Gas turbine with a stator blade

• US 8,210,797 B2
• Filed: 11/24/2010
• Issued: 07/03/2012
• Est. Priority Date: 05/26/2008
• Status: Expired due to Fees

• Current Assignee: Ansaldo Energia IP UK Limited (Ansaldo Energia SPA)
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Dueckershoff, Roland, Steiger, Ulrich, Rathmann, Ulrich
• Primary Examiner(s): Nguyen, Ninh H
• Application Number:
  US12/954,205
• Publication Number:
  US 20110085894A1
• Time in Patent Office: 587 Days
• Field of Search: 415/115, 415/209.3, 415/213.1, 415/177
• US Class Current: 415/115
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F01D 9/065 Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids see also F01D25/16, F01D25/24 and F01D25/26
• CPC Class Codes: F05D 2240/57 Leaf seals
• CPC Class Codes: F05D 2240/81 Cooled platforms

Abstract

A gas turbine with a stator blade is disclosed. The stator blade is fastened on a blade carrier and includes a blade airfoil which extends inwards in the radial direction from an outer platform into a hot gas passage. A cooling medium can flow through an interior of the blade airfoil, such as cooling air, which flows through an access in the blade carrier into a first plenum which is arranged above the outer platform, and from there, via an inlet which is provided in the outer platform, flows into the interior of the blade airfoil.

Claims

1. A gas turbine comprising:

a stator blade fastened on a blade carrier, the stator blade including;

a blade airfoil which extends inwards in a radial direction from an outer platform into a hot gas passage;

an access in the blade carrier into a first plenum which is arranged above the outer platform for a cooling medium to flow, via an inlet provided in the outer platform into an interior of the stator blade;

a first means for controlling cooling-medium pressure in the first plenum; and

a second means for cooling the outer platform by directing the cooling medium from the first plenum.

2. The gas turbine as claimed in claim 1, wherein the first means are arranged in a region of the first plenum.

3. The gas turbine as claimed in claim 2, wherein the first means comprises:

a throttling element for throttling a flow of cooling medium through the inlet in the outer platform.

4. The gas turbine as claimed in claim 3, wherein the throttling element is formed as a plate which covers the inlet except for at least one throttling opening which is provided in the plate.

5. The gas turbine as claimed in claim 4, wherein the throttling opening is circular.

6. The gas turbine as claimed in claim 4, wherein the access to the first plenum is formed as at least one throttling opening.

7. The gas turbine as claimed in claim 4, comprising:

outwardly projecting, hook-like fastening elements, for fastening the stator blade on the blade carrier, the fastening elements being formed on an upper side of the outer platform at a distance from each other, and the first plenum being formed between two fastening elements.

8. The gas turbine as claimed in claim 3, wherein the access to the first plenum is formed as at least one throttling opening.

9. The gas turbine as claimed in claim 3, comprising:

outwardly projecting, hook-like fastening elements, for fastening the stator blade on the blade carrier, the fastening elements being formed on an upper side of the outer platform at a distance from each other, and the first plenum being formed between two fastening elements.

10. The gas turbine as claimed in claim 2, wherein the access to the first plenum is formed as at least one throttling opening.

11. The gas turbine as claimed in claim 2, comprising:

outwardly projecting, hook-like fastening elements, for fastening the stator blade on the blade carrier, the fastening elements being formed on an upper side of the outer platform at a distance from each other, and the first plenum being formed between two fastening elements.

12. The gas turbine as claimed in claim 1, wherein the access to the first plenum is formed as at least one throttling opening.

13. The gas turbine as claimed in claim 12, comprising:

outwardly projecting, hook-like fastening elements, for fastening the stator blade on the blade carrier, the fastening elements being formed on an upper side of the outer platform at a distance from each other, and the first plenum being formed between two fastening elements.

14. The gas turbine as claimed in claim 1, comprising:

outwardly projecting, hook-like fastening elements, for fastening the stator blade on the blade carrier, the fastening elements being formed on an upper side of the outer platform at a distance from each other, and the first plenum being formed between two fastening elements.

15. The gas turbine as claimed in claim 14, wherein the second means comprises:

a second plenum arranged on a side of one fastening element opposite from the first plenum, for receiving cooling medium which escapes from the first plenum, the second plenum being in fluid communication with the hot gas passage via throttling means.

16. The gas turbine as claimed in claim 15, comprising:

sealing strips which seal gaps which exist between adjacent stator blades of a stator blade row against the hot gas passage, the sealing strips being inserted in corresponding sealing grooves in lateral surfaces of the outer platforms of plural stator blades, and the sealing strips being formed as throttling means in a region of the second plenum.

17. The gas turbine as claimed in claim 16, wherein the sealing strips in the region of the second plenum are formed at least one of shorter and thinner than associated sealing grooves for achieving a throttling effect.

18. The gas turbine as claimed in claim 17, comprising:

a heat shield segment which partially delimits the second plenum of a stator blade, the heat shield segment being adjacent to the outer platform of the stator blade in a flow direction of a hot gas flow; and

a stepped gap, via which the second plenum is in communication with the hot gas passage, being arranged between the heat shield segment and the outer platform towards the hot gas passage.

19. The gas turbine as claimed in claim 15, comprising:

a heat shield segment which partially delimits the second plenum, the heat shield segment being adjacent to the outer platform of the stator blade in a flow direction of a hot gas flow; and

a stepped gap, via which the second plenum is in communication with the hot gas passage, being arranged between the heat shield segment and the outer platform towards the hot gas passage.