IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0214760
(2002-08-09)
|
우선권정보 |
EP-0119263 (2001-08-09) |
발명자
/ 주소 |
|
출원인 / 주소 |
- Siemens Aktiengesellschaft
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
5 인용 특허 :
5 |
초록
▼
A turbine blade/vane, having a blade/vane aerofoil which extends along a blade/vane axis and through which cooling medium flows, mainly in the longitudinal direction of the turbine blade/vane, is configured comparatively simply for reliable and effective closed cooling. In particular, it is configur
A turbine blade/vane, having a blade/vane aerofoil which extends along a blade/vane axis and through which cooling medium flows, mainly in the longitudinal direction of the turbine blade/vane, is configured comparatively simply for reliable and effective closed cooling. In particular, it is configured with the use of cooling air as the cooling medium. An incident flow duct and an efflux duct for cooling medium are routed within the blade/vane aerofoil, essentially over its complete length. The incident flow duct and the efflux duct are connected together on the cooling medium side in such a way that cooling medium passing from the incident flow duct into the efflux duct is conducted in a transverse direction along a wall inner surface, which has to be cooled, of the blade/vane aerofoil.
대표청구항
▼
1. A turbine blade/vane comprising:a blade/vane aerofoil which extends along a blade/vane axis and through which a cooling medium can flow, mainly in the longitudinal direction of the turbine blade/vane; an incident flow duct and an efflux duct for the cooling medium, routed within the blade/vane ae
1. A turbine blade/vane comprising:a blade/vane aerofoil which extends along a blade/vane axis and through which a cooling medium can flow, mainly in the longitudinal direction of the turbine blade/vane; an incident flow duct and an efflux duct for the cooling medium, routed within the blade/vane aerofoil, essentially over its complete length, wherein the incident flow duct and the efflux duct are connected together on the cooling medium side such that the cooling medium passing from the incident flow duct into the efflux duct is conducted in a transverse direction along a wall inner surface, which has to be cooled, of the blade/vane aerofoil. 2. The turbine blade/vane as claimed in claim 1, wherein the incident flow duct includes outlet openings for the cooling medium, approximately uniformly distributed over the length of the turbine blade/vane and facing toward the wall inner surface, which has to be cooled, of the blade/vane aerofoil.3. The turbine blade/vane as claimed in claim 1, wherein the free cross section of the incident flow duct in the blade/vane aerofoil decreases in a longitudinal direction of the aerofoil.4. The turbine blade/vane as claimed in claim 3, wherein a free cross section of the incident flow duct in the blade/vane aerofoil decreases linearly in the longitudinal direction of the aerofoil.5. The turbine blade/vane as claimed in claim 4, wherein a free cross section of the efflux duct in the blade/vane aerofoil increases in the longitudinal direction of the aerofoil to correspond with the decrease in the free cross section of the incident flow duct.6. The turbine blade/vane as claimed in claim 1, wherein at least one of the incident flow duct and the efflux duct includes a triangular cross section parallel to the longitudinal direction of the blade/vane aerofoil and at right angles to the wall inner surface, which has to be cooled, of the blade/vane aerofoil.7. The turbine blade/vane as claimed in claim 1, wherein a second incident flow duct for cooling medium for cooling a further wall inner surface of the blade/vane aerofoil is arranged symmetrically, with respect to the blade/vane axis, relative to the first incident flow duct.8. The turbine blade/vane as claimed in claim 7, wherein the first incident flow duct and the second incident flow duct open into a common efflux duct for cooling medium.9. The turbine blade/vane as claimed in claim 1, wherein a wall inner surface, which has to be cooled, of the blade/vane aerofoil is respectively provided with ribs, arranged transversely to the blade/vane axis, which guide the cooling medium.10. The turbine blade/vane as claimed in claim 1, wherein at least one of the incident flow duct is closed at its end remote from an inlet area for cooling medium, and the efflux duct is closed at its beginning remote from an outlet area for cooling medium.11. The turbine blade/vane as claimed in claim 1, further comprising:a platform, extending transversely to the blade/vane axis, formed on the blade/vane aerofoil at its cooling medium efflux end, wherein the platform includes a cooling chamber joined to the incident flow duct and to which cooling medium can be admitted. 12. The turbine blade/vane as claimed in claim 1, further comprising:a platform, extending transversely to the blade/vane axis, formed on the blade/vane aerofoil at its cooling medium incident flow end, wherein the platform includes a cooling chamber joined to the efflux duct and to which cooling medium can be admitted. 13. The turbine blade/vane as claimed in claim 11, wherein a cooling chamber is cast into the platform and is closed toward the outside by a cover panel.14. The turbine blade/vane as claimed in claim 13, wherein the cooling chamber is provided, in a floor area, with an impingement cooling panel arranged at a distance from the chamber floor.15. The turbine blade/vane as claimed in claim 14, wherein an efflux space of the cooling chamber, bounded by the chamber floor and the impingement cooling panel, is joined to the efflux duct.16. The turbine blade/vane as claimed in claim 14, wherein an incident flow space of the cooling chamber, bounded by the cover panel and the impingement cooling panel, is joined to the incident flow duct.17. The turbine blade/vane as claimed in claim 1, configured as a guide vane for a gas turbine.18. The turbine blade/vane as claimed in claim 2, wherein the free cross section of the incident flow duct in the blade/vane aerofoil decreases in a longitudinal direction of the aerofoil.19. The turbine blade/vane as claimed in claim 3, wherein a free cross section of the efflux duct in the blade/vane aerofoil increases in the longitudinal direction of the aerofoil.20. The turbine blade/vane as claimed in claim 2, wherein at least one of the incident flow duct and the efflux duct includes a triangular cross section parallel to the longitudinal direction of the blade/vane aerofoil and at right angles to the wall inner surface, which has to be cooled, of the blade/vane aerofoil.21. The turbine blade/vane as claimed in claim 3, wherein at least one of the incident flow duct and the efflux duct includes a triangular cross section parallel to the longitudinal direction of the blade/vane aerofoil and at right angles to the wall inner surface, which has to be cooled, of the blade/vane aerofoil.22. The turbine blade/vane as claimed in claim 2, wherein a second incident flow duct for cooling medium for cooling a further wall inner surface of the blade/vane aerofoil is arranged symmetrically, with respect to the blade/vane axis, relative to the first incident flow duct.23. The turbine blade/vane as claimed in claim 22, wherein the first incident flow duct and the second incident flow duct open into a common efflux duct for cooling medium.24. The turbine blade/vane as claimed in claim 3, wherein a second incident flow duct for cooling medium for cooling a further wall inner surface of the blade/vane aerofoil is arranged symmetrically, with respect to the blade/vane axis, relative to the first incident flow duct.25. The turbine blade/vane as claimed in claim 24, wherein the first incident flow duct and the second incident flow duct open into a common efflux duct for cooling medium.26. The turbine blade/vane as claimed in claim 2, wherein a wall inner surface, which has to be cooled, of the blade/vane aerofoil is respectively provided with ribs, arranged transversely to the blade/vane axis, which guide the cooling medium.27. The turbine blade/vane as claimed in claim 3, wherein a wall inner surface, which has to be cooled, of the blade/vane aerofoil is respectively provided with ribs, arranged transversely to the blade/vane axis, which guide the cooling medium.28. The turbine blade/vane as claimed in claim 2, wherein at least one of the incident flow duct is closed at its end remote from an inlet area for cooling medium, and the efflux duct is closed at its beginning remote from an outlet area for cooling medium.29. The turbine blade/vane as claimed in claim 11, further comprising:a second platform, extending transversely to the blade/vane axis, formed on the blade/vane aerofoil at its cooling medium incident flow end, wherein the second platform includes a cooling chamber joined to the efflux duct and to which cooling medium can be admitted. 30. A gas turbine, comprising:a turbine blade/vane including, a blade/vane aerofoil which extends along a blade/vane axis and through which a cooling medium can flow, mainly in the longitudinal direction of the turbine blade/vane, and an incident flow duct and an efflux duct for the cooling medium, routed within the blade/vane aerofoil, essentially over its complete length, wherein the incident flow duct and the efflux duct are connected together on the cooling medium side such that the cooling medium passing from the incident flow duct into the efflux duct is conducted in a transverse direction along a wall inner surface, which has to be cooled, of the blade/vane aerofoil.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.