallel walls () adapted to slidingly engage a plate () of a row 1 vane segment (). The transition-to-turbine seal () thus provides both axial and radial freedom of movement. Materials and coatings for the transition exit seal () and the stage-1 seal () are selected to promote preferential wear of these components relative to wear of the surface of the row 1 vane segment (). Wear of the exit rail () is reduced or eliminated due to the noted fixed attachment.

Transition-to-turbine seal apparatus and kit for transition/turbine junction of a gas turbine engine

A seal usable to seal a transition in a can-annular combustion system of a turbine engine to a turbine vane assembly to direct exhaust gases through the turbine vane assembly. The seal may be formed from an elongated body extending along an outer edge of the transition and having first and second edges. The first edge of the seal may be attached to the transition, and the elongated body may extend away from the transition edge and contact a portion of the turbine vane assembly. The elongated body may flex during use without yielding or otherwise deforming.

Seal usable between a transition and a turbine vane assembly in a turbine engine

A replaceable section () of force-cooling tubing assembly () for attachment to a transition piece () of a gas turbine is comprised of two ends () fashioned for attachment by removable unions () to adjoining parts of a force-cooling tubing assembly. When assembled thereto to complete the assembly, the replaceable sectionprovides for fluid communication between a manifold () and the transition piece () for either the supply or return of cooling fluid. A transition piece () in combination with two such assemblies, one a supply assembly (), the other a return assembly (), comprises a field-installable transition piece assembly () that provides for rapid and easy installation. The features of the replaceable section () include a relatively inflexible bracing zone such as a bracing member () having a support structure such as a lateral plate () that extends to the transition piece (), a formed tubing bend () typically forming a U-bend, and optionally a second flexible component comprised of an inline flexible coupling ().

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Orlando, FL, United States of America

James Michael Zborovsky