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US 8,292,583 B2Granted
Turbine blade having a constant thickness airfoil skin
AssigneeSiemens Energy, Inc.
InventorJohn J. Marra
Life of this patent
Estimating the term…
Abstract
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.
Claims20
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.
4 more elements
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.
1 more element
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.
1 more element
Dependencies are inferred from the claim text.