IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0439277
(2012-04-04)
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등록번호 |
US-8961108
(2015-02-24)
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발명자
/ 주소 |
- Bergman, Russell J.
- Gregg, Shawn J.
- Papple, Michael
- Lutjen, Paul M.
- Caprario, Joseph T.
- Ennacer, Mohammed
- Dabbs, Thurman Carlo
|
출원인 / 주소 |
- United Technologies Corporation
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대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
5 |
초록
▼
A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. T
A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.
대표청구항
▼
1. A cooling system for a gas turbine engine, the cooling system comprising: a first plenum bounded in part by a first portion of an engine casing and a mounting hook; the first portion of the engine casing disposed radially outward from a rotor stage adjacent to a stator vane; the mounting hook con
1. A cooling system for a gas turbine engine, the cooling system comprising: a first plenum bounded in part by a first portion of an engine casing and a mounting hook; the first portion of the engine casing disposed radially outward from a rotor stage adjacent to a stator vane; the mounting hook connecting the stator vane to the engine casing between the first portion of the engine casing and a second portion of the engine casing disposed radially outward from the stator vane;a first cooling flow passageway in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane; the first airfoil cooling channel for cooling a leading edge of the airfoil; the first cooling flow passageway disposed within the mounting hook; anda second cooling flow passageway in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane; the second cooling flow passageway disposed within the mounting hook;wherein the first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other. 2. The system of claim 1, wherein the second cooling flow passageway is in fluid communication with the first plenum by way of fluid communication with a cooling channel within a BOAS of the rotor stage. 3. The system of claim 2, wherein fluid communication between the first plenum and the first cooling flow passageway is isolated from fluid communication between the cooling channel within the BOAS and the second cooling flow passageway by a seal; the seal disposed between the mounting hook and the BOAS. 4. The system of claim 3, wherein the seal is at least one of a W seal, a dog bone seal, a brush seal, a rope seal, a C seal, a crush seal, a flap seal, and a feather seal. 5. The system of claim 1, wherein the first cooling flow passageway is within an alignment feature of the mounting hook. 6. The system of claim 5, wherein the alignment feature extends through an opening in a BOAS support structure of the rotor stage. 7. The system of claim 5, wherein the first cooling flow passageway is in fluid communication with the first plenum by way of a transfer tube between an opening in the BOAS support structure and the first cooling flow passageway. 8. The system of claim 1, wherein cooling system further comprises: a second plenum bounded in part by the second portion of the engine casing and the mounting hook;a third cooling flow passageway in fluid communication with the second plenum and with a second airfoil cooling channel within an airfoil of the stator vane. 9. The system of claim 8, wherein the first plenum and the second plenum each supply cooling air; and the first plenum supplies cooling air at a higher air pressure than the second plenum. 10. A method of cooling a portion of a gas turbine engine comprises: providing a first source of cooling air to a first plenum;flowing a first cooling air flow from the first plenum to a first airfoil cooling channel within an airfoil of a stator vane; the first airfoil cooling channel for cooling a leading edge of the airfoil; the first cooling air flow passing through a first cooling flow passageway disposed within a mounting hook of the stator vane; andflowing a second cooling air flow from the first plenum to a cooling channel within an outer diameter vane platform, the second cooling air flow passing through a second cooling flow passageway disposed within the mounting hook of the stator vane. 11. The method of claim 10, wherein the first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other. 12. The method of claim 10, wherein flowing a second cooling air flow from the first plenum to a cooling channel within an outer diameter vane platform includes flowing the second cooling air flow through a cooling channel within a BOAS of a rotor stage adjacent to the stator vane before flowing the second cooling air flow through the second cooling flow passageway. 13. The method of claim 12, further comprising isolating the first cooling air flow between the first plenum and the first cooling flow passageway from the second cooling air flow between the cooling channel within the BOAS and the second cooling flow passageway. 14. The method of claim 10, wherein the first cooling flow passageway is disposed within an alignment feature of the mounting hook. 15. The method of claim 14, wherein flowing the first cooling air flow from the first plenum to a first airfoil cooling channel within the airfoil includes flowing the first cooling air flow through a transfer tube between the first cooling flow passageway and an opening in a BOAS support structure of a rotor stage adjacent to the stator vane. 16. The method of claim 10, further comprising: providing a second source of cooling air to a second plenum;flowing a third cooling air flow from the second plenum to a second airfoil cooling channel within the airfoil, the third cooling air flow passing through a first cooling flow passageway disposed within the outer diameter platform of the stator vane. 17. The method of claim 16, wherein the cooling air provided to the first plenum is at a higher air pressure than the cooling air provided to the second plenum. 18. A stator vane for a gas turbine engine, the stator vane comprising: a predominantly arcuate inner diameter platform;an airfoil extending from a radially outer surface of the inner diameter platform, the airfoil including a first airfoil cooling channel for cooling a leading edge of the airfoil; anda predominantly arcuate outer diameter platform connected to the airfoil opposite the inner diameter platform; the airfoil connected to a radially inner surface of the outer diameter platform; the outer diameter platform including: a platform cooling channel within the outer diameter platform; anda mounting hook extending radially outward from the outer diameter platform, the mounting hook including: a first side facing the space radially outward from a radially outer surface of the outer diameter platform;a second side facing a direction opposite that of the first side;a first cooling flow passageway disposed within the mounting hook and extending from a first opening in the second side to the first airfoil cooling channel; anda second cooling flow passageway disposed within the mounting hook and extending from a second opening in the second side to the platform cooling channel;wherein the first cooling flow passageway and the second cooling flow passageway do not intersect. 19. The stator vane of claim 18, wherein the second side of the mounting hook further comprises an alignment feature and the first opening is in the alignment feature. 20. The stator vane of claim 19, wherein the first opening is shaped for connecting the first cooling flow passageway to a transfer tube. 21. The stator vane of claim 18, wherein the mounting hook further includes a flange projecting from the second side and running in a circumferential direction, the flange running between the first opening and the second opening. 22. The stator vane of claim 18, wherein a portion of the mounting hook containing a portion of the first cooling flow passageway is thicker than a remaining portion of the mounting hook. 23. The stator vane of claim 18, further comprising: a second airfoil cooling channel within the airfoil, the second airfoil cooling channel farther than the first airfoil cooling channel from the leading edge of the airfoil; anda third cooling flow passageway disposed within the outer diameter platform and extending from the space radially outward from the radially outer surface of the outer diameter platform to the second airfoil cooling channel.
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