Film cooling of turbine blades or vanes

Patent metadata

Field	Value
Publication number	US-9771804-B2
Application number	US-201214235060-A
Country	US
Kind code	B2
Filing date	Jul 13, 2012
Priority date	Aug 8, 2011
Publication date	Sep 26, 2017
Grant date	Sep 26, 2017

Abstract

The present invention relates to a turbine assembly having an aerofoil and/or an end wall each having an outer surface with a structure for directing a flow of a cooling medium at the outer surface. The structure at the outer surface has at least a first groove and a second groove extending in the outer surface from a leading to a trailing edge and being oriented in at least two different directions with a deflection angle (α) towards each other, with the deflection angle (α) having a component in a span wise direction of the aerofoil. The structure at the outer surface of the end wall has at least a first groove and a second groove extending in an axial direction of the turbine assembly, matching an outer profile of the aerofoil and oriented in at least two different directions with a deflection angle (α) towards each other.

First claim

The invention claimed is:

1. A turbine assembly comprising:
an aerofoil comprising an outer surface, the outer surface comprising a structure configured to direct a flow of a cooling medium at the outer surface during operation of a turbine,
wherein the outer surface defines a mainstream gas path surface,
wherein the structure comprises a first groove and a second groove,
wherein the first groove and the second groove extend in the outer surface of the aerofoil from a leading edge to a trailing edge of the aerofoil and are oriented in at least two different directions with a deflection angle (α) towards each other,
wherein said deflection angle (α) has a component in a span wise direction of the aerofoil, and
wherein the first groove and the second groove cut across each other.

2. The turbine assembly according to claim 1 ,
wherein the deflection angle (α) is up to 45°.

3. The turbine assembly according to claim 1 , further comprising
several first grooves and/or several second grooves,
wherein a distance quotient (P/H) referring to a distance (P) between two adjacent grooves of the several first grooves and a height (H) of the several first grooves is greater than or equal to 1 and less than or equal to 30 and/or wherein a distance quotient (P/H) referring to a distance (P) between two adjacent grooves of the several second grooves and a height (H) of the several second grooves is greater than or equal to 1 and less than or equal to 30.

4. The turbine assembly according to claim 1 , further comprising
several first grooves and/or several second grooves,
wherein a clearance quotient (W/H) referring to a clearance (W) between two adjacent first grooves of the several first grooves and a height (H) of the several first grooves is greater than or equal to 0.2 and less than or equal to 20 and/or wherein a clearance quotient (W/H) referring to a clearance (W) and a height (H) between two adjacent second grooves of the several second grooves and a height (H) of the several second grooves is greater than or equal to 0.2 and less than or equal to 20.

5. The turbine assembly according to claim 1 ,
wherein the first groove and/or the second groove are manufactured into and/or onto the outer surface via a process selected from a group consisting of a casting process, a machining process, an etching process, an electro discharge machining process, a spark erosion process, an electro chemical machining process, an electro plating process and a coating process.

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

7. The turbine assembly according to claim 1 , further comprising
several first grooves and/or several second grooves.

8. The turbine assembly according to claim 7 ,
wherein the several first grooves are parallel towards each other and/or the several second grooves are parallel towards each other.

9. The turbine assembly according to claim 1 , further comprising
a cooling system for feeding the flow of the cooling medium to the outer surface.

10. The turbine assembly according to claim 9 ,
wherein the cooling system comprises a slot configured to feed the flow of the cooling medium to the first groove and/or the second groove.

11. The turbine assembly according to claim 9 ,
wherein the cooling system comprises a hole configured to open into the first groove or the second groove.

12. The turbine assembly according to claim 9 , further comprising
a rim seal which forms an opening of the cooling system.

13. The turbine assembly according to claim 9 ,
wherein the first groove and/or the second groove are arranged in an axial direction and in a stream wise direction downstream of a film cooling injection point of the cooling system.

14. A turbine assembly comprising:
an aerofoil comprising an outer surface, the outer surface comprising a structure configured to direct a flow of a cooling medium at the outer surface during operation of a turbine,
wherein the outer surface defines a mainstream gas path surface,
wherein the structure comprises several first grooves and several second grooves with the several first grooves being parallel towards each other and the several second grooves being parallel towards each other, wherein a first groove of the several first grooves and a second groove of the several second grooves are arranged end-to-end to form a line,
wherein the several first grooves and second grooves extend in the outer surface of the aerofoil from a leading edge to a trailing edge of the aerofoil and are oriented in at least two different directions with a deflection angle (α) towards each other,
wherein said deflection angle (α) has a component in a span wise direction of the aerofoil.

15. The turbine assembly according to claim 14 ,
wherein the deflection angle (α) is up to 45°.

16. The turbine assembly according to claim 14 , further comprising
a cooling system for feeding the flow of the cooling medium to the outer surface.

17. The turbine assembly according to claim 16 , further comprising
a rim seal which forms an opening of the cooling system.

18. The turbine assembly according to claim 16 ,
wherein the first groove and/or the second groove are arranged in an axial direction and in a stream wise direction downstream of a film cooling injection point of the cooling system.

19. The turbine assembly according to claim 16 ,
wherein the cooling system comprises a film cooling injection point to feed the flow of the cooling medium to the first groove and/or the second groove.

20. The turbine assembly according to claim 19 ,
wherein the film cooling injection point is an opening, comprising a hole and/or a slot.

Assignees

• Guo Liang
• Maltson John David
• Yan Yuying
• Siemens Ag

Inventors

• Guo Liang
• Maltson John David
• Yan Yuying

Classifications

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2260/202

  by film cooling · CPC title

• F01D5/145 Primary

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title

• F05D2240/12

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