Integrated bridge turbine blade
AssigneeGeneral Electric Company
InventorsChing-Pang Lee, Richard Clay Haubert, Harvey Michael Maclin
Life of this patent
Estimating the term…
Abstract
A turbine blade includes a hollow airfoil integrally joined to a dovetail. The airfoil includes a perforate first bridge defining a flow channel behind the airfoil leading edge. A second bridge is spaced behind the first bridge and extends from a pressure sidewall of the airfoil short of the airfoil trailing edge. A third bridge has opposite ends joined to the pressure sidewall and the second bridge to define with the first bridge a supply channel for the leading edge channel, and defines with the second bridge a louver channel extending aft along the second bridge to its distal end at the pressure sidewall.
Claims21
A turbine blade comprising:
- a hollow airfoil including a concave pressure sidewall and laterally opposite convex suction sidewall joined together at chordally opposite leading and trailing edges extending in span from a root to a tip;
- a dovetail integrally joined to said airfoil at said root;
- said airfoil further including a perforate first bridge spaced behind said leading edge and integrally joined to said pressure and suction sidewalls to define a leading edge channel therebetween;
- said airfoil further including an imperforate second cold bridge spaced behind said first bridge, and extending integrally from said suction sidewall chordally aft to integrally join said pressure sidewall before said trailing edge to define a first serpentine flow channel adjacent said suction sidewall;
- and
- said airfoil further including an imperforate third bridge disposed between said first and second bridges, and integrally joined at opposite ends to said pressure sidewall and said second bridge in a convex profile to define with said first bridge a complementary concave supply channel for channeling air through said first bridge, and to define with said second bridge a louver channel extending axially aft therealong to a distal end thereof at said pressure sidewall.
A turbine blade comprising:
- a hollow airfoil including a concave pressure sidewall and laterally opposite convex suction sidewall joined together at chordally opposite leading and trailing edges extending in span from a root to a tip;
- a dovetail integrally joined to said airfoil at said root;
- said airfoil further including a perforate first bridge spaced behind said leading edge and integrally joined to said pressure and suction sidewalls to define a leading edge channel therebetween;
- said airfoil further including a second cold bridge spaced behind said first bridge, and extending integrally from said suction sidewall chordally aft to integrally join said pressure sidewall before said trailing edge to define a first serpentine flow channel adjacent said suction sidewall;
- and
- said airfoil further including a third bridge disposed between said first and second bridges, and integrally joined at opposite ends to said pressure sidewall and said second bridge to define with said first bridge a supply channel for channeling air through said first bridge, and to define with said second bridge a louver channel extending axially aft therealong to a distal end thereof at said pressure sidewall.
Dependencies are inferred from the claim text.