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, wherein the hollow portion is devoid of any coupling structure therein.
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, the part span shroud including: a hollow portion devoid of any coupling structure; anda contact surface having a first section, a second section, end a third section, the second section being disposed between the first section and the third section, and being brazed or welded to enclose a portion of the hollow portion. 2. The rotating blade of claim 1, wherein the hollow portion is disposed on an interior of a leading 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 3, wherein a size and a shape of the fillet are optimized based on the part span shroud including the hollow portion. 5. 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. 6. The rotating blade of claim 5, wherein the part span shroud is disposed on the airfoil portion nearer to a leading edge than a trailing edge. 7. 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. 8. The rotating blade of claim 1, wherein the second section is brazed or welded with at least one of: colbalt-chromium-tungsten alloy or cobalt-chromium-molybdenum alloy. 9. The rotating blade of claim 1, wherein the first section and third section are brazed or welded with at least one of: a nickel based alloy or a nickel based super alloy. 10. 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, the part span shroud including: a hollow portion devoid of any coupling structure; anda contact surface having a first section, a second section, and a third section, the second section being disposed between the first section and the third section, and being brazed or welded to enclose a portion of the hollow portion. 11. The turbomachine of claim 10, wherein the hollow portion is disposed on an interior of a leading edge of the part span shroud. 12. The turbomachine of claim 10, wherein the part span shroud further comprises a fillet for easing an exterior corner formed by the part span shroud and the airfoil portion. 13. The turbomachine of claim 12, wherein a size and a shape of the fillet are optimized based on the part span shroud including the hollow portion. 14. The turbomachine of claim 10, wherein a center of gravity of the part span shroud is laterally aligned with a center of gravity of the blade. 15. The turbomachine of claim 14, wherein the part span shroud is disposed on the airfoil portion nearer to a leading edge than a trailing edge. 16. The turbomachine of claim 10, wherein the turbomachine comprises one of: a gas turbine, a steam turbine, or a compressor. 17. The turbomachine of claim 10, wherein the second section is brazed or welded with at least one of: colbalt-chromium-tungsten alloy or cobalt-chromium-molybdenum alloy. 18. The turbomachine of claim 10, wherein the first section and third section are brazed or welded with at least one of: a nickel based alloy or a nickel based super alloy.
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