Tear-drop shaped part-span shroud
AssigneeGeneral Electric Company
InventorRohit CHOUHAN
Life of this patent
Estimating the term…
Abstract
A rotatable blade for use in a turbomachine includes an airfoil portion having a leading edge, a trailing edge a radially-inner end and a radially-outer end; a root section affixed to the radially-inner end of the airfoil portion. A part-span shroud is located on the airfoil portion between the root section and the radially-outer end. The part-span shroud is substantially tear-drop shaped such that its cross-sectional shape has a maximum thickness located within 20 to 40% of a chord length extending between leading and trailing edges of the part-span shroud, as measured from the leading edge of the part-span shroud.
Claims20
A rotatable blade for a turbomachine comprising:
- an airfoil portion having a leading edge and a trailing edge, a radially-inner end and a radially-outer end;
- a root section affixed to the radially-inner end of the airfoil portion;
- and
- a substantially tear-drop shaped part-span shroud located on the airfoil portion between the root section and the radially outer end, wherein said part-span shroud is provided with a cross-sectional shape having a maximum thickness located within 20 to 40% of a chord length extending from a leading edge of said part-span shroud to a trailing edge of said part-span shroud, as measured from said leading edge of said part-span shroud.
A turbomachine comprising:
- a rotor rotatably mounted within a stator, the rotor including:
- a shaft;
- at 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 thereon;
- and
- wherein each blade includes an airfoil portion having a leading edge and a trailing edge, a radially-inner end and a radially-outer end, a pressure side and a suction side;
- a root section at the radially-inner end of said airfoil portion;
- and a part-span shroud located on said airfoil portion between said root section and said radially outer end, on said pressure side and said suction side, wherein said part-span shroud is provided with a substantially tear-drop cross-sectional shape having a maximum thickness located within 20 to 40% of a chord length extending between a leading edge of said part-span shroud and a trailing edge of said part-span shroud, as measured from said leading edge of said part-span shroud.
A turbomachine comprising:
- a rotor rotatably mounted within a stator, the rotor including:
- a shaft;
- at 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 thereon;
- and
- wherein each blade includes an airfoil portion having a leading edge and a trailing edge, a radially-inner end and a radially-outer end, a pressure side and a suction side;
- a root section at the radially-inner end of said airfoil portion;
- and a part-span shroud located on said airfoil portion between said root section and said radially outer end, on said pressure side and said suction side, wherein said part-span shroud is provided with a substantially tear-drop cross-sectional shape having a maximum thickness located at 31%, 36% or 37% of a chord length extending between a leading edge of said part-span shroud and a trailing edge of said part-span shroud, as measured from said leading edge of said part-span shroud;
- and wherein said part-span shroud is disposed on the airfoil portion between about 40% to 80% of a radial height of said airfoil portion as measured from the root section of the blade.
Dependencies are inferred from the claim text.