Siemens Energy, Inc.

Florida Turbine Technologies, Inc.

United Technologies Corporation

William W Pankey

Jack W Wilson

Richard Colin Charron

Clinton A Mayer

Andrew Carlson

Benjamin G Hettinger

Matthew D Montgomery

Andreas Sadil

Nicholas F Martin, Jr

Paul G Hicks

Walter Marussich

Kenneth K Landis

Gary D Snyder

Marco Claudio Pio Brunelli

Sameer A Khan

Beatriz Suarez-Crosse

An arrangement for a gas turbine engine includes a combustor for producing a working medium by combustion of a mixture of fuel and an oxidant, a turbine section comprising a stationary vane carrier on which a first row of stationary vanes is arranged, and a transition duct for leading the working medium from the combustor to the turbine section. The transition duct has a forward end that adjoins the combustor and an aft end that adjoins the stationary vane carrier. The transition duct has a transition duct axis extending from the forward end to the aft end along a straight line. The transition duct axis is normal to a vane axis of a stationary vane in the first row of stationary vanes.

Transition duct arrangement in a gas turbine engine

In a method for installation of a transition duct in a gas turbine engine, a guide structure is positioned that extends in an inclined direction with respect to a gas turbine axis. At least a portion of the guide structure is disposed between a turbine section and a combustor section of the gas turbine engine. The transition duct is engaged with the guide structure such that the transition duct is movable along the guide structure. Motion is imparted to the transition duct along the guide structure in a forward-to-aft direction, to move the transition duct to an installed position in which an aft end of the transition duct is aligned for attachment to a forward face of a stator component of the turbine section.

Method and tool for installation of a transition duct

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 duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.

Gas flow path for a gas turbine engine

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

A structural support system is provided in a can annular gas turbine engine having an arrangement including a plurality of integrated exit pieces (IEPs) forming an annular chamber for delivering gases from a plurality of combustors to a first row of turbine blades. A bracket structure is connected between an IEP and an inner support structure on the engine. The bracket structure includes an axial bracket member attached to an IEP and extending axially in a forward direction. A transverse bracket member has an end attached to the inner support structure and extends circumferentially to a connection with a forward end of the axial bracket member. The transverse bracket member provides a fixed radial position for the forward end of the axial bracket member and is flexible in the axial direction to permit axial movement of the axial bracket member.

Structural support bracket for gas flow path

An apparatus for supporting an aft portion of a transition duct in a gas turbine engine includes a transition aft frame that engages with an annular shaped stator component disposed in a turbine section of the gas turbine engine. The transition aft frame includes radially inner and outer panels and circumferentially spaced first and second side panels connecting the inner and outer panels. A forward face of the stator component includes first and second connection points circumferentially spaced apart. The transition aft frame includes first and second attachment structures that respectively engage with the first and second connection points when the transition duct is aligned axially with the stator component. The first and second attachment structures are spaced apart in a manner effective to transfer moment load from the first and second attachment structures to the first and second side panels respectively.

Apparatus and method incorporating a transition AFT support for a gas turbine engine

An exit piece () with an inlet throat () that conducts a combustion gas flow (A) in a path () from a combustor () to an annular chamber () that feeds the first blade section () of a gas turbine (). The exit piece further includes an outlet portion () that forms a circumferential segment of the annular chamber. The outlet portion interconnects with adjacent outlet portions by hinges (A,B,A,B). Each hinge may have a hinge axis (A,B) parallel to a centerline () of the turbine. Respective gas flows (A) are configured by an assembly () of the exit pieces to converge on the feed chamber () into a uniform helical flow that drives the first blade section with minimal circumferential variations in force.

Gas turbine combustor exit piece with hinged connections

A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system is provided within the panel and includes a cooling fluid supply trench having an open top portion and extending radially inwardly from a central recessed portion of the panel. The cooling system further includes a plurality of cooling fluid passages extending from the cooling fluid supply trench to a leading edge and/or a trailing edge of the panel. The cooling fluid passages receive cooling fluid from the cooling fluid supply trench, wherein the cooling fluid provides convective cooling to the panel as it passes through the cooling fluid passages.

Ring segment with cooling fluid supply trench

A compressor stator vane and rotor blade tip clearance control assembly in which a plurality of stator vane segments each with vanes extending inward are connected to an annular sync ring through eccentric cranks so that circumferential movement of the sync ring will produce radial displacement of the vane segments and control the clearance between the blade tips. An actuator piston is rigidly fixed to the sync ring and forms an actuator chamber with stationary actuator housing. Bleed off pressure from one of the compressor stages is used to move the actuator piston, which moves the sync ring to radially displace the vane segments.

Vane segment tip clearance control

A variable inlet guide vane assembly for a gas turbine engine, where the guide vanes are pivotably connected to a sync ring that is contained within an annular groove within the casing so that leakage through holes in the casing is minimized. The guide vanes include a slider mechanism on one of the ends that will allow for both an axial and a rotational movement of the guide vane pin when the guide vanes pivot about a fixed pin on an opposite end of the guide vanes. A round rotary vane actuator with a height much less than a diameter is mounted outside of the casing and connects to the sync ring through a driving linkage.

Variable inlet guide vane assembly

A gas turbine engine air valve assembly has first and second valving elements. The second element is rotatable about a first axis relative to the first element. The rotation controls a flow of air through the first and second elements. An actuator is coupled by a linkage to the second element. The linkage includes a spindle having a first portion coupled to the actuator to rotate the spindle about a second axis. A guided spherical bearing couples a second portion of the spindle to the second element.

Gas turbine engine air valve assembly

A variable inlet guide vane assembly for a gas turbine engine, where the guide vanes are pivotably connected to a sync ring that is contained within an annular groove within the casing so that leakage through holes in the casing is minimized. The guide vanes include a slider mechanism on one of the ends that will allow for both an axial and a rotational movement of the guide vane pin when the guide vanes pivot about a fixed pin on an opposite end of the guide vanes. a round rotary vane actuator with a height much less than a diameter is mounted outside of the casing and connects to the sync ring through a driving linkage.

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Palm Beach Gardens, FL, United States of America

William W Pankey