Turbine blade having a constant thickness airfoil skin
A turbine blade is provided for a gas turbine comprising: a support structure comprising a base defining a root of the blade and a framework extending radially outwardly from the base, and an outer skin coupled to the support structure framework. The skin has a generally constant thickness along substantially the entire radial extent thereof. The framework and the skin define an airfoil of the blade.
1. A turbine blade for a gas turbine comprising:
a support structure comprising a base defining a root of said blade and a framework extending radially outwardly from said base, said support structure framework comprising:
a plurality of spars extending radially outwardly from said base;
a plurality of first tabs extending away from a leading spar; and
a plurality of second tabs extending away from a trailing spar, said skin being coupled to said spars and said first and second tabs; and
an outer skin coupled to said support structure framework, said skin having a generally constant thickness along substantially the entire radial extent thereof, and said framework and said skin defining an airfoil of said blade.
2. The turbine blade as set out in claim 1 , wherein said support structure framework further comprises a plurality of stringers extending between said spars.
3. The turbine blade as set out in claim 2 , wherein cooling openings are provided in said spars and said stringers.
4. The turbine blade as set out in claim 1 , further comprising a tip cap coupled to said spars.
5. The turbine blade as set out in claim 2 , further comprising a damping element extending through openings provided in said stringers, said damping element comprising at least one damping bulb making contact with and extending between opposing sections of said skin, said damping bulb damping vibrations in said skin.
6. The turbine blade as set out in claim 1 , further comprising at least one platform section, non-integral with and located adjacent to said airfoil.
7. The turbine blade as set out in claim 6 , wherein said blade root is mounted to a disk and said platform section is coupled to the disk.
8. The turbine blade as set out in claim 1 , wherein said skin has a thickness falling within a range of from about 0.010 inch to about 0.040 inch.
9. The turbine blade as set out in claim 1 , wherein a thickness of said support structure framework becomes smaller in a radial direction from a first end adjacent said base to a second end opposite said first end.
10. A turbine blade for a gas turbine comprising:
a support structure comprising a base defining a root of said blade and a framework extending radially outwardly from said base;
a skin coupled to said support structure framework, said framework and said skin defining an airfoil of said blade; and
a damping element extending through openings provided in said support structure framework, said damping element comprising a rod having at least one member making contact with and extending between opposing sections of said skin, said member damping vibrations in said skin.
11. The turbine blade as set out in claim 10 , wherein said support structure framework comprises a plurality of spars extending radially outwardly from said base and a plurality of stringers extending between said spars, said openings being provided in said stringers.
12. The turbine blade as set out in claim 10 , wherein said at least one member comprises at least one bulb.
13. The turbine blade as set out in claim 10 , wherein a thickness of said support structure framework becomes smaller in a radial direction from a first end adjacent said base to a second end opposite said first end.
14. A turbine blade for a gas turbine mounted to a rotor disk comprising:
a support structure comprising a base defining a curved root of said blade and a framework extending radially outwardly from said base;
a skin coupled to said support structure framework, said framework and said skin defining a curved airfoil of said blade; and
at least one curved platform section located adjacent to said airfoil and coupled to said rotor disk.
15. The turbine blade as set out in claim 14 , wherein said blade root is mounted to said rotor disk.
16. The turbine blade as set out in claim 15 , wherein said platform section is bolted to said rotor disk at one location on said platform and further coupled to said rotor disk via a non-bolted mechanical connection at another location on said platform.
17. The turbine blade as set out in claim 14 , wherein said at least one platform section comprises first and second platform sections mounted on opposing sides of said airfoil.
18. The turbine blade as set out in claim 14 , wherein said root, said airfoil, and said platform section are curved in an axial and circumferential plane.
19. The turbine blade as set out in claim 14 , wherein said support structure framework comprises:
a plurality of spars extending radially outwardly from said base;
a plurality of first tabs extending away from a leading spar; and
a plurality of second tabs extending away from a trailing spar, said skin being coupled to said spars and said first and second tabs.
20. The turbine blade as set out in claim 14 , wherein said support structure framework comprises a plurality of stringers and a damping element extending through openings provided in said stringers, said damping element making contact with and extending between opposing sections of said skin, said damping element damping vibrations in said skin.