Impingement cooling of turbine blades or vanes

• US 9,863,255 B2
• Filed: 11/22/2012
• Issued: 01/09/2018
• Est. Priority Date: 02/15/2012
• Status: Active Grant

• Current Assignee: Siemens AG
• Original Assignee: Siemens AG
• Inventors: Mugglestone, Jonathan
• Primary Examiner(s): Younger, Sean J
• Application Number:
  US14/373,873
• Publication Number:
  US 20150016973A1
• Time in Patent Office: 1,874 Days
• Field of Search: 415115
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F01D 9/02 Nozzles; Nozzle boxes; Stator blades; Guide conduits , e.g. individual nozzles nozzle boxes F01D9/047
• CPC Class Codes: F05D 2260/201 by impingement of a fluid

Abstract

A turbine assembly having a hollow aerofoil and impingement device, the aerofoil having a first side wall from leading to trailing edge and a cavity arranged a distance to an inner surface of the cavity for impingement cooling and a flow channel for cooling medium from the leading to trailing edge, the impingement device has first and second pieces arranged side by side, the second piece downstream of the first forming a first flow passage providing passage from one side of the aerofoil towards an opposite side. A blocking element is arranged in the flow channel between the second piece and first side wall at a suction side for blocking flow of cooling medium from leading to trailing edge denying access to a section of the flow channel downstream of the blocking element while directing cooling medium in the first flow passage away from the suction side towards pressure side.

Claims

1. A turbine assembly comprising:

a basically hollow aerofoil and at least one impingement device,

wherein the hollow aerofoil comprises at least one first side wall extending from a leading edge towards a trailing edge of the hollow aerofoil, and at least one cavity in which in an assembled state of the at least one impingement device in the hollow aerofoil the at least one impingement device is arranged;

at a predetermined distance from an inner surface of the at least one cavity for impingement cooling of the inner surface; and

to form a flow channel for a cooling medium extending from the leading edge towards the trailing edge, and

wherein the at least one impingement device comprises a first piece and a second piece arranged side by side in an axial direction from the leading edge to the trailing edge, with the first piece located towards the leading edge and the second piece located towards the trailing edge, and with an axial distance therebetween that forms a first flow passage that provides a passage from one side of the hollow aerofoil towards an opposite side of the hollow aerofoil, and

at least one first blocking element arranged in the flow channel between a side of the second piece that is closer to the leading edge than to the trailing edge and the at least one first side wall of the hollow aerofoil, wherein the at least one first side wall comprises a suction side wall of the hollow aerofoil, and wherein the at least one first blocking element is configured to block a flow of cooling medium in a direction from the leading edge to the trailing edge of the hollow aerofoil, thereby denying the flow of cooling medium direct access to a section of the flow channel downstream of the at least one first blocking element while directing the flow of cooling medium into the first flow passage away from the suction side wall towards a pressure side wall of the hollow aerofoil, wherein the flow of cooling medium then flows directly from the first flow passage axially toward the trailing edge between the second piece and the pressure side wall.

2. The turbine assembly according to claim 1,

wherein the at least one first blocking element extends at least partially along a span of the at least one impingement device.

3. The turbine assembly according to claim 2,

wherein the at least one first blocking element extends substantially completely along the span of the at least one impingement device.

4. The turbine assembly according to claim 1,

wherein the at least one first blocking element is formed integrally with the at least one impingement device.

5. The turbine assembly according to claim 1,

further comprising at least one further blocking element arranged in the flow channel between the at least one impingement device and at least one further side wall of the hollow aerofoil.

6. The turbine assembly according to claim 5,

wherein the at least one further side wall comprises the pressure side wall of the hollow aerofoil, and wherein the at least one further blocking element is arranged between the second piece of the at least one impingement device and the pressure side wall of the hollow aerofoil.

7. The turbine assembly according to claim 1,

wherein the first flow passage comprises radial ends and wherein at least one radial end of the first flow passage is sealed in a hermetically sealed manner by a sealing element.

8. The turbine assembly according to claim 7,

wherein the sealing element is formed integrally with the at least one impingement device.

9. The turbine assembly according to claim 1,

wherein the hollow aerofoil comprises a centre line extending from the leading edge to the trailing edge, wherein the first flow passage is arranged basically perpendicular to the centre line of the hollow aerofoil.

10. The turbine assembly according to claim 1,

wherein the at least one impingement device comprises a third piece, wherein in the assembled state in the hollow aerofoil the third piece is disposed between the second piece and the pressure side wall, and the second piece and the third piece are arranged with a distance in respect to each other forming at least one further flow passage therebetween, and wherein the cooling medium flows from the first flow passage axially toward the trailing edge in the at least one further flow passage and then out through the trailing edge.

11. The turbine assembly according to claim 10,

wherein the at least one further flow passage is arranged basically along a centre line of the hollow aerofoil extending from the leading edge to the trailing edge.

12. The turbine assembly according to claim 10,

wherein the second piece is arranged toward the suction side wall of the hollow aerofoil and the third piece is arranged towards the pressure side wall of the hollow aerofoil.

13. The turbine assembly according to claim 1,

wherein the hollow aerofoil is a turbine blade or vane.

14. The turbine assembly according to claim 1, wherein the cooling medium flows from the first flow passage axially toward the trailing edge between the second piece and the pressure side wall and then out through the trailing edge.