Impingement cooled transition piece aft frame
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0553153
(2009-09-03)
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등록번호 |
US-8707705
(2014-04-29)
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발명자
/ 주소 |
- Berry, Jonathan Dwight
- McMahan, Kevin Weston
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
0 인용 특허 :
7 |
초록
▼
An aft frame of a turbine engine transition piece body is provided and includes an annular body disposed within a first annular space defined between an impingement sleeve and a compressor discharge casing and aft of a second annular space defined between the transition piece body and the impingemen
An aft frame of a turbine engine transition piece body is provided and includes an annular body disposed within a first annular space defined between an impingement sleeve and a compressor discharge casing and aft of a second annular space defined between the transition piece body and the impingement sleeve and including a main portion with a first surface facing the first annular space and a second surface facing the forward annular space. The main portion has an impingement hole extending therethrough from an inlet at the first surface of the annular body to an outlet at the second surface of the annular body to define a fluid path along which the first and second annular spaces communicate with one another.
대표청구항
▼
1. An aft frame of a turbine engine including a transition piece body, comprising: an annular body disposed within a first annular space defined between an impingement sleeve and a compressor discharge casing and aft of a second annular space defined between the transition piece body and the impinge
1. An aft frame of a turbine engine including a transition piece body, comprising: an annular body disposed within a first annular space defined between an impingement sleeve and a compressor discharge casing and aft of a second annular space defined between the transition piece body and the impingement sleeve and including a main portion with a first surface facing the first annular space and a second surface facing the second annular space,the main portion having an impingement hole extending therethrough from an inlet at the first surface of the annular body along a first section that extends in a radial direction and along a second section that extends in an axial direction to an outlet at the second surface of the annular body to define a fluid path along which the first annular space and the second annular space communicate with one another, the first section and the second section being perimetrically localized and an outlet of the first section being defined along a sidewall of the second section. 2. The aft flame according to claim 1, wherein the main portion further comprises an edge connected to an edge of the transition piece body. 3. The aft frame according to claim 1, wherein the main portion further comprises impingement hole sidewalls cooled by impingement flow communicated from the first annular space to the second annular space. 4. The aft frame according to claim 1, further comprising a seal to provide sealing between the first annular space and the second annular spaces. 5. The aft frame according to claim 4, wherein the main portion is formed to define a seal receptive groove that communicates with the impingement hole. 6. The aft frame according to claim 1, wherein the impingement hole is defined with a third section, which extends in a perimetric direction from the sidewall of the second section. 7. The aft frame according to claim 1, wherein the impingement hole is defined as a plurality of impingement holes. 8. The aft frame according to claim 7, wherein each impingement hole of the plurality of impingement holes is defined with a corresponding first section, which extends in the radial direction, and a corresponding second section, which extends in the axial direction. 9. The aft frame according to claim 8, wherein each impingement hole of the plurality of the impingement holes is defined with a corresponding third section, which extends in the perimetric direction between sidewalls of the corresponding second sections of adjacent ones of the plurality of the impingement holes. 10. The aft frame according to claim 7, wherein the plurality of the impingement holes communicate exclusively and directly with adjacent ones of the plurality of the impingement holes. 11. An aft frame of a turbine engine including a transition piece body, comprising: an annular body disposed within a first annular space defined between an impingement sleeve and a compressor discharge casing and aft of a second annular space defined between the transition piece body and the impingement sleeve and including a main portion with a first surface facing the first annular space and a second surface facing the second annular space,the main portion having an impingement hole extending therethrough from an inlet at the first surface of the annular body along a first section that extends in a radial direction and along a second section that extends in an axial direction to an outlet at the second surface of the annular body to define a fluid path along which the first annular space and the second annular space exclusively communicate with one another, the first section and the second section being perimetrically localized and an outlet of the first section being defined along a sidewall of the second section. 12. The aft frame according to claim 11, wherein the impingement hole is defined with a third section, which extends in a perimetric direction. 13. The aft frame according to claim 11, wherein the impingement hole is defined as a plurality of impingement holes. 14. The aft frame according to claim 13, wherein each impingement hole of the plurality of impingement holes is defined with a corresponding first section, which extends in the radial direction, and a corresponding second section, which extends in the axial direction. 15. The aft frame according to claim 14, wherein each impingement hole of the plurality of the impingement holes is defined with a third section, which extends in a perimetric direction. 16. The aft frame according to claim 13, wherein the plurality of the impingement holes communicate with one another. 17. A turbine engine, comprising: a compressor discharge casing (CDC);a transition piece body;an impingement sleeve disposed to delimit a first annular space with the CDC and a second annular space with the transition piece body; andan annular body, connected to the transition piece body and the impingement sleeve to be disposed within the first annular space and aft of the second annular space, and including a main portion with a first surface facing the first annular space and a second surface facing the second annular space, the main portion having an impingement hole extending therethrough from an inlet at the first surface along a first section that extends in a radial direction and along a second section that extends in an axial direction to an outlet at the second surface to define a fluid path along which the first annular space and the second annular space communicate with one another, the first section and the second section being perimetrically localized and an outlet of the first section being defined along a sidewall of the second section. 18. The turbine engine according to claim 16, further comprising a head end, which is disposed upstream from the transition piece body and which communicates with the second annular space.
이 특허에 인용된 특허 (7)
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Robert Harold Cromer ; William Theodore Bechtel ; Maz Sutcu, Cooling air recycling for gas turbine transition duct end frame and related method.
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Iizuka Nobuyuki (Hitachi JPX) Kumata Kazuhiko (Katsuta JPX) Kuroda Michio (Hitachi JPX), Gas turbine combustion apparatus.
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Davis ; Jr. Lewis B. (Schenectady NY) Goodwin Walter W. (Loudonville NY) Steber Charles E. (Scotia NY), Impingement cooled transition duct.
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Intile,John Charles; West,James A.; Byrne,William, Method and apparatus for cooling combustor liner and transition piece of a gas turbine.
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Park, Eui-Jin; Choi, Yun-Ho; Park, In-Young; Jeong, Hwan-Il; Choi, Sung-Sok, Structure for preventing gap formation and plasma processing equipment having the same.
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Kondo, Mitsuru; Hada, Satoshi; Tanaka, Katsunori, Transition piece outlet structure enabling to reduce the temperature, and a transition piece, a combustor and a gas turbine providing the above output structure.
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Cromer Robert H. (Gloversville NY), Transition piece seal spring for a gas turbine.
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