COVER PLATE WITH INTERSTAGE SEAL FOR A GAS TURBINE ENGINE
First Claim
Patent Images
1. An air seal assembly for a gas turbine engine comprising:
- a first rotor disk defined about an axis of rotation;
a second rotor disk defined about said axis of rotation;
a vane structure axially between said first rotor disk and said second rotor disk;
a first cover plate with a radially extending knife edge seal defined about said axis of rotation, said first cover plate mountable to an aft surface of said first rotor disk for rotation therewith, said first radially extending knife edge seal interfaces with said vane structure; and
a second cover plate with a second radially extending knife edge seal defined about said axis of rotation, said second cover plate mountable to a forward surface of said second rotor disk for rotation therewith, said second radially extending knife edge seal interfaces with said vane structure.
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Abstract
An air seal assembly for a gas turbine engine includes a first cover plate with a radially extending knife edge seal defined about and axis of rotation. The first cover plate is mountable to a first rotor disk for rotation therewith, the first radially extending knife edge seal interfaces with a vane structure. A second cover plate with a second radially extending knife edge seal defined about the axis of rotation, the second cover plate mountable to the second rotor disk for rotation therewith. The second radially extending knife edge seal interfaces with the vane structure.
25 Citations
17 Claims
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1. An air seal assembly for a gas turbine engine comprising:
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a first rotor disk defined about an axis of rotation; a second rotor disk defined about said axis of rotation; a vane structure axially between said first rotor disk and said second rotor disk; a first cover plate with a radially extending knife edge seal defined about said axis of rotation, said first cover plate mountable to an aft surface of said first rotor disk for rotation therewith, said first radially extending knife edge seal interfaces with said vane structure; and a second cover plate with a second radially extending knife edge seal defined about said axis of rotation, said second cover plate mountable to a forward surface of said second rotor disk for rotation therewith, said second radially extending knife edge seal interfaces with said vane structure. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14)
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15. A method to assemble an air seal assembly of a gas turbine engine comprising:
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mounting a first cover plate with a radially extending knife edge seal defined about a axis of rotation to a first rotor disk for rotation therewith, the first radially extending knife edge seal interfacing with a vane structure; and mounting a second cover plate with a radially extending knife edge seal defined about a axis of rotation to a second rotor disk for rotation therewith, the second radially extending knife edge seal interfacing with the vane structure. - View Dependent Claims (16, 17)
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Specification