IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0451511
(2008-05-02)
|
등록번호 |
US-8388303
(2013-03-05)
|
우선권정보 |
DE-10 2007 023 380 (2007-05-18) |
국제출원번호 |
PCT/DE2008/000758
(2008-05-02)
|
§371/§102 date |
20091116
(20091116)
|
국제공개번호 |
WO2008/141609
(2008-11-27)
|
발명자
/ 주소 |
- Weidmann, Wilfried
- Wirth, Moritz
|
출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
4 |
초록
▼
A gas turbine having a rotor which includes a turbine rotor, a shaft and a compressor rotor, the turbine rotor having at least one rotor disk and a rotor cone leading from the or a rotor disk to the shaft, the downstream end of the shaft being rotatably supported in a bearing having a bearing chambe
A gas turbine having a rotor which includes a turbine rotor, a shaft and a compressor rotor, the turbine rotor having at least one rotor disk and a rotor cone leading from the or a rotor disk to the shaft, the downstream end of the shaft being rotatably supported in a bearing having a bearing chamber, the interior space of the shaft being designed as a flow channel for bearing-chamber sealing air, and the space surrounding the rotor cone upstream of the same being designed as a flow space for cooling air is disclosed. In the region of the rotor connection, the shaft exhibits an expanded portion, at whose upstream end, openings are provided to allow cooling air to enter, and, at whose downstream end, openings are provided to allow cooling air to exit into the space between the bearing chamber and the rotor cone, a wall separating the streams of the cooling air and of the sealing air in the shaft interior from one another.
대표청구항
▼
1. A gas turbine comprising: a rotor including a turbine rotor, a shaft and a compressor rotor, the turbine rotor having at least one bladed rotor disk and a rotor cone leading from the at least one rotor disk to the shaft, a downstream end of the shaft being rotatably supported in a bearing having
1. A gas turbine comprising: a rotor including a turbine rotor, a shaft and a compressor rotor, the turbine rotor having at least one bladed rotor disk and a rotor cone leading from the at least one rotor disk to the shaft, a downstream end of the shaft being rotatably supported in a bearing having a bearing chamber, an interior space of the shaft being designed as a flow channel for sealing air leading to the bearing chamber, and a space surrounding the rotor cone upstream of the rotor cone being designed as a flow space for cooling air used for cooling the rotor blades,wherein, in a region of a connection of the rotor cone, the shaft has an expanded portion having an enlarged inside and outside diameter, and at an upstream end of the expanded portion, openings are provided to allow the cooling air to enter into an expanded interior space of the shaft and, at a downstream end of the expanded portion, other openings are provided to allow the cooling air to exit into a further space between the bearing chamber and the rotor cone, the expanded interior space being sealed from the a further interior space of the shaft by a wall for separating the cooling air and the sealing air,wherein the expanded portion is integrally formed with the downstream end of the shaft. 2. The gas turbine as recited in claim 1 wherein the bearing chamber is part of a turbine exhaust case configured downstream of the turbine rotor. 3. The gas turbine as recited in claim 1 further comprising a pipe forming an annular flow channel for the sealing air and configured coaxially at a radial distance in the interior space of the shaft. 4. The gas turbine as recited in claim 1 wherein the flow channel for the sealing air leads through further openings in the shaft radially outwardly between two axially spaced, non-hermetic seals to the bearing chamber. 5. The gas turbine as recited in claim 4 wherein the seals are in the form of brush seals. 6. The gas turbine as recited in claim 1 wherein the rotor cone is attached at the expanded portion of the shaft via a tooth system engaging circumferentially with form locking, via press-fit connections configured axially on both sides of the tooth system, via an axial stop, as well as via an axially acting screw connection. 7. The gas turbine as recited in claim 1 wherein the gas turbine is a multi-shaft gas turbine and part of a low-pressure system. 8. The gas turbine as recited in claim 1 wherein the rotor cone increases in radius in a downstream direction. 9. The gas turbine as recited in claim 1 wherein the bearing is radially exterior with respect to the shaft at an axial location of the bearing. 10. The gas turbine as recited in claim 1 wherein the shaft rotates with the bladed rotor disk. 11. The gas turbine as recited in claim 10 wherein the rotor cone is connected to the shaft via a toothed connection. 12. The gas turbine as recited in claim 10 wherein a connection between the rotor cone and the shaft includes two press fit connections and a tooth system. 13. The gas turbine as recited in claim 12 wherein the connection further includes an axial stop and a screw connection. 14. The gas turbine as recited in claim 10 wherein the bladed rotor disk is integral with the rotor cone. 15. The gas turbine as recited in claim 1 wherein the at least one least one bladed rotor disk includes a plurality of bladed rotor disks and the rotor cone is connected to a furthest downstream of the plurality of bladed rotor disks. 16. The gas turbine as recited in claim 1 wherein the sealing air and cooling air so not mix within the shaft. 17. The gas turbine as recited in claim 1 wherein the sealing air has a temperature lower than the cooling air. 18. The gas turbine as recited in claim 1 wherein the shaft has a central pipe. 19. A gas turbine comprising: a rotor including a turbine rotor, a shaft rotating with the turbine rotor and a compressor rotor, the turbine rotor having at least one bladed rotor disk and a rotor cone leading from the at least one rotor disk to the shaft, a downstream end of the shaft being rotatably supported on an outside surface in a bearing having a bearing chamber, an interior space of the shaft being designed as a flow channel for sealing air leading to the bearing chamber, and a space surrounding the rotor cone upstream of the rotor cone being designed as a flow space for cooling air used for cooling the rotor blades,wherein, in a region of a connection of the rotor cone, the shaft has an expanded portion having an enlarged inside and outside diameter, and at an upstream end of the expanded portion, openings are provided to allow the cooling air to enter into an expanded interior space of the shaft, and, at a downstream end of the expanded portion, other openings are provided to allow the cooling air to exit into a further space between the bearing chamber and the rotor cone, the expanded interior space being sealed from a further interior space of the shaft by a wall for separating the cooling air and the sealing air,wherein the expanded portion is integrally formed with the downstream end of the shaft.
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