Dust resistant platform blade
AssigneeGeneral Electric Company
InventorsChing-Pang Lee, Darek Tomasz Zatorski, Brian Alan Norton, Jan Christopher Schilling
Life of this patent
Estimating the term…
Abstract
A gas turbine engine rotor blade includes an airfoil, platform, shank, and dovetail integrally joined together. A dust escape hole extends through the platform adjacent a fillet bridging the platform and shank to bleed dust therefrom during operation.
Claims29
A turbine rotor blade comprising a hollow airfoil, platform, shank, and dovetail integrally joined together, with a dust escape hole extending through said platform adjacent a fillet bridging said platform and shank and being larger in diameter than a film cooling hole extending through said airfoil.
A turbine rotor blade comprising:
- a hollow airfoil joined in turn to a platform, shank, and supporting dovetail;
- said airfoil including opposite pressure and suction sides extending longitudinally in span from a root at said platform to an opposite tip, and axially in chord between opposite leading and trailing edges, and further including a film cooling hole therein;
- said platform extending laterally from both said pressure and suction sides, and integrally joined to a forward seal at said leading edge and to an aft seal at said trailing edge;
- and
- said platform joins said shank at a fillet, and includes a dust escape hole being larger in diameter than said film cooling hole and adjoining said fillet to bleed dust therefrom.
A turbine rotor blade comprising an airfoil, platform, shank, and dovetail integrally joined together, with said platform being imperforate except for no more than three dust escape holes extending therethrough adjacent a fillet bridging said platform and shank.
Dependencies are inferred from the claim text.