Gas turbine having at least two shafts designed as hollow shafts at least in some areas and arranged coaxially relative to one another

Patent metadata

Field	Value
Publication number	US-10082037-B2
Application number	US-201514874831-A
Country	US
Kind code	B2
Filing date	Oct 5, 2015
Priority date	Oct 6, 2014
Publication date	Sep 25, 2018
Grant date	Sep 25, 2018

Abstract

The present invention describes a gas turbine having two shafts, which are rotatably mounted using bearing devices in the area of a casing. An intermediate shaft sealing device is arranged between the bearing devices, which includes a sealing element connected to a first shaft, in which a further sealing element connected to the second shaft radially engages. An operating pressure is applied, in the area limited by the shafts in the axial direction of the shafts, to facing effective areas of the sealing elements, while the pressure prevailing in the area outside the shafts in the axial direction acts on effective areas of the sealing elements facing away from one another. A ratio between the outer diameters limiting the facing effective areas and the inner diameters likewise limiting these effective areas is in each case greater than or equal to 1.25.

First claim

What is claimed is:

1. A gas turbine comprising:
a casing;
bearing devices supported by the casing;
two shafts, each of the two shafts being hollow in some areas, the two shafts being arranged coaxially relative to one another,
the two shafts being rotatably mounted in the casing by the bearing devices,
a hydraulic intermediate shaft sealing device arranged between the bearing devices and which separates a first area inside at least one of the two shafts and limited by the two shafts from a second area outside the two shafts,
where, in the first area, a first operating pressure prevails that differs from a second operating pressure acting in the second area,
the hydraulic intermediate shaft sealing device including a first sealing element connected to a first shaft of the two shafts, the first sealing element extending over a circumference of the first shaft, and including an inner groove area with a defined groove depth,
a second sealing element connected to a second shaft of the two shafts and radially engaging the inner groove area,
where the first operating pressure is applied in the first area in an axial direction of the two shafts to facing effective areas of the first and second sealing elements, with each facing effective area being radially limited by an outer diameter and an inner diameter, each outer diameter and each inner diameter positioned on a respective one of the first and second sealing elements, while the second operating pressure prevailing in the second area acts in the axial direction on effective areas of the first and second sealing elements facing away from one another,
where a ratio between the outer diameters of the facing effective areas of the first and second sealing elements and the inner diameters of the facing effective areas of the first and second sealing elements is in each case greater than or equal to 1.25.

2. The gas turbine in accordance with claim 1 , wherein the inner groove area includes a groove bottom, in a radial direction, at a distance from a radially outer area of the second sealing element.

3. The gas turbine in accordance with claim 2 , wherein during operation of the gas turbine, the radially outer area of the second sealing element dips into a defined oil volume in the inner groove area of the first sealing element.

4. The gas turbine in accordance with claim 3 , wherein the second sealing element is shaped in some areas as an annular disk.

5. The gas turbine in accordance with claim 4 , and further comprising a bearing chamber in which the bearing devices are positioned.

6. The gas turbine in accordance with claim 5 , and further comprising a piston ring positioned between the two shafts, which separates, while the two shafts are stationary, the second area and the first area on a side of the hydraulic intermediate shaft sealing device facing the first area.

7. The gas turbine in accordance with claim 6 , wherein the two shafts rotate in a same rotational direction.

8. The gas turbine in accordance with claim 2 , wherein the second sealing element is shaped in some areas as an annular disk.

9. The gas turbine in accordance with claim 8 , and further comprising a bearing chamber in which the bearing devices are positioned.

10. The gas turbine in accordance with claim 9 , and further comprising a piston ring positioned between the two shafts, which separates, while the two shafts are stationary, the second area and the first area on a side of the hydraulic intermediate shaft sealing device facing the first area.

11. The gas turbine in accordance with claim 10 , wherein the two shafts rotate in a same rotational direction.

12. The gas turbine in accordance with claim 1 , wherein the second sealing element is shaped in some areas as an annular disk.

13. The gas turbine in accordance with claim 12 , and further comprising a bearing chamber in which the bearing devices are positioned.

14. The gas turbine in accordance with claim 13 , and further comprising a piston ring positioned between the two shafts, which separates, while the two shafts are stationary, the second area and the first area on a side of the hydraulic intermediate shaft sealing device facing the first area.

15. The gas turbine in accordance with claim 14 , wherein the two shafts rotate in a same rotational direction.

16. The gas turbine in accordance with claim 1 , and further comprising a bearing chamber in which the bearing devices are positioned.

17. The gas turbine in accordance with claim 1 , and further comprising a piston ring positioned between the two shafts, which separates, while the two shafts are stationary, the second area and the first area on a side of the hydraulic intermediate shaft sealing device facing the first area.

18. The gas turbine in accordance with claim 1 , wherein the two shafts rotate in a same rotational direction.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Venter Gideon

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/55

  Seals · CPC title

• F05D2240/57

  Leaf seals · CPC title

• F01D11/04

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

• F05D2240/52

  Axial thrust bearings · CPC title