Back to results
US 11,391,167 B2Granted
Hybrid airfoil for gas turbine engines
AssigneeRaytheon Technologies Corporation
InventorsJason Husband, James Glaspey
Life of this patent
Estimating the term…
Abstract
An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending from a root section. The airfoil section includes a sheath that receives a core. The core includes first and second ligaments received in respective internal channels defined by the sheath, and each one of the first and second ligaments includes at least one interface portion in the root section dimensioned to receive a retention pin.
Claims21
An airfoil for a gas turbine engine comprising:
- an airfoil section extending from a root section, the airfoil section extending between a leading edge and a trailing edge in a chordwise direction and extending between a tip portion and the root section in a radial direction, and the airfoil section defining a pressure side and a suction side separated in a thickness direction;
- wherein the airfoil section includes a metallic sheath that receives a composite core, and the core includes first and second ligaments received in respective internal channels defined by in a thickness of a first skin of the sheath such that the first and second ligaments are spaced apart along the root section with respect to the chordwise direction;
- wherein each one of the first and second ligaments includes at least one interface portion in the root section, and the at least one interface portion of the first ligament and the at least one interface portion of the second ligament define respective sets of bores each dimensioned to receive a retention pin;
- and
- wherein each one of the first and second ligaments includes a plurality of composite layers that loop around the at least one interface portion, the plurality of composite layers includes a first layer and a second layer between the first layer and the at least one interface portion, the first layer defining a first fiber construction, and the second layer defining a second fiber construction that differs from the first fiber construction.
2 more elements
A rotor assembly for a gas turbine engine comprising:
- a rotatable hub including a main body extending along a longitudinal axis and an array of annular flanges extending about an outer periphery of the main body;
- an array of airfoils circumferentially distributed about the outer periphery, each one of the airfoils comprising:
- an airfoil section extending from a root section;
- wherein the airfoil section includes a metallic sheath that receives a composite core, the core includes a plurality of ligaments received in respective internal channels defined in a thickness of a first skin of the sheath such that the ligaments are spaced apart in the root section with respect to the longitudinal axis;
- and
- wherein each one of the ligaments includes at least one interface portion in the root section, and each one of the ligaments includes at least one composite layer that loops around the at least one interface portion such that opposed end portions of at least one composite layer are joined together along the airfoil section;
- a plurality of retention pins, each one of the retention pins extending through the root section of a respective one of the airfoils and through the array of annular flanges to mechanically attach the root section to the hub, wherein the at least one interface portion includes a mandrel tapering from a bushing to define a teardrop profile, the bushing slideably receiving a respective one of the retention pins, and the at least one composite layer follows a contour of the respective mandrel;
- and
- an array of platforms mechanically attached to the hub and that abut against respective pairs of the airfoils radially outward of the retention pins.
6 more elements
A rotor assembly for a gas turbine engine comprising:
- a rotatable hub including a main body extending along a longitudinal axis and an array of annular flanges extending about an outer periphery of the main body;
- an array of airfoils circumferentially distributed about the outer periphery, each one of the airfoils comprising:
- an airfoil section extending from a root section;
- wherein the airfoil section includes a metallic sheath that receives a composite core, the core includes a plurality of ligaments received in respective internal channels defined in the thickness of a first skin of the sheath such that the ligaments are spaced apart in the root section with respect to the longitudinal axis;
- wherein each one of the ligaments includes at least one interface portion in the root section, and each one of the ligaments includes at least one composite layer that loops around and tapers inwardly from the at least one interface portion such that opposed end portions of at least one composite layer are joined together along the airfoil section;
- a plurality of retention pins, each one of the retention pins extending through the root section of a respective one of the airfoils and through the array of annular flanges to mechanically attach the root section to the hub;
- an array of platforms mechanically attached to the hub and that abut against respective pairs of the airfoils radially outward of the retention pins;
- and
- an array of composite shrouds extending outwardly from pressure and suction sides of the respective airfoil section at a position radially outward of the platforms.
6 more elements
Dependencies are inferred from the claim text.