High speed rotor assembly shroud
View Patent ↗An improved rotor assembly shroud includes at least one reinforcing flange on the upper surface of the shroud. The strength provided by the reinforcing flange allows for a smaller shroud thickness resulting in a net reduction of shroud mass. The lower shroud mass reduces the centrifugal stress on the rotor assembly blade during operation. The strength provided by the reinforcing flanges also significantly reduces the centrifugal bending stress on the shroud during operation. The shroud mass may be further reduced by tapering the shroud leading and trailing edges or, for shrouds incorporating a damper, by providing a damper cavity with a lower diameter surface defining an opening therethrough.
1. A blade of a rotor assembly, said blade comprising:
a root portion;
an airfoil portion extending radially from said root portion;
a shroud extending radially from said airfoil portion, said shroud having a lower portion with a thickness in a radial direction and including at least one reinforcing flange extending radially from said lower portion defining a reinforcing flange height and extending axially along said lower portion defining a reinforcing flange width;
wherein said reinforcing flange height is at least three times greater than the minimum thickness of said shroud lower portion.
2. The blade of claim 1 , wherein said reinforcing flange includes a sealing rail extending radially therefrom.
3. The blade of claim 1 , wherein said shroud includes at least two reinforcing flanges wherein the sum of all reinforcing flange widths is at least two times greater than the average height of the reinforcing flanges.
4. The blade of claim 1 , wherein said lower portion extends axially between opposed leading and trailing edges and extends circumferentially between opposed first and second circumferential sides; and wherein said leading edge and trailing edges are tapered in a circumferential direction.
5. The blade of claim 4 , wherein said shroud defines a constant thickness between said opposed leading and trailing edges and said opposed first and second circumferential sides.
6. The blade of claim 1 , wherein said shroud defines a damper cavity having an inner diameter surface and an outer diameter surface.
7. A blade of a rotor assembly, said blade comprising:
a root portion;
an airfoil portion extending radially from said root portion;
a shroud extending radially from said airfoil portion, said shroud having a lower portion with a thickness in a radial direction and including at least one reinforcing flange extending radially from said lower portion defining a reinforcing flange height and extending axially along said lower portion defining a reinforcing flange width, said reinforcing flange height being at least three times greater than the minimum thickness of said shroud lower portion;
wherein said shroud defines a damper cavity having an inner diameter surface and an outer diameter surface, and said damper cavity inner diameter surface defines an opening therethrough, said opening having at least two opposed ledges.
8. A blade of a rotor assembly, said blade comprising:
a root portion;
an airfoil portion extending radially from said root portion;
a shroud extending radially from said airfoil portion, said shroud having a lower portion with a constant thickness in a radial direction and including at least one reinforcing flange extending radially from said lower portion defining a reinforcing flange height and extending axially along said lower portion defining a reinforcing flange width, said reinforcing flange having a radially distal surface that is substantially parallel to said shroud lower portion; and
a sealing rail extending radially from said radially distal surface of said reinforcing flange.
9. The blade of claim 8 , wherein said reinforcing flange height is at least three times greater than the thickness of said shroud.
10. The blade of claim 8 , wherein said shroud includes at least two reinforcing flanges wherein the sum of all reinforcing flange widths is at least two times greater than the average height of the reinforcing flanges.
11. The blade of claim 8 , wherein said lower portion extends axially between opposed leading and trailing edges and extends circumferentially between opposed first and second circumferential sides; and wherein said leading edge and trailing edges are tapered in a circumferential direction.
12. The blade of claim 8 , wherein said shroud defines a damper cavity having an inner diameter surface and an outer diameter surface.
13. A blade of a rotor assembly, said blade comprising:
a root portion;
an airfoil portion extending radially from said root portion;
a shroud extending radially from said airfoil portion, said shroud having a lower portion with a substantially constant thickness in a radial direction and including at least one reinforcing flange extending radially from said lower portion defining a reinforcing flange height and extending axially along said lower portion defining a reinforcing flange width;
wherein said shroud defines a damper cavity having an inner diameter surface and an outer diameter surface, and said damper cavity inner diameter surface defines an opening therethrough, said opening having at least two opposed ledges.
14. A blade of a rotor assembly, said blade comprising:
a root portion;
an airfoil portion extending radially from said root portion;
a shroud extending radially from said airfoil portion, said shroud having a lower portion with a thickness in a radial direction and wherein said lower portion extends axially between opposed leading and trailing edges and extends circumferentially between opposed first and second circumferential sides; said leading and trailing edges being tapered in a circumferential direction;
wherein said shroud defines a damper cavity with an inner diameter surface and an outer diameter surface wherein said damper cavity inner diameter surface defines an opening therethrough, said opening having at least two opposed ledges.
15. The blade of claim 14 , wherein said shroud includes at least one reinforcing flange extending radially from said lower portion defining a reinforcing flange height and extending axially along said lower portion defining a reinforcing flange width; and wherein said reinforcing flange height is at least three times greater than the minimum thickness of said shroud lower portion.
16. The blade of claim 15 , wherein said shroud includes at least two reinforcing flanges wherein the sum of all reinforcing flange widths is at least two times greater than the average height of the reinforcing flanges.
17. The blade of claim 14 , wherein said shroud defines a constant thickness between said opposed leading and trailing edges and said opposed first and second circumferential sides.
18. A blade of a rotor assembly, said blade comprising:
a root portion;
an airfoil portion extending radially from said root portion; and
a shroud extending radially from said airfoil portion, said shroud having a lower portion with a thickness in a radial direction, said shroud defining a damper cavity with an inner diameter surface and an outer diameter surface wherein said damper cavity inner diameter surface defines an opening therethrough, said opening having at least two opposed ledges.
19. The blade of claim 18 , wherein said shroud includes at least one reinforcing flange extending radially from said lower portion defining a reinforcing flange height and extending axially along said lower portion defining a reinforcing flange width; and wherein said reinforcing flange height is at least three times greater than the minimum thickness of said shroud lower portion.
20. The blade of claim 19 , wherein said shroud includes at least two reinforcing flanges wherein the sum of all reinforcing flange widths is at least two times greater than the average height of the reinforcing flanges.
21. The blade of claim 18 , wherein said shroud defines a constant thickness between said opposed leading and trailing edges and said opposed first and second circumferential sides.
22. The blade of claim 18 , wherein said lower portion extends axially between opposed leading and trailing edges and extends circumferentially between opposed first and second circumferential sides; and wherein said leading edge and trailing edges are tapered in a circumferential direction.