IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0662891
(2012-10-29)
|
등록번호 |
US-9328619
(2016-05-03)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
27 |
초록
▼
A rotating blade for use in a turbomachine is disclosed. In an embodiment, the rotating blade includes an airfoil portion, a root section affixed to a first end of the airfoil portion, and a tip section affixed to a second end of the airfoil portion, the second end being opposite the first end. A pa
A rotating blade for use in a turbomachine is disclosed. In an embodiment, the rotating blade includes an airfoil portion, a root section affixed to a first end of the airfoil portion, and a tip section affixed to a second end of the airfoil portion, the second end being opposite the first end. A part span shroud is affixed to the airfoil portion between the tip section and the root section, wherein the part span shroud further comprises a hollow portion.
대표청구항
▼
1. A rotating blade for a turbomachine, the rotating blade comprising: an airfoil portion;a root section affixed to a first end of the airfoil portion;a tip section affixed to a second end of the airfoil portion, the second end being opposite the first end; anda part span shroud affixed to the airfo
1. A rotating blade for a turbomachine, the rotating blade comprising: an airfoil portion;a root section affixed to a first end of the airfoil portion;a tip section affixed to a second end of the airfoil portion, the second end being opposite the first end; anda part span shroud affixed to the airfoil portion between the root section and the tip section, wherein the part span shroud further comprises a hollow portion extending within the part span shroud and terminating at one of a suction surface of the airfoil portion or a pressure surface of the airfoil portion, andwherein the part span shroud further comprises one of a brazed contact surface or a welded contact surface to enclose the hollow portion within the part span shroud. 2. The rotating blade of claim 1, wherein the hollow portion is disposed in a position that is closer to a leading edge of the part span shroud than a trailing edge of the part span shroud. 3. The rotating blade of claim 1, wherein the part span shroud further comprises a fillet for easing an exterior corner formed by the part span shroud and the airfoil portion. 4. The rotating blade of claim 1, wherein a center of gravity of the part span shroud is laterally aligned with a center of gravity of the blade. 5. The rotating blade of claim 4, wherein the part span shroud is disposed on the airfoil portion nearer to a leading edge than a trailing edge. 6. The rotating blade of claim 1, wherein the rotating blade operates as one of: a front stage blade in a compressor,a latter stage blade in a gas turbine, ora low pressure section blade in a steam turbine. 7. The rotating blade of claim 1, further comprising a blade attachment member projecting from the root section. 8. The rotating blade of claim 1, wherein the hollow portion includes a plurality of cavities within the part span shroud. 9. A turbomachine comprising: a rotor rotatably mounted within a stator, the rotor including:a shaft; andat least one rotor wheel mounted on the shaft, each of the at least one rotor wheels including a plurality of radially outwardly extending blades mounted thereto,wherein each blade includes: an airfoil portion;a root section affixed to a first end of the airfoil portion;a tip section affixed to a second end of the airfoil portion, the second end being opposite the first end; anda part span shroud affixed to the airfoil portion between the root section and the tip section,wherein the part span shroud further comprises a hollow portion extending within the part span shroud and terminating at one of a suction surface of the airfoil portion or a pressure surface of the airfoil portion, andwherein the part span shroud further comprises one of a brazed contact surface or a welded contact surface to enclose the hollow portion within the part span shroud. 10. The turbomachine of claim 9, wherein the hollow portion is disposed in a position that is closer to a leading edge of the part span shroud than a trailing edge of the part span shroud. 11. The turbomachine of claim 9, wherein the part span shroud further comprises a fillet for easing an exterior corner formed by the part span shroud and the airfoil portion. 12. The turbomachine of claim 9, wherein a center of gravity of the part span shroud is laterally aligned with a center of gravity of the blade. 13. The turbomachine of claim 12, wherein the part span shroud is disposed on the airfoil portion nearer to a leading edge than a trailing edge. 14. The turbomachine of claim 9, wherein the turbomachine comprises one of: a gas turbine, a steam turbine, or a compressor. 15. The turbomachine of claim 9, further comprising a blade attachment member projecting from the root section. 16. The turbomachine of claim 9, wherein the hollow portion includes a plurality of cavities within the part span shroud.
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