Frangible Gas Turbine Engine Airfoil
First Claim
1. An airfoil for an aircraft engine, the airfoil comprisinga plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base, including at least one discontinuous ply includinga first ply segment,a second ply segment, anda first butt joint disposed between the first ply segment and the second ply segment along a first fragment profile to frangibly attach the first and second ply segments.
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Accused Products
Abstract
An airfoil for an aircraft engine is provided. The airfoil may include a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base. The airfoil may include at least one discontinuous ply having a first ply segment, a second ply segment, and a butt joint disposed between the first ply segment and the second ply segment. The butt joint may be disposed along a first fragment profile to frangibly attach the first and second ply segments.
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Citations
20 Claims
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1. An airfoil for an aircraft engine, the airfoil comprising
a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base, including at least one discontinuous ply including a first ply segment, a second ply segment, and a first butt joint disposed between the first ply segment and the second ply segment along a first fragment profile to frangibly attach the first and second ply segments.
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11. A gas turbine engine defining a central axis, the gas turbine engine comprising:
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an engine shaft extending along the central axis; a compressor attached to the engine shaft and extending radially about the central axis; a combustor positioned downstream of the compressor to receive a compressed fluid therefrom; a turbine mounted on the engine shaft downstream of the combustor to provide a rotational force to the compressor; and a fan section including a plurality of radially-extending fan blades operably connected to the engine shaft, each fan blade including a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base, each fan blade including at least one discontinuous ply including a first ply segment, a second ply segment, and a first butt joint disposed between the first ply segment and the second ply segment along a first fragment profile to frangibly attach the first and second ply segments. - View Dependent Claims (12, 13, 14, 15, 16, 17, 18, 19, 20)
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Specification