A blade for use in a gas turbine engine has an airfoil including a leading edge and a trailing edge. A sheath is positioned at the leading edge and secured to the airfoil by a first adhesive formed of a first material. The sheath is formed of a second material that is distinct from said first materi
A blade for use in a gas turbine engine has an airfoil including a leading edge and a trailing edge. A sheath is positioned at the leading edge and secured to the airfoil by a first adhesive formed of a first material. The sheath is formed of a second material that is distinct from said first material. The first material is less electrically conductive than the second material. A grounding element is in contact with the sheath. The grounding element is in contact with a portion of the airfoil formed of a third material that is more electrically conductive than the first material. The grounding element and the portion of the airfoil together form a ground path from the sheath into the airfoil.
대표청구항▼
1. A blade for use in a gas turbine engine comprising: an airfoil including a leading edge and a trailing edge,a sheath positioned at the leading edge, said sheath being secured to said airfoil by a first adhesive formed of a first material,said sheath being formed of a second material that is disti
1. A blade for use in a gas turbine engine comprising: an airfoil including a leading edge and a trailing edge,a sheath positioned at the leading edge, said sheath being secured to said airfoil by a first adhesive formed of a first material,said sheath being formed of a second material that is distinct from said first material, said first material being less electrically conductive than said second material;a grounding element in contact with said sheath, and said grounding element being in contact with a forward portion of a main body of said airfoil, said main body of said airfoil being formed of a third material that is more electrically conductive than said first material,said grounding element and said main body of said airfoil together forming a ground path from said sheath into said airfoil; andsaid airfoil extending outwardly to define a radial dimension, and said airfoil extending between suction and pressure sides to define a lateral dimension, andsaid grounding element disposed at a location between said sheath and said forward portion of the main body of said airfoil,the grounding element being positioned both laterally and radially inward of portions of said first adhesive to isolate said grounding element from liquids. 2. The blade as set forth in claim 1, wherein said second material includes titanium, and said third material is aluminum. 3. The blade as set forth in claim 1, wherein said grounding element is a metal piece which is secured to said sheath and said forward portion of the main body of said airfoil. 4. The blade as set forth in claim 1, wherein said grounding element is a second adhesive which is more conductive than said first adhesive. 5. The blade as set forth in claim 4, wherein said second adhesive includes silver-filled silicone. 6. The blade as set forth in claim 1, wherein said blade is a fan blade. 7. A rotor for use in a gas turbine engine comprising: a rotor having a slot receiving a blade, said blade including an airfoil and a dovetail, said dovetail received in said slot;said airfoil including a leading edge and a trailing edge, a sheath positioned at the leading edge, said sheath being secured to said airfoil by a first adhesive formed of a first material, said sheath being formed of a second material that is distinct from said first material, said first material being less electrically conductive than said second material;a grounding element in contact with said sheath, and said grounding element being in contact with a forward portion of a main body of said airfoil, said main body of said airfoil being formed of a third material that is more electrically conductive than said first material, said grounding element and said main body of said airfoil together forming a ground path from said sheath into said airfoil; andsaid airfoil extending outwardly to define a radial dimension, and said airfoil extending between suction and pressure sides to define a lateral dimension, and said grounding element disposed at a location between said sheath and said forward portion of the main body of said airfoil, said grounding element being positioned both laterally and radially inward of portions of said first adhesive to isolate said grounding element from liquids. 8. The rotor as set forth in claim 7, wherein said second material includes titanium, and said third material is aluminum. 9. The rotor as set forth in claim 7, wherein said grounding element is a metal piece which is secured to said sheath and said forward portion of the main body of said airfoil. 10. The rotor as set forth in claim 7, wherein said grounding element is a second adhesive which is more conductive than said first adhesive. 11. The rotor as set forth in claim 10, wherein said second adhesive includes silver-filled silicone. 12. The rotor as set forth in claim 7, wherein said blade is a fan blade and said rotor is a fan rotor. 13. A gas turbine engine comprising: a fan section, a compressor section, a combustor section, and a turbine section, said turbine section having at least one rotor for driving a compressor rotor of said compressor section, and also driving a fan rotor of said fan section through a gear reduction;said fan rotor having a slot receiving a fan blade, said fan blade having a dovetail received in said slot and an airfoil, said airfoil including a leading edge and a trailing edge, a sheath positioned at the leading edge, said sheath being secured to said airfoil by a first adhesive formed of a first material, said sheath being formed of a second material that is distinct from said first material, said first material being less electrically conductive than said second material;a grounding element in contact with said sheath, and said grounding element being in contact with a forward portion of a main body of said airfoil, said main body of said airfoil being formed of a third material that is more electrically conductive than said first material, said grounding element and said main body of said airfoil together forming a ground path from said sheath into said airfoil; andsaid airfoil extending outwardly to define a radial dimension, and said airfoil extending between suction and pressure sides to define a lateral dimension, and said grounding element disposed at a location between said sheath and said forward portion of the main body of said airfoil, the grounding element being positioned both laterally and radially inward of portions of said first adhesive to isolate said grounding element from liquids. 14. The gas turbine engine as set forth in claim 13, wherein said second material includes titanium, and said third material is aluminum. 15. The gas turbine engine as set forth in claim 13, wherein said grounding element is a metal piece which is secured to said sheath and said forward portion of the main body of said airfoil. 16. The as turbine engine as set forth in claim 13, wherein said grounding element is a second adhesive which is more conductive than said first adhesive. 17. The gas turbine engine as set forth in claim 16, wherein said second adhesive includes silver-filled silicone.
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