TURBINE ARRANGEMENT AND GAS TURBINE ENGINE

• US 20130189110A1
• Filed: 09/19/2011
• Published: 07/25/2013
• Est. Priority Date: 09/29/2010
• Status: Active Grant

• Current Assignee: Siemens Energy Global GmbH & Co. KG (Siemens AG)
• Original Assignee: Siemens AG
• Inventors: Batt, Stephen, Mugglestone, Jonathan
• Granted Patent: US 9,238,969 B2
• Time in Patent Office: Days
• US Class Current: 416/219.R
• CPC Class Codes: F01D 5/30 Fixing blades to rotors; Blade roots ; Blade spacers
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2240/81 Cooled platforms
• CPC Class Codes: F05D 2260/201 by impingement of a fluid

Abstract

A turbine arrangement includes first and second platforms forming a section of a main fluid path, aerofoils, and an impingement plate. Each aerofoil extends from the first to the second platform. The second platform has a surface opposite to the main fluid path with recesses surrounded by a raised edge, which provides support for the mountable impingement plate. The edge is formed as a first closed loop surrounding a first recess and further surrounding a first aperture of a first aerofoil and as a second closed loop surrounding a second recess and further surrounding a second aperture of a second aerofoil. A portion of the edge defines a continuous barrier between the first recess and the second recess for blocking cooling fluid. The barrier forms a mating surface for a central area of the impingement plate.

Claims

1-13. -13. (canceled)

14. A turbine arrangement, comprising:

a first platform and a second platform, the first and second platform forming a section of a main fluid path;

a plurality of aerofoils, each of the plurality of aerofoils extending between the first platform and the second platform;

an impingement plate;

wherein the second platform has a surface opposite to the main fluid path with a plurality of recesses, the recesses surrounded by a raised edge, the edge providing a support for the mountable impingement plate,

wherein the edge is formed

as a first closed loop surrounding a first recess of the plurality of recesses and further surrounding a first aperture of a first aerofoil of the plurality of aerofoils, and

as a second closed loop surrounding a second recess of the plurality of recesses and further surrounding a second aperture of a second aerofoil of the plurality of aerofoils,

such that a portion of the edge defines a continuous barrier between the first recess and the second recess for blocking cooling fluid, and

such that the barrier forms a mating surface for a central area of the impingement plate, and

wherein

the first aperture has an elevated first rim which is configured with a height less than a height of the edge, and/or the second aperture has an elevated second rim which is configured with a height less than a height of the edge.

15. The turbine arrangement according to claim 14, wherein the edge has a flat surface, wherein the flat surface is located in a substantially cylindrical plane to form a mating surface for the impingement plate.

16. The turbine arrangement according to claim 14, wherein the first platform, the second platform and the plurality of aerofoils are built as a single piece turbine nozzle guide vane segment.

17. The turbine arrangement according to claim 14, wherein the first recess comprises at least one first aperture for cooling an interior of the first aerofoil and/or the second recess comprises at least one second aperture for cooling an interior of the second aerofoil.

18. The turbine arrangement according to claim 14, wherein

the first platform configured substantially is in form of a section of a first cylinder and the second platform configured substantially is in form of a section of a second cylinder, the second cylinder being arranged co-axially to the first cylinder about an axis, and

the first and the second platforms each has an axial dimension and a circumferential dimension.

19. The turbine arrangement according to claim 18, wherein the edge comprises a first elevation in circumferential direction, a second elevation in circumferential direction, a third elevation in axial direction and a fourth elevation in axial direction, all forming a mating surface for a border area of the impingement plate.

20. The turbine arrangement according to claim 18, wherein the barrier being directed substantially in axial direction.

21. The turbine arrangement according to claim 20, wherein the barrier comprises a bend, the bend being substantially parallel to an orientation of the first aerofoil and/or of the second aerofoil.

22. The turbine arrangement according to claim 18, wherein the second platform comprises a first flange in direction of a first axial end of the second platform and a second flange in direction of a second axial end of the second platform, the barrier substantially spanning between the first flange and the second flange.

23. The turbine arrangement according to claim 14, wherein the edge provides the only support to the impingement plate.

24. A gas turbine engine, comprising:

at least one guide vane ring comprising a plurality of turbine arrangements according to claim 14,

such that the turbine arrangements form together an annular fluid path for a main fluid flow.

25. The gas turbine engine according to claim 24, wherein

a first space defined by the first recess and an opposing impingement plate is in fluid communication with a hollow body of the first aerofoil, and

a second space defined by the second recess and the opposing impingement plate is in fluid communication with a hollow body of the second aerofoil.

26. The gas turbine engine according to claim 25, wherein the first space and/or the second space are free of pas-sages through the second platform into the main fluid path.