Gas turbine engine transitions comprising closed cooled transition cooling channels
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-001/00
출원번호
UP-0350562
(2006-02-09)
등록번호
US-7827801
(2010-11-25)
발명자
/ 주소
Dawson, Robert W.
Bland, Robert J.
Youngblood, Bradley T.
출원인 / 주소
Siemens Energy, Inc.
인용정보
피인용 횟수 :
8인용 특허 :
24
초록▼
A transition (200) for a gas turbine engine (100) comprises a transition wall (201) comprising cooling channels (213L, 213R, 223L, 223R) that are adapted to pass a cooling fluid, such as compressed air from a compressor (102) during operation of the gas turbine engine (100) so as to cool combusted h
A transition (200) for a gas turbine engine (100) comprises a transition wall (201) comprising cooling channels (213L, 213R, 223L, 223R) that are adapted to pass a cooling fluid, such as compressed air from a compressor (102) during operation of the gas turbine engine (100) so as to cool combusted hot gases passing through the transition (200). For each cooling channel (213L, 213R, 223L, 223R), respective entry ports (212L, 212L, 222L, 222R) and exit ports (214L, 214R, 224L, 224R) are arranged so as to obtain a performance improvement based upon pressure differentials between the respective entry and exit ports. In various embodiments, a scoop (220) is associated with an entry port (222L, 222R) so as to establish a more elevated pressure differential in the respective cooling channel (223L, 223R). An entry port (330a-h) may be positioned offset relative to a lower-positioned exit port (340a-h) so as to so minimize or eliminate intake of heated airflow from a respective nearby exit port (340a-h). Such offset positioning may be based on the airflow paths and cooling requirements at selected high-temperature operating conditions.
대표청구항▼
I claim as my invention: 1. A transition for a gas turbine engine, the transition comprising a transition wall having an outer surface and an inner surface and comprising an inboard side, an outboard side, and a first lateral side and a second lateral side connecting the inboard and the outboard si
I claim as my invention: 1. A transition for a gas turbine engine, the transition comprising a transition wall having an outer surface and an inner surface and comprising an inboard side, an outboard side, and a first lateral side and a second lateral side connecting the inboard and the outboard sides, the transition wall further comprising: a. a first entry port through the outer surface along the inboard side communicating with at least one first cooling channel within the transition wall originating at the first entry port and terminating at a first exit port through the outer surface disposed along the first lateral side; and b. a second entry port through the outer surface along the first lateral side, disposed relative to an inboardly opening scoop extending from the first lateral side for entrapment of a portion of air passing over the transition from the inboard side toward the outboard side, the second entry port communicating with at least one second cooling channel originating at the second entry port and extending from the second entry port to a second exit port through the outer surface disposed along the outboard side. 2. The transition of claim 1, additionally comprising at least one additional cooling channel comprising an intake end in fluid communication with the first entry port or the second entry port. 3. The transition of claim 1, additionally comprising at least one additional cooling channel comprising an exit end in fluid communication with the first exit port or the second exit port. 4. The transition of claim 1, additionally comprising: a. a third entry port through the outer surface, adjacent the first entry port, communicating with at least one third cooling channel within the transition wall originating at the third entry port and terminating at a third exit port through the outer surface disposed along the second lateral side, and b. a fourth entry port through the outer surface along the second lateral side, disposed relative to an inboardly-opening scoop extending from the second lateral side for entrapment of air passing over the transition from the inboard side toward the outboard side, the fourth entry port communicating with at least one fourth cooling channel originating at the fourth entry port and extending from the fourth entry port to a fourth exit port through the outer surface disposed along the outboard side. 5. The transition of claim 4 wherein the transition wall is comprised of a top half and a bottom half joined along two weld seams disposed respectively along the first lateral side and the second lateral side, one of the weld seams separating the first exit port from the second entry port and the other of the weld seams separating the third exit port from the fourth entry port. 6. The transition of claim 5, wherein the second entry port and the fourth entry port are offset, respectively, from respective paths of local airflow exiting the first and third exit ports. 7. A gas turbine engine comprising the transition of claim 1. 8. A gas turbine engine comprising the transition of claim 6.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (24)
Robert James Bland, Aerodynamic devices for enhancing sidepanel cooling on an impingement cooled transition duct and related method.
Saitou, Takeo; Watanabe, Yasuyuki; Yoshida, Shouhei, Gas turbine combustor including a transition piece flow sleeve wrapped on an outside surface of a transition piece.
Saitou, Takeo; Watanabe, Yasuyuki; Yoshida, Shouhei, Gas turbine combustor including a transition piece flow sleeve wrapped on an outside surface of a transition piece.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.