Granted Patent B2

US 9,238,969 · App. 13/876,595 · Granted Jan 19, 2016

Abstract

Claims (47)

1. A turbine assembly, comprising:

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

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

an impingement plate;

wherein the second platform has a surface opposite to the main fluid path with a plurality of recesses,

wherein the plurality of the recesses is surrounded by a raised edge,

wherein the raised edge provides a support for the mountable impingement plate,

wherein the raised edge includes

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

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

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

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

wherein at least one of:

the first aperture has an elevated first rim which is configured with a height less than a height of the raised edge, and

the second aperture has an elevated second rim which is configured with a height less than the height of the raised edge.

2. The turbine assembly according to claim 1 , wherein the raised edge has a flat surface, wherein the flat surface is located in a cylindrical plane to form a mating surface for the impingement plate.

3. The turbine assembly according to claim 1 , wherein the first platform, the second platform and the plurality of the aerofoils are integral in a single piece turbine nozzle guide vane segment.

4. The turbine assembly according to claim 1 , 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.

5. The turbine assembly according to claim 1 , wherein

the first platform is configured in form of a section of a first cylinder and the second platform is configured 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.

6. The turbine assembly according to claim 5 , wherein the raised 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,

wherein the first elevation, the second elevation, the third elevation and the fourth elevation form a mating surface for a border area of the impingement plate.

7. The turbine assembly according to claim 5 , wherein the barrier is directed in axial direction.

8. The turbine assembly according to claim 7 , wherein the barrier comprises a bend, the bend being parallel to an orientation of at least one of the first aerofoil and of the second aerofoil of the plurality of the aerofoils.

9. The turbine assembly according to claim 5 , 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.

10. The turbine assembly according to claim 1 , wherein the raised edge only provides the support to the impingement plate.

11. A gas turbine engine, comprising:

at least one guide vane ring; and

a turbine assembly, comprising:

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

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

an impingement plate;

wherein the second platform has a surface opposite to the main fluid path with a plurality of recesses,

wherein the plurality of the recesses is surrounded by a raised edge,

wherein the raised edge provides a support for the mountable impingement plate,

wherein the raised edge includes

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

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

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

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

wherein at least one of the first aperture has an elevated first rim which is configured with a height less than a height of the raised edge, and the second aperture has an elevated second rim which is configured with a height less than the height of the raised edge;

wherein the at least one guide vane ring and the turbine assembly define an annular fluid path for a main fluid flow.

12. The gas turbine engine according to claim 11 , 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 of the plurality of the aerofoils, 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 of the plurality of the aerofoils.

13. The gas turbine engine according to claim 12 , wherein at least one of the first space and the second space are free of passages through the second platform into the main fluid path.

Assignments (6)