IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0453621
(2009-05-15)
|
등록번호 |
US-8250870
(2012-08-28)
|
우선권정보 |
DE-10 2008 024 146 (2008-05-19) |
발명자
/ 주소 |
|
출원인 / 주소 |
- Rolls-Royce Deutschland Ltd Co KG
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
7 |
초록
▼
A vortex reducer for the guidance of bleed airflows (21), is arranged in an inter-disk chamber (3) between two rotor disks (1, 2) of the compressor of a gas turbine with at least one shaft, and includes at least one ring (11) with circumferentially disposed hole passages, in which bleed air tubes (1
A vortex reducer for the guidance of bleed airflows (21), is arranged in an inter-disk chamber (3) between two rotor disks (1, 2) of the compressor of a gas turbine with at least one shaft, and includes at least one ring (11) with circumferentially disposed hole passages, in which bleed air tubes (15) are arranged. In order to provide a vortex reducer, which requires small material input and, therefore, has low weight, while producing directed bleed airflows with low pressure losses, the hole passages include first hole passages (13) and second hole passages (14), and bleed air tubes (15) are provided only in the first hole passages (13), with the bleed air tubes (15) being evenly distributed on the circumference of the ring (11), and the second hole passages (14) being devoid of bleed air tubes (15).
대표청구항
▼
1. A vortex reducer for the guidance of bleed airflows, which is arranged in an inter-disk chamber between two rotor disks of a compressor of a gas turbine, comprising: at least one ring having a plurality of circumferentially disposed hole passages, the hole passages including a plurality of first
1. A vortex reducer for the guidance of bleed airflows, which is arranged in an inter-disk chamber between two rotor disks of a compressor of a gas turbine, comprising: at least one ring having a plurality of circumferentially disposed hole passages, the hole passages including a plurality of first hole passages distributed evenly around a circumference of the ring and a plurality of second hole passages, the first hole passages and second hole passages positioned at outer radial positions; anda plurality of bleed air tubes respectively connected to the plurality of first hole passages for extending the respective first hole passages radially inward in an interior of the inter-disk chamber to open the first hole passages to the inter-disk chamber at inner radial positions radially inward of the outer radial positions, the second hole passages being free of bleed air tubes and opening to the inter-disk chamber at the outer radial positions at circumferential interspaces between the bleed air tubes;outer surfaces of the bleed air tubes guiding air flows from the second hole passages through the circumferential interspaces between the bleed air tubes to reduce swirl of the air flows from the second hole passages. 2. The vortex reducer of claim 1, wherein the first hole passages account for one third of a total number of the hole passages and the second hole passages account for two thirds of the total number of the hole passages. 3. The vortex reducer of claim 2, wherein each of the bleed air tubes is rectilinearly arranged in a radial direction. 4. The vortex reducer of claim 2, wherein each of the bleed air tubes is curved against a direction of rotation of the compressor. 5. The vortex reducer of claim 2, wherein the bleed air tubes include fins protruding into the interspaces between the bleed air tubes. 6. The vortex reducer of claim 1, wherein the bleed air tubes have an oval cross-section. 7. The vortex reducer of claim 1, wherein at least one of the rotor disks includes radial blades, which axially project into the interspaces between the bleed air tubes. 8. The vortex reducer of claim 1, and further comprising at least one deflector positioned on at least one of a radially inner end of a bleed air tube and a shaft of the gas turbine. 9. A method for guiding bleed airflows in a gas turbine, comprising: providing a vortex reducer for guiding the bleed airflows in an inter-disk chamber between two rotor disks of a compressor of the gas turbine, the vortex reducer having at least one ring having a plurality of circumferentially disposed hole passages, the hole passages including a plurality of first hole passages distributed evenly around a circumference of the ring and a plurality of second hole passages, the first hole passages and second hole passages positioned at outer radial positions;providing a plurality of bleed air tubes positioned respectively in the plurality of first hole passages for extending the respective first hole passages radially inward in an interior of the inter-disk chamber to open the first hole passages to the inter-disk chamber at inner radial positions radially inward of the outer radial positions;leaving the second hole passages free of bleed air tubes to open to the inter-disk chamber at the outer radial positions at circumferential interspaces between the bleed air tubes;passing first partial bleed airflows through the first hole passages into the bleed air tubes to be guided towards a shaft of the gas turbine and to exit the bleed air tubes into the inter-disk chamber at the inner radial positions;passing second partial bleed airflows through the second hole passages to exit the second hole passages into the inter-disk chamber at the outer radial positions at the circumferential interspaces between the bleed air tubes,guiding the airflows from the second hole passages through the circumferential interspaces between the bleed air tubes with outer surfaces of the bleed air tubes to reduce swirl of the air flows from the second hole passages. 10. The method of claim 9, and further comprising guiding the second partial airflows in the interspaces between the bleed air tubes with at least one of fins positioned on the bleed air tubes and blades of the rotors. 11. The method of claim 10, wherein the first partial airflows and the second partial airflows are guided in a radial direction from the outer to the inner side. 12. The method of claim 10, wherein the first partial airflows and the second partial airflows are guided against a direction of rotation of the compressor and also towards the shaft. 13. The method of claim 10, and further comprising deflecting the first and second partial airflows issuing from the vortex reducer in an area of the shaft and producing an axial total airflow from the first and second partial airflows.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.