Airfoil for a gas turbine engine
AssigneeGeneral Electric Company
InventorsNicholas Joseph Kray, Nitesh Jain
Life of this patent
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Abstract
In one exemplary embodiment of the present disclosure an airfoil is provided. The airfoil defines a spanwise direction, a root end, and a tip end. The airfoil includes: a body defining a pressure side and a suction side and extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a spar enclosed in the body of the airfoil extending along the spanwise direction, the spar comprising a plurality of spar segments arranged in an overlapping configuration along the spanwise direction.
Claims5
A gas turbine engine comprising:
- an airfoil defining a spanwise direction, a root end, and a tip end, the airfoil comprising
- a body defining a pressure side and a suction side and extending along the spanwise direction between the root end and the tip end, the body formed of a composite material;
- and
- a spar enclosed in the body of the airfoil extending along the spanwise direction, the spar comprising a plurality of spar segments arranged in an overlapping configuration along the spanwise direction;
- wherein the plurality of spar segments includes a first spar segment and a second spar segment, wherein the first spar segment overlaps with the second spar segment at a first overlap section of the first spar segment, wherein the first spar segment defines a first overall length and a first overlap length of the first overlap section, wherein the first overlap length is equal to 15% or less of the first overall length.
An airfoil defining a spanwise direction, a root end, and a tip end, the airfoil comprising:
- a body defining a pressure side and a suction side and extending along the spanwise direction between the root end and the tip end, the body formed of a composite material;
- and
- a spar enclosed in the body of the airfoil extending along the spanwise direction, the spar comprising a plurality of spar segments arranged in an overlapping configuration along the spanwise direction;
- wherein the spar is a first spar, wherein the body of the airfoil further includes a second spar, wherein the first spar is a pressure side spar and wherein the second spar is a suction side spar;
- and
- wherein the first spar defines a plurality of overlap sections, wherein the second spar defines a plurality of overlap sections, and wherein the plurality of overlap section of the first spar are arranged in a unique configuration relative to the plurality of overlap sections of the second spar.
Dependencies are inferred from the claim text.