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US 4,536,129 AGranted
Turbine blade with disk rim shield
AssigneeUnited Technologies Corporation
InventorAlan L. Jankot
Life of this patent
Estimating the term…
Abstract
In a gas turbine engine the turbine blade has protective flanges closely overlying the rim of the rotor to shield the rotor from the hot power gases and to form a path for cooling air. These flanges are spaced radially inward from the flanges on the blade that define the inner wall of the gas path through the turbine.
Claims5
A turbine blade having
- an airfoil section,
- a platform at the inner end of the airfoil section,
- a shank extending from the platform from the side opposite to the airfoil section,
- opposed flanges extending outwardly in substantially parallel relation to the platform at the end of the shank, and
- a blade root immediately at the end of the shank on the other side of the flanges, said opposed flanges being of such a dimension that when the blade is assembled on the disk, the flanges of adjacent blades will be closely adjacent to one another and closely overlying and in spaced relation to the rim of the disk to form an axial air passage at said rim.
2 more elements
The combination with a disk having spaced slots in the periphery to receive the blade roots with a portion of the rim located between adjacent slots of turbine blades having roots positioned in said slots,
- each blade having flanges extending over the rim portions at the outer end of the root and closely overlying the rim portions of the disk in closely spaced relation thereto to form an axial cooling air passage therebetween,
- struts extending outwardly from the roots on the sides of the flanges opposite to the roots,
- platforms at the end of the struts, and
- airfoil portions extending outwardly from said platforms.
1 more element
Dependencies are inferred from the claim text.