IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0521413
(2000-03-08)
|
우선권정보 |
JP-0060321 (1999-03-08) |
발명자
/ 주소 |
- Kuwabara, Masamitsu
- Tomita, Yasuoki
- Suenaga, Kiyoshi
- Kataoka, Masahito
- Sato, Yoshichika
- Watanabe, Koji
|
출원인 / 주소 |
- Mitsubishi Heavy Industries, Ltd.
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
14 인용 특허 :
8 |
초록
▼
In a tail tube seal structure of gas turbine, a U-shaped groove is provided at one side of a tail tube seal where a flange of a tail tube outlet is fitted, and a pi-shaped groove is provided at other side of the tail tube seal where a gas pass side flange end is fitted, thereby composing the seal of
In a tail tube seal structure of gas turbine, a U-shaped groove is provided at one side of a tail tube seal where a flange of a tail tube outlet is fitted, and a pi-shaped groove is provided at other side of the tail tube seal where a gas pass side flange end is fitted, thereby composing the seal of the connection area. Inclined cooling holes are drilled in the tail tube seal in addition to the cooling holes existing conventionally. The cooling air flows in from the inclined holes and cools the gas pass side of the groove due to the film effect. Therefore, the difference in thermal expansion between the groove and flange end is decreased, the wear of this area is decreased, and the reliability of the seal is enhanced.
대표청구항
▼
1. A tail tube sealing structure for a combustor having a tail tube outlet including a first flange, and a shroud with a second flange, said combustor receiving compressed air from a compressor that discharges a first amount of the compressed air, said tail tube sealing structure defining a gas pass
1. A tail tube sealing structure for a combustor having a tail tube outlet including a first flange, and a shroud with a second flange, said combustor receiving compressed air from a compressor that discharges a first amount of the compressed air, said tail tube sealing structure defining a gas passage and comprising a member having a wall defined by an inside surface and an outside surface, said member having a first groove fitting the first flange around said tail tube outlet and having a second groove having a bottom and fitting the second flange of said shroud, said member having a plurality of first cooling holes disposed at a first position in a gas flow direction and extending through the wall between the outside surface and the inside surface so as to pass cooling air into said gas passage, and a plurality of second cooling holes disposed at a second position downstream of said first position and adjacent to the first cooling holes, said second cooling holes extending through the wall between the outside surface and the inside surface in the gas flow direction and being open to said gas passage on the inside surface at a third position in the gas flow direction, the third position being located on, or downstream in the gas flow direction of, an imaginary annular curved line defined as an intersection of an imaginary plane substantially flush with the bottom of said second groove with said inside surface, said first cooling holes and said second cooling holes passing the cooling air in a second amount,whereby the film cooling effect on the inside surface is enhanced to thereby decrease frictional force generated upon contract of said member with said second flange of said shroud, andwhereby the second amount of the cooling air is reduced to at most about 1 to 2% of the first amount of the compressed air discharged from said compressor. 2. The tail tube seal structure of a combustor according to claim 1, wherein said second cooling holes are provided at intervals around the periphery of the wall along the gas pass of said member. 3. The tail tube seal structure of a combustor according to claim 1, wherein a smooth slope is formed in the inner surface of the wall contiguous to the second flange so that the air flowing out from said second cooling holes may flow in the gas flow direction. 4. The tail tube seal structure of a combustor according to claim 1, wherein said second flange defines a smooth surface, a brush seal is provided in the second groove of said member, and said brush seal contacts with the smooth surface of said flange end. 5. The tail tube seal structure of a combustor according to claim 1, wherein said second cooling holes are at least one of circular or elliptical. 6. The tail tube seal structure of a combustor according to claim 1, wherein said second cooling holes are slender holes. 7. A gas turbine having a combustor with a tail tube outlet, including a first flange on the periphery of said outlet, a shroud with a second flange, said combustor receiving compressed air from a compressor that discharges a first amount of the compressed air, and a tail tube seal structure for a sealed connection between the tail tube outlet and the shroud, the tail tube outlet, the seal structure and the shroud defining a gas passage for flow of gas from an upstream position at the tail tube outlet toward a downstream position at the shroud in a gas flow direction, said tail tube seal structure comprising a member having a wall defined by an inside surface and an outside surface, said member having a first groove fitting the first flange around said tail tube outlet and having a second groove having a bottom and fitting the second flange of said shroud, said member having a plurality of first cooling holes disposed at a first position in the gas flow direction and extending through the wall between the outside surface and the inside surface so as to pass cooling air into said gas passage, and a plurality of second cool ing holes disposed at a second position downstream of said first position and adjacent to the first cooling holes, said second cooling holes extending through the wall between the outside surface and the inside surface in the gas flow direction and being open to said gas passage on the inside surface at a third position in the gas flow direction, the third position being located on, or downstream in the gas flow direction of, an imaginary annular curved line defined as an intersection of an imaginary plane substantially flush with the bottom of said second groove with said inside surface, said first cooling holes and said second cooling holes passing the cooling air in a second amount,whereby the film cooling effect on the inside surface is enhanced to thereby decrease frictional force generated upon contact of said member with said second flange of said shroud, andwhereby the second amount of the cooling air is reduced to at most about 1 to 2% of the first amount of the compressed air discharged from said compressor. 8. The tail tube seal structure of a combustor according to claim 7, wherein said second cooling holes are provided at intervals around the periphery of the wall along the gas pass of said member. 9. The tail tube seal structure of a combustor according to claim 7, wherein a smooth slope is formed in the inner surface of the wall contiguous to the second flange so that the air flowing out from said second cooling holes may flow in the gas flow direction. 10. The tail tube seal structure of a combustor according to claim 7, wherein said second flange defines a smooth surface, a brush seal is provided in the second groove of said member, and said brush seal contacts with the smooth surface of said flange end. 11. The tail tube seal structure of a combustor according to claim 7, wherein said second cooling holes are at least one of circular or elliptical. 12. The tail tube seal structure of a combustor according to claim 7, wherein said second cooling holes are slender holes.
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