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

Patent metadata

Field	Value
Publication number	US-9803487-B2
Application number	US-201415318078-A
Country	US
Kind code	B2
Filing date	Jun 26, 2014
Priority date	Jun 26, 2014
Publication date	Oct 31, 2017
Grant date	Oct 31, 2017

Abstract

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.

First claim

We claim:

1. A transition duct system for routing gas flow in a combustion turbine subsystem that includes a first stage blade array having a plurality of blades extending in a radial direction from a rotor assembly for rotation in a circumferential direction, the circumferential direction having a tangential direction component, an axis of the rotor assembly defining a longitudinal direction, and at least one combustor located longitudinally upstream of the first stage blade array and located radially outboard of the first stage blade array, the transition duct system comprising:
a first transition duct body having an internal passage extending between an inlet and an outlet;
wherein the outlet of the first transition duct body is offset from the inlet of the first transition duct body in the longitudinal direction and the tangential direction;
wherein the outlet of the first transition duct body is formed from a radially outer side opposite to a radially inner side, and the radially outer side and the radially inner side are coupled together with opposed first and second side walls;
a second transition duct body having an internal passage extending between an inlet and an outlet;
wherein the outlet of the second transition duct body is offset from the inlet of the second transition duct body in the longitudinal direction and the tangential direction;
wherein the outlet of the second transition duct body is formed from a radially outer side opposite to a radially inner side, and the radially outer side and the radially inner side are coupled together with opposed first and second side walls;
wherein the first side wall of the first transition duct body intersects with the second side wall of the second transition duct body forming a converging flow joint; and
a converging flow joint insert extending through an outer wall of the converging flow joint and positioned at a downstream end of the converging flow joint to form a trailing edge of the converging flow joint,
wherein an internal cooling system within the converging flow joint insert comprises at least one internal cooling chamber having an internal volume less than one half of a volume contained within outer walls forming the converging flow joint insert,
at least one exhaust orifice extending from an inlet at the at least one internal cooling chamber through an outer wall forming a first section of the converging flow joint insert, wherein the first section has a uniform thickness from a first side of the converging flow joint insert to a second side of the converging flow joint insert opposite to the first side of the converging flow joint insert, and further comprising at least one exhaust orifice extending from an inlet at the at least one internal cooling chamber through an outer wall forming a second section of the converging flow joint insert, wherein the second section extends from the first section and forms an outer downstream tip of the converging flow joint insert, wherein the second section has a nonuniform thickness with a thickness at the outer downstream tip being less than a thickness at an upstream edge of the second section.

2. A transition duct system for routing gas flow in a combustion turbine subsystem that includes a first stage blade array having a plurality of blades extending in a radial direction from a rotor assembly for rotation in a circumferential direction, the circumferential direction having a tangential direction component, an axis of the rotor assembly defining a longitudinal direction, and at least one combustor located longitudinally upstream of the first stage blade array and located radially outboard of the first stage blade array, the transition duct system comprising:
a first transition duct body having an internal passage extending between an inlet and an outlet;
wherein the outlet of the first transition duct body is offset from the inlet of the first transition duct body in the longitudinal direction and the tangential direction;
wherein the outlet of the first transition duct body is formed from a radially outer side opposite to a radially inner side, and the radially outer side and the radially inner side are coupled together with opposed first and second side walls;
a second transition duct body having an internal passage extending between an inlet and an outlet;
wherein the outlet of the second transition duct body is offset from the inlet of the second transition duct body in the longitudinal direction and the tangential direction;
wherein the outlet of the second transition duct body is formed from a radially outer side opposite to a radially inner side, and the radially outer side and the radially inner side are coupled together with opposed first and second side walls;
wherein the first side wall of the first transition duct body intersects with the second side wall of the second transition duct body forming a converging flow joint;
a converging flow joint insert extending through an outer wall of the converging flow joint and positioned at a downstream end of the converging flow joint to form a trailing edge of the converging flow joint;
an internal cooling system within the converging flow joint insert, the internal cooling system having an internal cooling chamber;
a converging flow joint insert receiver positioned at the converging flow joint and in which the converging flow joint insert is positioned,
wherein a body of the converging flow joint insert includes a first section with a uniform thickness from a first side of the converging flow joint insert to a second side of the converging flow joint insert opposite to the first side of the converging flow joint insert and a second section extending from the first section and forming an outer downstream tip of the converging flow joint insert, wherein the second section has a nonuniform thickness with a thickness at the outer downstream tip being less than a thickness at an upstream edge of the second section;
at least one exhaust orifice extending from an inlet at the internal cooling chamber through an outer wall forming the first section of the converging flow joint insert; and
at least one exhaust orifice extending from an inlet at the internal cooling chamber through an outer wall forming the second section of the converging flow joint insert.

3. A transition duct system for routing gas flow in a combustion turbine subsystem that includes a first stage blade array having a plurality of blades extending in a radial direction from a rotor assembly for rotation in a circumferential direction, the circumferential direction having a tangential direction component, an axis of the rotor assembly defining a longitudinal direction, and at least one combustor located longitudinally upstream of the first stage blade array and located radially outboard of the first stage blade array, the transition duct system comprising:
a first transition duct body having an internal passage extending between an inlet and an outlet;
wherein the outlet of the first transition duct body is offset from the inlet of the first transition duct body in the longitudinal direction and the tangential direction;
wherein the outlet of the first transition duct body is formed from a radially outer side opposite to a radially inner side, and the radially outer side and the radially inner side are coupled together with opposed first and second side walls;
a second transition duct body having an internal passage extending between an inlet and an outlet;
wherein the outlet of the second transition duct body is offset from the inlet of the second transition duct body in the longitudinal direction and the tangential direction;
wherein the outlet of the second transition duct body is formed from a radially outer side opposite to a radially inner side, and the radially outer side- and the radially inner side are coup

Assignees

• Siemens Energy Inc

Inventors

• Wiebe David J
• Carlson Andrew
• Stoker Kyle C

Classifications

• F01D9/00

  Stators · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F01D9/023 Primary

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title

• F05D2260/94

  Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] · CPC title

• F23R3/46

  Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings · CPC title