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US 9,039,382 B2Granted
Blade skirt
AssigneeGeneral Electric Company
InventorDavid Scott Stapleton
Life of this patent
Estimating the term…
Abstract
A blade of a gas turbine engine is provided having an airfoil, a platform, a shank, a dovetail, and a skirt. The airfoil may extend distally from the platform, and the shank may extend proximally from the platform. The dovetail may also be provided to extend proximally from the shank. The skirt may be disposed on an aft side of the shank and may extend from the shank in a direction at least partially axially aft from the shank.
Claims18
A gas turbine engine blade comprising:
- a proximal end and a radially opposite distal end, and a forward side and an axially opposite aft side;
- an airfoil, a platform, a shank, and a dovetail;
- wherein said airfoil extends distally from said platform and terminates at said distal end, said shank extends proximally from said platform, and said dovetail extends proximally from said shank and terminates at said proximal end;
- a skirt disposed at least partially on an aft side of said shank and extending at least partially from said shank in a direction that is at least partially axially aft of said shank;
- wherein said skirt includes a skirt radius which serves as a transitioning surface between a proximal surface of said skirt and an aft surface of said shank and also between said aft surface of said shank and a lateral side of said shank.
2 more elements
A gas turbine engine blade comprising:
- a proximal end and a radially opposite distal end, and a forward side and an axially opposed aft side;
- an airfoil, a platform, a shank, and a dovetail;
- wherein said airfoil extends distally from said platform and terminates at said distal end, said shank extends proximally from said platform, and said dovetail extends proximally from said shank and terminates at said proximal end;
- a skirt disposed on said aft side and at least partially extending from said aft side axially proud of an axially aft side surface of said shank;
- wherein said skirt includes a skirt radius which serves as a transitioning surface between a proximal surface of said skirt and said axially aft side surface of said shank and also between said axially aft side surface of said shank and a lateral side of said shank.
2 more elements
A blade for a gas turbine engine comprising:
- a forward end and an axially opposed aft end along a longitudinal axis, and radial axes extending from and perpendicular to said longitudinal axis, each of said radial axes having a proximal end at said longitudinal axis and a radially opposed distal end;
- an airfoil, a platform, a shank, a dovetail, and a skirt;
- wherein said airfoil extends radially distally from said platform along one of said radial axes, said shank extends radially proximally from said platform along one of said radial axes, and said dovetail extends radially proximally from said shank along one of said radial axes;
- said skirt extending at least partially axially aft from said shank;
- wherein said skirt includes a skirt radius which serves as a transitioning surface between a proximal surface of said skirt and an aft surface of said shank and also between said aft surface of said shank and a lateral side of said shank.
2 more elements
Dependencies are inferred from the claim text.