Liner, flow sleeve and gas turbine combustor each having cooling sleeve
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/54
F02C-007/18
F23R-003/00
F23R-003/02
출원번호
US-0590747
(2015-01-06)
등록번호
US-10094573
(2018-10-09)
우선권정보
KR-10-2014-0005741 (2014-01-16)
발명자
/ 주소
Kim, Young Bong
Choe, Jinhoon
Roh, Ujin
출원인 / 주소
DOOSAN Heavy Industries Construction Co., LTD
대리인 / 주소
Invenstone Patent, LLC
인용정보
피인용 횟수 :
0인용 특허 :
27
초록▼
A gas turbine combustor includes a liner and a transmission piece. Fuel injected in the liner from a fuel nozzle of a gas turbine mixes with compressed air. High temperature gas produced in the liner is transmitted through the transmission piece. The liner is disposed in a flow sleeve in which cooli
A gas turbine combustor includes a liner and a transmission piece. Fuel injected in the liner from a fuel nozzle of a gas turbine mixes with compressed air. High temperature gas produced in the liner is transmitted through the transmission piece. The liner is disposed in a flow sleeve in which cooling holes are formed. The transition piece is disposed in a perforated sleeve. Compressed air supplied through holes formed in the perforated sleeve collides with the transition piece. The liner includes a cooling sleeve disposed thereon that divides the air supplied through the cooling holes of the flow sleeve and the compressed air flowing to a space portion between the liner and the flow sleeve.
대표청구항▼
1. A liner for a gas turbine combustor, the gas turbine combustor having a flow sleeve disposed around the liner and a transition piece, the liner comprising: a cooling sleeve disposed on the liner operable to divide air supplied through cooling holes defined in the flow sleeve and compressed air fl
1. A liner for a gas turbine combustor, the gas turbine combustor having a flow sleeve disposed around the liner and a transition piece, the liner comprising: a cooling sleeve disposed on the liner operable to divide air supplied through cooling holes defined in the flow sleeve and compressed air flowing to a space portion defined between the liner and the flow sleeve, the compressed air having collided against the transition piece. 2. The liner according to claim 1, wherein the cooling sleeve comprises convex portions and concave portions, and the concave portions are operable to direct the compressed air flowing to the space portion. 3. The liner according to claim 2, wherein the convex portions are operable to guide the air supplied through the cooling holes of the flow sleeve,the convex portions are disposed in a direction parallel to the cooling holes, andeach concave portion is adjacent to at least one of the convex portions. 4. The liner according to claim 2, wherein a height of the convex portions increases from the transition piece toward the liner. 5. The liner according to claim 1, wherein the cooling holes are arranged in a plurality of rows in a longitudinal direction of the liner, andthe cooling sleeve extends up to a first cooling hole row in a direction from the transition piece toward the liner. 6. A flow sleeve for a gas turbine combustor, the gas turbine combustor having a liner disposed in the flow sleeve and a transition piece, the flow sleeve comprising: a cooling sleeve disposed on the flow sleeve operable to divide air supplied through cooling holes defined in the flow sleeve and compressed air flowing to a space portion defined between the liner and the flow sleeve, the compressed air having collided against the transition piece. 7. The flow sleeve according to claim 6, wherein the cooling sleeve comprises convex portions and concave portions, and the concave portions are operable to direct the compressed air flowing to the space portion. 8. The flow sleeve according to claim 7, wherein the convex portions are operable to guide the air supplied through the cooling holes of the flow sleeve,the convex portions are disposed in a direction parallel to the cooling holes, andeach concave portion is adjacent to at least one of the convex portions. 9. The flow sleeve according to claim 7, wherein a height of the convex portions increases from the transition piece toward the liner. 10. The flow sleeve according to claim 6, wherein the cooling holes are arranged in a plurality of rows in a longitudinal direction of the liner, andthe cooling sleeve extends up to a first cooling hole row in a direction from the transition piece toward the liner. 11. A gas turbine combustor comprising: a liner operable to receive fuel injected from a fuel nozzle of a gas turbine that mixes with compressed air and is burned;a flow sleeve disposed around the liner, the flow sleeve having cooling holes defined therein operable to cool the liner when air is supplied through the cooling holes;a transition piece operable to transmit and increase transmission speed of gas produced in the liner;a perforated sleeve disposed around the transition piece, the transition piece having holes defined therein operable to supply compressed air that collides against the transition piece and flows to a space portion defined between the liner and the flow sleeve; anda cooling sleeve disposed between the flow sleeve and the liner operable to divide air supplied through the cooling holes of the flow sleeve and compressed air flowing to the space portion, the compressed air having collided against the transition piece. 12. The gas turbine combustor according to claim 11, wherein the cooling sleeve comprises convex portions and concave portions, and the concave portions are operable to direct the compressed air flowing to the space portion. 13. The gas turbine combustor according to claim 12, wherein the convex portions are operable to guide the air supplied through the cooling holes of the flow sleeve,the convex portions are disposed in a direction parallel to the cooling holes, andeach concave portion is adjacent to at least one of the convex portions. 14. The gas turbine combustor according to claim 12, wherein a height of the convex portions increases from the transition piece toward the liner. 15. The gas turbine combustor according to claim 11, wherein the cooling holes are arranged in a plurality of rows in a longitudinal direction of the liner, andthe cooling sleeve extends up to a first cooling hole row in a direction from the transition piece toward the liner. 16. The gas turbine combustor according to claim 12, wherein the cooling sleeve is coupled to the flow sleeve. 17. The gas turbine combustor according to claim 12, wherein the cooling sleeve is coupled to the liner.
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이 특허에 인용된 특허 (27)
Robert James Bland, Aerodynamic devices for enhancing sidepanel cooling on an impingement cooled transition duct and related method.
Haumann Jurgen (Rekingen CHX) Knopfli Alfred (Othmarsingen CHX) Sattelmayer Thomas (Mandach CHX) Tresch Rudolf (Seon CHX), Apparatus for impingement cooling.
Sato Yukinori (Iruma JPX) Watanabe Takeshi (Ome JPX) Nikai Isao (Yokohama JPX) Watanabe Kenji (Yokohama JPX), Liner cooling construction for gas turbine combustor or the like.
Bintz Miles F. (Schenectady NY) Dehmer ; deceased Raymond L. (late of Clifton Park NY by Mary Mae Dehmer ; administrator), Liquid-cooled transition member to turbine inlet.
Lee Ching-Pang (Cincinnati OH) Savage Joseph W. (Maineville OH) Bobo Melvin (Cincinnati OH), Scaled heat transfer surface with protruding ramp surface turbulators.
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