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US 6,672,832 B2Granted
Step-down turbine platform
AssigneeGeneral Electric Company
InventorsLeslie Eugene Leeke, Sean Robert Keith, Lawrence Paul Timko
Life of this patent
Estimating the term…
Abstract
A turbine includes a row of blades each having an integral airfoil, platform, and dovetail. Each platform has opposite first and second side edges corresponding with the opposite pressure and suction sides of the airfoil. The platform first side edge is radially higher than the platform second side edge continuously between opposite forward and aft edges of the platform. In this way, adjacent platforms define a down step therebetween for preventing obstruction of combustion gases flowable downstream thereover.
Claims18
A turbine comprising:
- a row of turbine blades extending radially outwardly from a supporting rotor disk;
- each turbine blade including an airfoil, a platform, and dovetail in a unitary assembly;
- each airfoil including opposite pressure and suction sides extending chordally between leading and trailing edges, and radially between a root adjoining said platform and a tip;
- each platform including an outer surface facing radially outwardly around said airfoil root within a perimeter of opposite first and second side edges, and opposite forward and aft edges;
- and
- said platform first side edge being disposed along said airfoil pressure side, said platform second side edge being disposed along said airfoil suction side, said platform first edge being radially higher than said platform inboard therefrom, said platform second edge being radially lower than said platform inboard therefrom, and said first side edge of each platform being radially higher than said second side edge of an adjacent platform continuously between said platform forward and aft edges to define a down step therebetween for preventing obstruction of combustion gases flowable thereover.
3 more elements
A turbine comprising:
- a row of turbine blades extending radially outwardly from a supporting rotor disk;
- each turbine blade including an airfoil, a platform, and dovetail in a unitary assembly;
- each airfoil including opposite pressure and suction sides extending chordally between leading and trailing edges, and radially between a root adjoining said platform and a tip;
- each platform including an outer surface facing radially outwardly around said airfoil root within a perimeter of opposite first and second side edges, and opposite forward and aft edges;
- said platform first side edge being disposed along said airfoil pressure side, said platform second side edge being disposed along said airfoil suction side, said platform first edge being radially higher than said platform inboard therefrom, said platform second edge being radially lower than said platform inboard therefrom, and said first side edge of each platform being radially higher than said second side edge of an adjacent platform continuously between said platform forward and aft edges to define a down step therebetween for preventing obstruction of combustion gases flowable thereover;
- and
- a turbine nozzle disposed upstream from said row of turbine blades, and including a row of nozzle vanes configured for directing said combustion gases downstream between said turbine blades in streamlines directed obliquely across said platform first side edges for step-down over adjacent platform second side edges from said forward to aft edges.
4 more elements
A turbine blade comprising:
- an airfoil, platform, and dovetail in a unitary assembly;
- said airfoil including opposite pressure and suction sides extending chordally between leading and trailing edges, and radially between a root adjoining said platform, and a tip;
- said platform including an outer surface facing radially outwardly around said airfoil root within a perimeter of opposite first and second side edges, and opposite forward and aft edges;
- and
- said platform first side edge being disposed along said airfoil pressure side, said platform second side edge being disposed along said airfoil suction side, said platform first edge being radially higher than said platform inboard therefrom, said platform second edge being radially lower said platform inboard therefrom, and said first side edge being radially higher than said second side edge continuously between said platform forward and aft edges to define a down step with an adjacent one of said turbine blades when mounted in a rotor disk.
2 more elements
Dependencies are inferred from the claim text.