Stress relieved blade support
AssigneeGeneral Electric Company
InventorTodd J. Ganshaw
Life of this patent
Estimating the term…
Abstract
A rotor blade having a dovetail is mounted in a complementary slot in a rotor disk, with radially engaging outer and inner pressure faces, respectively. Relief grooves are provided for reducing stiffness at contact edges between the pressure faces to reduce peak stress thereat.
Claims20
A gas turbine engine rotor blade mountable in a slot of a rotor disk, comprising:
- an airfoil;
- a platform integrally joined to said airfoil;
- and
- a dovetail integrally joined to said platform, and including a neck of minimum cross sectional area extending between a pair of dovetail lobes configured to engage said disk slot;
- each of said lobes including an outer face facing outwardly to engage corresponding inner faces of said disk slot between corresponding inner and outer edges of contact of said lobes;
- and
- a relief groove disposed in each of said lobes inboard said inner contact edge thereof for reducing stiffness at said inner contact edge to reduce peak stress thereat.
A gas turbine engine rotor disk for supporting blades comprising:
- a plurality of posts spaced apart circumferentially by corresponding dovetail slots for receiving corresponding dovetails of said blades;
- each of said posts having opposite first and second lobes with inner faces facing radially inwardly to engage corresponding outer faces of said blade dovetails between edges of contact;
- and
- relief grooves disposed in said lobes outboard said contact edges.
A rotor blade having a dovetail mounted in a complementary slot in a rotor disk, with radially engaging outer and inner pressure faces, respectively, extending between corresponding edges of contact, and means for reducing stiffness at said contact edges to reduce peak stress thereat.
Dependencies are inferred from the claim text.