Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Andrew Carlson

William W Pankey

David James Wiebe

Andreas Heselhaus

Ross H Peterson

Markus Gill

Christian Gindorf

Robert Kunte

Marcel Schlösser

Kyle C Stoker

A rotor blade for a gas turbine, includes a blade extending in a radial direction, with a blade body having a peripheral wall with pressure-side and suction-side wall sections, a plate-shaped crown base connected to the peripheral wall in the region of the blade tip, and a sweep edge extending along the peripheral wall, the peripheral wall and the crown base defining a cavity in the blade body, the sweep edge being aligned on the outer side with the peripheral wall and protruding radially over the crown base, and cooling channels are embodied in the blade body, extending from the cavity to cooling fluid outlets provided in the sweep edge. At least one recess being formed in the front surface of the sweep edge, into which at least some of the cooling channels flow such that the cooling fluid outlets are entirely arranged in a bottom region of the recess.

Rotor blade for a gas turbine with a cooled sweep edge

An apparatus for attaching a transition duct to a turbine section of a gas turbine engine includes an annular shaped vane carrier that engages with a transition aft frame. The transition aft frame includes an outwardly extending clamp that is at least partially inserted into a radial recess of the vane carrier structure. A spacer is inserted into the recess. A first pair of mating surfaces is formed by a first end face of the spacer and an end face of the clamp and a second pair of mating surfaces is formed by a second end face of the spacer and a wall of the recess. At least one of the pairs of mating surfaces is inclined at an angle with respect to a radial plane of the vane carrier structure. A retention device secures the spacer to the vane carrier structure.

Method and apparatus for attaching a transition duct to a turbine section in a gas turbine engine

A transition duct system for routing a gas flow in a combustion turbine engine is provided. The transition duct system includes one or more converging flow joint inserts forming a trailing edge at an intersection between adjacent transition ducts. The converging flow joint insert may be contained within a converging flow joint insert receiver and may be disconnected from the transition duct bodies by which the converging flow joint insert is positioned. Being disconnected eliminates stress formation within the converging flow joint insert, thereby enhancing the life of the insert. The converging flow joint insert may be removable such that the insert can be replaced once worn beyond design limits.

Converging flow joint insert system at an intersection between adjacent transitions extending between a combustor and a turbine assembly in a gas turbine engine

A combustion turbine engine combustor section includes a plurality of annularly arrayed combustors housed within paired combustor portals of a combustor casing. Each combustor portal has a corresponding top hat cover having a peripheral flange. The paired combustor portals are formed in combustor housings having a figure eight-shaped sleeve wall planform. The paired adjoining combustor portals share a common Siamesed portion of the sleeve wall. A combustor portal mating surface is formed on an axial distal end of the sleeve wall, having a figure eight planform and defining a first array of fastener receiving apertures. A top hat cover retention bracket assembly having a composite planform conforming to the combustor portal mating surface planform and a second array of apertures that conform to the first array pattern apertures, is placed over the peripheral flanges of the paired combustor top hat covers and secured by top hat cover fasteners.

Combustion turbine with Siamesed wall paired combustor housings

A support arrangement () for a transition piece () of a gas turbine engine (). The support arrangement includes a mounting bracket () for the transition piece and a pin () supporting the mounting bracket in an interior () of the gas turbine engine and extending through an opening () in a casing () to an exterior () of the gas turbine engine. The support arrangement further includes a spherical washer () positioned between the pin and either the mounting bracket or the casing.

Support arrangement for a transition piece of a gas turbine engine

Combustor top hat covers are attached to midframe combustor portals with a lugged backing plate that interlocks with mating recesses formed in the corresponding midframe combustor portal. Exemplary embodiments utilize twist lock engagement of backing plate ring lugs under projecting tabs formed over a lug raceway recess in the combustor portal mating surface. The top hat cover is in turn fastened to the combustor portal by fasteners that engage corresponding threaded apertures formed in the backing plate.

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Jupiter, FL, United States of America

Andrew Carlson