Impingement cooling of turbine blades or vanes

Patent metadata

Field	Value
Publication number	US-9650899-B2
Application number	US-201214126440-A
Country	US
Kind code	B2
Filing date	Jun 11, 2012
Priority date	Jun 27, 2011
Publication date	May 16, 2017
Grant date	May 16, 2017

Abstract

A turbine assembly includes a basically hollow aerofoil. A wall segment may be arranged at a side of the aerofoil. An insertion aperture in the wall segment provides access to the aerofoil and an impingement tube may be inserted via the insertion aperture into the aerofoil to be located within the aerofoil and extend at least in a span wise direction of the aerofoil. A protrusion section of the impingement tube may extend in a direction basically perpendicular to the span wise direction over an edge of the insertion aperture. The protrusion section may be overlapped by at least a part of the wall segment. Adjacent to the protrusion section, an overlap section of the impingement tube is arranged to abut the edge of the insertion aperture. The protrusion section and the overlap section may be formed integrally with each other in one piece.

First claim

The invention claimed is:

1. A turbine assembly comprising
a basically hollow aerofoil,
at least a wall segment arranged at a side of the hollow aerofoil oriented basically perpendicular to a span wise direction of the hollow aerofoil and with at least an insertion aperture in said at least one wall segment providing access to the hollow aerofoil and at least an impingement tube to be inserted via the insertion aperture into the hollow aerofoil to be located within the hollow aerofoil and extending in at least the span wise direction of the hollow aerofoil,
wherein in an assembled state of the impingement tube in the hollow aerofoil at least a protrusion section of the impingement tube extends in a direction oriented basically perpendicular to the span wise direction over an edge of the insertion aperture in the wall segment, wherein the protrusion section is overlapped by at least a part of the wall segment and wherein adjacent to the protrusion section an overlap section of the impingement tube is arranged which abuts the edge of the insertion aperture in the wall segment and wherein the protrusion section and the overlap section are formed integrally with each other in one piece.

2. The turbine assembly according to claim 1 , wherein the hollow aerofoil comprises a trailing edge and a leading edge, and wherein the protrusion section of the impingement tube extends in a direction oriented to the trailing edge.

3. The turbine assembly according to claim 1 , wherein the impingement tube extends substantially completely through a span of the hollow aerofoil.

4. The turbine assembly according to claim 1 , wherein the impingement tube has a stepped contour which abuts the edge of the insertion aperture in the wall segment.

5. The turbine assembly according to claim 1 , wherein the impingement tube is formed from at least two separate pieces, from a trailing piece and a leading piece, wherein the trailing piece is located towards a trailing edge of the hollow aerofoil and the leading piece is located towards a leading edge of the hollow aerofoil.

6. The turbine assembly according to claim 1 , wherein the impingement tube is formed from at least two separate pieces each extending substantially completely through a span of the hollow aerofoil.

7. The turbine assembly according to claim 5 , wherein the leading piece locks the trailing piece into position in the hollow aerofoil, thereby preventing the trailing piece to become dislocated from the hollow aerofoil.

8. The turbine assembly according to claim 5 , wherein the leading piece locks the trailing piece into position in the hollow aerofoil via a press fit structure and/or a form fit structure.

9. The turbine assembly according to claim 1 , wherein the wall segment with at least the insertion aperture in the wall segment is a region of an outer platform and/or an inner platform.

10. The turbine assembly according to claim 1 , wherein the hollow aerofoil comprises at least a spacer at an interior surface of the hollow aerofoil to hold the impingement tube at a predetermined distance to said surface of the hollow aerofoil, wherein said at least spacer comprises a protrusion or a locking pin or a rib.

11. The turbine assembly according to claim 1 , wherein the hollow aerofoil is a turbine blade or vane.

12. The turbine assembly according to claim 8 , wherein the form fit structure is disposed between a stepped contour of the impingement tube and the edge of the insertion aperture in the wall segment.

13. A method for assembling an impingement tube in a basically hollow aerofoil of a turbine assembly, said method comprising:
inserting the impingement tube through an insertion aperture in a wall segment into the hollow aerofoil, wherein the wall segment is arranged at a side of the hollow aerofoil oriented basically perpendicular to a span wise direction of the hollow aerofoil,
maneuvering of at least a protrusion section of the impingement tube into position so that the protrusion section extends in a direction oriented basically perpendicular to the span wise direction over an edge of the insertion aperture in the wall segment wherein the protrusion section is overlapped by at least a part of the wall segment and wherein adjacent to the protrusion section an overlap section of the impingement tube is arranged which abuts the edge of the insertion aperture in the wall segment and wherein the protrusion section and the overlap section are formed integrally with each other in one piece.

14. The method for assembling an impingement tube in a hollow aerofoil of a turbine assembly according to claim 13 , wherein the impingement tube comprises at least a trailing piece and a leading piece and wherein after a maneuvering of the trailing piece into position the leading piece is inserted into the hallow aerofoil adjacent to the trailing piece through the insertion aperture in the wall segment and maneuvered into position in the hallow aerofoil.

15. The method for assembling an impingement tube in a hollow aerofoil of a turbine assembly according to claim 14 , further comprising locking the trailing piece into position in the hollow aerofoil via the leading piece thereby preventing the trailing piece to become dislocated from the hollow aerofoil, wherein the locking of the trailing piece into position in the hollow aerofoil comprises a press fitting and/or a form fitting.

16. A turbine assembly comprising:
an airfoil extending in a spanwise direction;
a platform attached to an end of the airfoil and extending generally perpendicularly to the spanwise direction;
an aperture in the platform providing access to a hollow interior of the airfoil, the aperture defined at least in part by an edge of the platform; and
an impingement tube disposed in the hollow interior of the airfoil and comprising:
a trailing piece sized for insertion through the aperture and comprising:
a protrusion section extending under an overlapping part of the platform; and
an overlap section extending from the protrusion section; and

a leading piece locking the trailing piece in position with the overlap section abutting the edge of the platform, the leading piece sized for insertion through the aperture after the trailing piece has been inserted.

17. The turbine assembly of claim 16 , wherein the leading piece locks the trailing piece in position with a press fit.

18. The turbine assembly of claim 16 , wherein the trailing piece and the overlap section are formed integrally.

Assignees

• Mugglestone Jonathan
• Siemens Ag

Inventors

• Mugglestone Jonathan

Classifications

• F01D5/18 Primary

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F01D5/189 Primary

  the insert having a tubular cross-section, e.g. airfoil shape · CPC title

• B23P15/04

  turbine or like blades from several pieces · CPC title

• F05D2230/51

  in a modular way, e.g. using several identical or complementary parts or features · CPC title

• F05D2230/53

  by integrally manufacturing a component, e.g. by milling from a billet or one piece construction · CPC title