Patent ID: 9410438
Filing Date: 2016-08-09
CPC Classification: F01D,F04D,F05D,Y02T,Y10T

Claim Text:
1. A rotor blade for a rotor of a gas turbine engine comprising a first airfoil component extending radially between a root and a tip and a second airfoil component, separate from the first airfoil component, extending radially between a root and a tip, the second airfoil component positioned downstream, in series, of the first airfoil component, the first airfoil component being metal and the second airfoil component being of a composite material, the first airfoil component forming the leading rotor blade component while the second airfoil component forms the trailing rotor blade component whereby the first airfoil component is suitable for transonic tip speeds while resisting foreign damage and erosion, and the composite material of the second airfoil component is a relatively lighter material, wherein an axial gap is defined between the leading airfoil component and the trailing airfoil component, and wherein the axial gap is filled with an elastomer.