Composite fan blade with leading edge sheath and energy absorbing insert
AssigneeRtx Corporation
InventorLarry Foster
Life of this patent
Estimating the term…
Abstract
An airfoil for a gas turbine engine includes a blade body, a leading edge sheath, and an energy absorbing insert. The blade body has a pressure side and a suction side that each between a forward portion and a trailing edge. The leading edge sheath has a leading edge portion that is spaced apart from the forward portion, a first arm that engages the pressure side, and a second arm that engages the suction side. A cavity is defined between the leading edge portion, the first arm, the second arm, and the forward portion. The energy absorbing insert is disposed within the cavity and improves the impact resistance of the airfoil.
Claims10
An airfoil for a gas turbine engine, comprising:
- a blade body having a forward face, a pressure side and a suction side, each of the pressure side and the suction side extending between a forward portion and a trailing edge;
- a leading edge sheath having a leading edge portion that is spaced apart from the forward portion, a first arm that engages the pressure side, and a second arm that engages the suction side, a cavity being defined between the leading edge portion, the first arm, the second arm, and the forward portion;
- and
- an energy absorbing insert including an insert face, the energy absorbing insert being disposed within the cavity, the energy absorbing insert being made of a non-Newtonian material, wherein the energy absorbing insert is arranged with the blade body such that the insert face extends completely across a width of the forward face, the width extending from the pressure side and the suction side.
A method of manufacturing an airfoil, comprising:
- forming a blade body having a forward face, a pressure side, and a suction side, each of the pressure side and the suction side extending between a forward portion and a trailing edge;
- providing a leading edge sheath having a leading edge portion, a first arm extending from the leading edge portion, and a second arm extending from the leading edge portion;
- positioning the leading edge sheath relative to the blade body such that the leading edge portion is spaced apart from the forward portion;
- joining the first arm to the pressure side and the second arm to the suction side, such that a cavity is defined between the leading edge portion, the first arm, the second arm, and the forward portion;
- and
- inserting an energy absorbing insert into the cavity, the energy absorbing insert being made of a non-Newtonian material, wherein the energy absorbing insert has an insert face and the energy absorbing insert is arranged with the blade body such that the insert face extends completely across a width of the forward face, the width extending from the pressure side and the suction side.
A method of manufacturing an airfoil, comprising:
- forming a blade body having a pressure side and a suction side each extending radially between a root and a tip and each extending between a forward portion and a trailing edge, the forward portion defining a forward face;
- and
- bonding an energy absorbing insert to the forward face of the forward portion that extends between the root and the tip, the energy absorbing insert being made of a non-Newtonian material, wherein the energy absorbing insert has an insert face and the energy absorbing insert is arranged with the blade body such that the insert face extends completely across a width of the forward face, the width extending from the pressure side and the suction side.
Dependencies are inferred from the claim text.