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US 11,377,969 B2Granted
Extended root region and platform over-wrap for a blade of a gas turbine engine
AssigneeRaytheon Technologies Corporation
InventorMichael G. McCaffrey
Life of this patent
Estimating the term…
Abstract
A rotor blade for a gas turbine engine including an inner ply layer group that at least partially defines a base of a root region; a platform around the inner ply layer group that at least partially defines the base; and a platform over-wrap around the platform, the platform over-wrap at least partially defines the base.
Claims18
A rotor blade for a gas turbine engine, comprising:
- an inner ply layer group that at least partially defines a base of a root region, wherein the base is a bottommost surface of the root region;
- a platform that comprises at least two platform sections, which, in combination, define the platform and surround the inner ply layer group;
- and
- a platform over-wrap around the platform, the platform over-wrap formed as a continuous band that wraps around the at least two platform sections.
1 more element
A method of manufacturing a rotor blade of a gas turbine engine, comprising:
- assembling a platform around an inner ply layer group, the platform and the inner ply layer group at least partially forming a base of a root region, wherein the base is a bottommost surface of the root region;
- wrapping the platform with a platform over-wrap, the platform comprises at least two platform sections which, in combination, define the platform and surround the inner ply layer group, the platform over-wrap at least partially forming the base;
- and
- forming the platform over-wrap as a continuous band that wraps around the at least two platform sections.
1 more element
Dependencies are inferred from the claim text.