Arrangement for a gas turbine combustion engine

Patent metadata

Field	Value
Publication number	US-10132175-B2
Application number	US-201415509987-A
Country	US
Kind code	B2
Filing date	Oct 7, 2014
Priority date	Oct 7, 2014
Publication date	Nov 20, 2018
Grant date	Nov 20, 2018

Abstract

An arrangement ( 10 ) for delivering gases from combustors ( 15 ) to a first row of blades. The arrangement ( 10 ) includes at least an upstream flow path ( 60 ) including an aft first side wall ( 64 ) and a downstream flow path ( 62 ) including a forward second side wall ( 66 ). A convergence junction trailing edge ( 40 ) is defined at a downstream terminal edge ( 41 ) of the first side wall ( 64 ), and the second side wall ( 66 ) converges toward the first side wall ( 64 ) in the direction of the convergence junction trailing edge ( 40 ). An impingement sheet structure ( 78 ) is located between and provides impingement cooling air to the first and second side walls ( 64, 66 ). Openings ( 88 ) provide a cooling air passage between the first and second side walls ( 64, 66 ) and provide a flow of post impingement air into the gas path at the convergence junction trailing edge ( 40 ).

First claim

What is claimed is:

1. An arrangement for delivering gases from a plurality of combustors of a can-annular gas turbine combustion engine to an annular outlet structure that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering a gas flow to a first row of blades, the arrangement is a tangential flow arrangement including at least an upstream flow path and a downstream flow path located circumferentially adjacent to each other, the downstream flow path including an aft first side wall and the upstream flow path including a forward second side wall;
a convergence junction trailing edge defined at a downstream terminal edge of the aft first side wall, and the forward second side wall converging toward the aft first side wall in the direction of the convergence junction trailing edge;
an impingement sheet structure located between and providing impingement cooling air to the aft first and forward second side walls;
wherein the aft first and forward second side walls each include a hot side exposed to the gas flow and an opposite cold side receiving the impingement cooling air from the impingement sheet structure, the cold side of the aft first side wall is located facing the cold side of the forward second side wall;
wherein the impingement sheet structure includes first and second sheet portions having inner surfaces engaged on the cold sides of the aft first and forward second side walls, respectively, wherein the first and second sheet portions extend to downstream ends and the first and second side walls meet at a wall apex adjacent to the convergence junction trailing edge;
one or more openings providing a cooling air passage between the aft first and forward second side walls and providing a flow of post impingement air into the gas flow at the convergence junction trailing edge; and
a post impingement is defined between the aft first and forward second side walls extending from the downstream ends of the sheet portions to the wall apex, and Post impingement air passes into the post impingement chamber prior to flowing through the cooling air passage.

2. The arrangement of claim 1 , including an open area between the cold sides of the aft first and forward second side walls, the open area being open to a combustor shell providing shell air as the impingement cooling air through impingement holes in the impingement sheet structure.

3. The arrangement of claim 1 , wherein the cold sides of the aft first and forward second side walls include ribs extending from planar surfaces, the ribs maintaining a spacing between the first and second sheet portions and the planar surfaces to define impingement chambers adjacent to the aft first and forward second side walls.

4. The arrangement of claim 1 , wherein a thickness of at least one of the at first and forward second side walls tapers to a reduced thickness along a length of the post impingement chamber to the convergence junction trailing edge.

5. An arrangement for delivering gases from a plurality of combustors of a can-annular gas turbine combustion engine to a first row of turbine blades, the arrangement being a tangential flow arrangement comprising a gas path cylinder, a cone, and an individual exit piece (IEP) for each combustor, wherein each IEP comprises a straight path portion for receiving a gas flow from a respective combustor via the cylinder and cone, and the IEP further includes a connection location, wherein each IEP connects to an adjacent IEP at the connection location of the adjacent IEP, and the connected IEPs define an annular outlet structure that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis, for delivering the gas flow to the first row of blades; wherein gases flow from respective combustors, through respective straight path portions, to the annular outlet structure;
each straight path portion defines a polygonal cross section forming a flow path comprising a radially outer wall opposite to a radially inner wall, and the radially outer and inner walls are coupled together with opposed forward and aft walls, the forward wall defining a continuous wall from an upstream end of the straight path portion to an exit end of the flow path;
adjacent straight path portions defining circumferentially adjacent upstream and downstream flow paths, wherein the aft wall of the downstream flow path defines a first side wall that terminates at a convergence junction trailing edge and the forward wall of the upstream flow path defines a second side wall that converges toward the first side wall in the direction of the convergence junction trailing edge;
an impingement sheet structure located between and providing impingement cooling air to the first and second side walls and comprising first and second sheet portions having inner surfaces engaged on the first and second sidewalls, respectively;
wherein the first and second sheet portions extend to downstream ends and the first and second side walls meet at a wall apex adjacent to the convergence junction trailing edge;
wherein the first and second side walls include ribs extending from Planar surfaces, the ribs maintaining a spacing between the first and second sheet portions and the planar surfaces to define impingement chambers adjacent to the first and second side walls;
one or more openings providing a cooling air passage between the first and second side walls and providing a flow of post impingement air into the gas flow at the convergence junction trailing edge; and
a post impingement chamber is defined between the first and second side walls extending from the downstream ends of the sheet Portions to the wall apex, and post impingement air passes into the post impingement chamber prior to flowing through the cooling air passage.

6. The arrangement of claim 5 , wherein the sheet portions have outer surfaces that are open to shell air provided as an air supply for combustion in the plurality of combustors, and the sheet portions have impingement holes for passage of shell air as the impingement cooling air against the first and second side walls.

7. The arrangement of claim 5 , wherein a thickness of at least one of the first and second side walls tapers to a reduced thickness along a length of the post impingement chamber to the convergence junction trailing edge.

8. The arrangement of claim 5 , wherein each of the first and second side walls include an elongated rib located adjacent to the post impingement chamber and having an elongated dimension extending in an upstream to downstream direction, and including a movable seal extending between the elongated ribs and defining an upstream end of the post impingement chamber.

9. The arrangement of claim 8 , including cooling air passages extending through each of the ribs and providing a flow of post impingement air from the impingement chambers to the post impingement chamber.

10. The arrangement of claim 8 , including film cooling holes defined through the first and second side walls and providing film cooling air from the impingement chambers to sides of the first and second side walls that are exposed to the gas flow.

11. The arrangement of claim 8 , herein a thickness of the first and second side walls tapers to a reduced thickness along a length of the post impingement chamber to the convergence junction trailing edge.

12. The arrangement of claim 5 , wherein a downstream portion of the second side wall is formed integral with the IEP that defines the downstream flow path including the first side wall, and the second side wall has a downstream edge that terminates upstream of a downstream edge of the first side wall.

Assignees

• Siemens Energy Inc

Inventors

• Little David A

Classifications

• F23R3/425

  Combustion chambers comprising a tangential or helicoidal arrangement of the flame tubes · CPC title

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F05D2250/25

  helical · 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