Carlson, Gaskey & Olds, P.C.
Gas turbine engine blade with variable density and wide chord tip
A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil includes a first portion near the airfoil base with a first density and includes a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction.
UNITED TECHNOLOGIES CORPORATION
F F F Y F F F
F05D F01D F01D Y02T F05D F01D F01D
additional inventional inventional additional additional inventional inventional
Pitchaiah Vijay David R. James D.
Chakka Pack Hill