Gas turbine with high-pressure turbine cooling system

Patent metadata

Field	Value
Publication number	US-9631515-B2
Application number	US-201414324621-A
Country	US
Kind code	B2
Filing date	Jul 7, 2014
Priority date	Jul 8, 2013
Publication date	Apr 25, 2017
Grant date	Apr 25, 2017

Abstract

The present invention relates to a gas turbine with a turbine stator wheel, which is fitted with stator vanes and includes a ring segment-shaped vane root, where the stator vanes are designed hollow and have a vane interior which can be supplied with cooling air, where a ring-shaped sealing element of an inter-stage seal is arranged radially on the inside, relative to an engine axis, on the vane root, where in the vane root at least one outflow duct is provided, characterized in that between the vane root and the sealing element an annular space extending substantially in the axial direction is formed, into which the outflow duct issues and which discharges into the area of the inter-stage seal.

First claim

What is claimed is:

1. A gas turbine comprising:
a turbine stator wheel, including a plurality of stator vanes and a ring segment-shaped vane root, the stator vanes being hollow and each including a vane interior which can be supplied with cooling air,
a ring-shaped sealing element of an inter-stage seal arranged radially inwardly, relative to an engine axis, of the vane root,
at least one outflow duct positioned in the vane root and connected to the vane interior to output the cooling air from the vane interior,
an annular space formed between the vane root and the sealing element and extending substantially in an axial direction,
the at least one outflow duct issuing the cooling air into the annular space and the annular space discharging the cooling air into an area of the inter-stage seal,
a plurality of axially extending ribs positioned in the annular space and extending from the at least one outflow duct through an exit opening of the annular towards area of the inter-stage seal, the ribs spacing apart the sealing element from the vane root and limiting circumferential cooling air flow in the annular space.

2. The gas turbine in accordance with claim 1 , wherein the annular space has a constant flow cross-section from the at least one outflow duct through an exit opening of the annular space into the area of the inter-stage seal.

3. The gas turbine in accordance with claim 1 , wherein the ribs are arranged on the sealing element.

4. The gas turbine in accordance with claim 1 , wherein a discharge area of the annular space provides for axial outflow of the cooling air.

5. The gas turbine in accordance with claim 1 , wherein a discharge area of the annular space provides for outflow of the cooling air at an angle relative to at least one chosen from the axial direction and a radial direction.

6. The gas turbine in accordance with claim 1 , and further comprising an annular flow-guiding element at a discharge area of the annular space.

7. The gas turbine in accordance with claim 6 , wherein the flow-guiding element includes passage ducts.

8. The gas turbine in accordance with claim 7 , wherein the passage ducts are inclined relative to at least one chosen from a radial direction and the axial direction.

9. The gas turbine in accordance with claim 1 , wherein the at least one outflow duct is inclined relative to at least one chosen from a radial direction and the axial direction.

10. The gas turbine in accordance with claim 1 , wherein the ribs include predominately radially extending portions adjoining predominately axially extending portions, the predominately radially extending portions positioned directly adjacent the at least one outflow duct upstream of the predominately axially extending portions which are positioned directly adjacent the exit opening of the annular towards area of the inter-stage seal.

11. The gas turbine in accordance with claim 10 , wherein the ribs include curved portions connecting the predominately radially extending portions to the predominately axially extending portions.

12. A gas turbine comprising:
a turbine stator wheel, including a plurality of stator vanes and a ring segment-shaped vane root, the stator vanes being hollow and each including a vane interior which can be supplied with cooling air,
a ring-shaped sealing element of an inter-stage seal arranged radially inwardly, relative to an engine axis, of the vane root,
at least one outflow duct positioned in the vane root and connected to the vane interior to output the cooling air from the vane interior,
an annular space formed between the vane root and the sealing element and extending substantially in an axial direction,
the at least one outflow duct issuing the cooling air into the annular space and the annular space discharging the cooling air into an area of the inter-stage seal,
wherein the annular space has a constant flow cross-section from the at least one outflow duct through an exit opening of the annular space into the area of the inter-stage seal.

13. The gas turbine in accordance with claim 12 , wherein a discharge area of the annular space provides for axial outflow of the cooling air.

14. The gas turbine in accordance with claim 12 , wherein a discharge area of the annular space provides for outflow of the cooling air at an angle relative to at least one chosen from the axial direction and a radial direction.

15. The gas turbine in accordance with claim 12 , and further comprising an annular flow-guiding element at a discharge area of the annular space.

16. The gas turbine in accordance with claim 15 , wherein the flow-guiding element includes passage ducts.

17. The gas turbine in accordance with claim 16 , wherein the passage ducts are inclined relative to at least one chosen from a radial direction and the axial direction.

18. The gas turbine in accordance with claim 12 , wherein the at least one outflow duct is inclined relative to at least one chosen from a radial direction and the axial direction.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Oyarbide Asier
• Hecken Reinhold

Classifications

• F01D11/04

  using sealing fluid, e.g. steam · CPC title

• F01D9/065

  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 title

• F01D25/12 Primary

  Cooling · CPC title

• Y02T50/676

  Cross-Sectional Technologies · mapped topic

• F01D11/001 Primary

  for sealing space between stator blade and rotor · CPC title