IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0213417
(2011-08-19)
|
등록번호 |
US-8727704
(2014-05-20)
|
발명자
/ 주소 |
- Lee, Ching-Pang
- Berrong, Eric C.
|
출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
8 인용 특허 :
18 |
초록
▼
A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system receives cooling fluid from an outer side of the panel for cooling the panel and includes at least one cooling fluid supply passage, at least one serpentine cooling passage, and at least one cooling flu
A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system receives cooling fluid from an outer side of the panel for cooling the panel and includes at least one cooling fluid supply passage, at least one serpentine cooling passage, and at least one cooling fluid discharge passage. The cooling fluid supply passage(s) receive the cooling fluid from the outer side of the panel and deliver the cooling fluid to a first cooling fluid chamber within the panel. The serpentine cooling passage(s) receive the cooling fluid from the first cooling fluid chamber, wherein the cooling fluid provides convective cooling to the panel as it passes through the serpentine cooling passage(s). The cooling fluid discharge passage(s) discharge the cooling fluid from the cooling system.
대표청구항
▼
1. A ring segment for a gas turbine engine comprising: a panel having a leading edge, a trailing edge, a first mating edge, a second mating edge, an outer side, and an inner side, wherein cooling fluid is provided to the outer side and the inner side defines at least a portion of a hot gas flow path
1. A ring segment for a gas turbine engine comprising: a panel having a leading edge, a trailing edge, a first mating edge, a second mating edge, an outer side, and an inner side, wherein cooling fluid is provided to the outer side and the inner side defines at least a portion of a hot gas flow path through the gas turbine engine;a cooling system within the panel that receives cooling fluid from the outer side of the panel for cooling the panel, the cooling system comprising: at least one cooling fluid supply passage within the panel that receives the cooling fluid from the outer side of the panel and delivers the cooling fluid to a first cooling fluid chamber within the panel;at least one serpentine cooling passage that receives the cooling fluid from the first cooling fluid chamber, the cooling fluid providing convective cooling to the panel as it passes through the at least one serpentine cooling passage;a plurality of transitional cooling fluid passages that receive the cooling fluid from the first cooling fluid chamber and discharge the cooling fluid toward the at least one serpentine cooling passage; andat least one cooling fluid discharge passage that discharges the cooling fluid from the cooling system. 2. The ring segment of claim 1, further comprising a second cooling fluid chamber extending circumferentially within the panel, wherein the second cooling fluid chamber receives the cooling fluid from each of the transitional cooling fluid passages and delivers the cooling fluid to the at least one serpentine cooling passage. 3. The ring segment of claim 2, further comprising a third cooling fluid chamber extending circumferentially within the panel, wherein the third cooling fluid chamber receives the cooling fluid from the at least one serpentine cooling passage and delivers the cooling fluid to the at least one cooling fluid discharge passage. 4. The ring segment of claim 3, wherein the at least one cooling fluid supply passage comprises a plurality of cooling fluid supply passages entirely located within the panel and the at least one cooling fluid discharge passage comprises a plurality of cooling fluid discharge passages. 5. The ring segment of claim 1, wherein the at least one serpentine cooling passage comprises at least two turns of about 180 degrees. 6. The ring segment of claim 5, wherein the turns are configured such that the cooling fluid passing through the at least one serpentine cooling passage flows generally axially toward the trailing edge, turns about 180 degrees and flows generally axially toward the leading edge, and again turns about 180 degrees and flows generally axially toward the trailing edge. 7. The ring segment of claim 6, wherein the at least one serpentine cooling passage is configured such that axially extending portions thereof are located circumferentially adjacent to each other at substantially the same radial location. 8. The ring segment of claim 5, wherein the at least one serpentine cooling passage comprises a plurality of serpentine cooling passages. 9. The ring segment of claim 1, wherein the first cooling fluid chamber extends within the panel from the first mating edge to the second mating edge. 10. The ring segment of claim 1, wherein the first cooling fluid chamber is located in the panel near the leading edge. 11. The ring segment of claim 1, further comprising a plurality of turbulator ribs located in the at least one serpentine cooling passage, the turbulator ribs turbulating the cooling fluid as it passes through the at least one serpentine cooling passage. 12. The ring segment of claim 1, wherein the at least one serpentine cooling passage is located at the same radial location as a portion of the at least one cooling fluid supply passage. 13. The ring segment of claim 1, wherein the at least one cooling fluid supply passage is entirely located within the panel and is angled in a radially inward direction and toward the leading edge of the panel such that the cooling fluid entering the at least one cooling fluid supply passage is able to approach the inner side of the panel near the leading edge. 14. The ring segment of claim 1, wherein the transitional cooling fluid passages extend generally axially through the panel toward the trailing edge of the panel. 15. A ring segment for a gas turbine engine comprising: a panel having a leading edge, a trailing edge, a first mating edge, a second mating edge, an outer side, and an inner side, wherein cooling fluid is provided to the outer side and the inner side defines at least a portion of a hot gas flow path through the gas turbine engine;a cooling system within the panel that receives cooling fluid from the outer side of the panel for cooling the panel, the cooling system comprising: a plurality of cooling fluid supply passages that receive the cooling fluid from the outer side of the panel and deliver the cooling fluid to a first cooling fluid chamber within the panel, the first cooling fluid chamber extending circumferentially between the first and second mating edges of the panel and being located near the leading edge of the panel;at least one serpentine cooling passage downstream from the first cooling fluid chamber and receiving the cooling fluid from the outer side of the panel, the cooling fluid providing convective cooling to the panel as it passes through the at least one serpentine cooling passage, wherein the at least one serpentine cooling passage comprises at least two turns of about 180 degrees, the turns being configured such that the cooling fluid passing through the at least one serpentine cooling passage flows generally axially toward the trailing edge, turns about 180 degrees and flows generally axially toward the leading edge, and again turns about 180 degrees and flows generally axially toward the trailing edge;a plurality of generally axially extending transitional cooling fluid passages that receive the cooling fluid from the first cooling fluid chamber and discharge the cooling fluid toward the at least one serpentine cooling passage; andat least one cooling fluid discharge passage that discharges the cooling fluid from the cooling system. 16. The ring segment of claim 15, wherein the at least one serpentine cooling passage is configured such that axially extending portions thereof are located circumferentially adjacent to each other at substantially the same radial location. 17. The ring segment of claim 16, wherein the at least one serpentine cooling passage comprises a plurality of serpentine cooling passages. 18. The ring segment of claim 17, further comprising a second cooling fluid chamber within the panel, the second cooling fluid chamber extending circumferentially between the first and second mating edges of the panel, wherein the second cooling fluid chamber receives the cooling fluid from the transitional cooling fluid passages and delivers the cooling fluid to the serpentine cooling passages. 19. The ring segment of claim 18, further comprising a third cooling fluid chamber within the panel, the third cooling fluid chamber extending circumferentially between the first and second mating edges of the panel, wherein the third cooling fluid chamber receives the cooling fluid from the serpentine cooling passages and delivers the cooling fluid to the at least one cooling fluid discharge passage. 20. The ring segment of claim 19, wherein the at least one cooling fluid discharge passage comprises a plurality of cooling fluid discharge passages.
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