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US 2015/0315924 A1Published application
Universal seal
AssigneeUnited Technologies Corporation
InventorsBradley T. Duelm, Randall J. Brown, Nathan A. Shirk, Lewis M. Holby
Life of this patent
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Abstract
A seal for a gas turbine engine includes a top, a bottom, a left side, a right side, a back and a front. The back is parallel to the front and the left side is parallel to the right side such that a non-square shape is formed by the intersection of the back, the left side, the front and the right side. The top includes a first vane mating surface and the bottom includes a second vane mating surface.
Claims9
A seal for a gas turbine engine comprising:
- a top;
- a bottom;
- a left side;
- a right side;
- a back;
- and
- a front, wherein said back is parallel to said front and said left side is parallel to said right side such that a non-square shape is formed by the intersection of the back, the left side, the front and the right side, and said top includes a first vane mating surface and said bottom includes a second vane mating surface.
4 more elements
A seal for a gas turbine engine comprising:
- a top surface;
- a bottom surface;
- a first side surface;
- a second side surface;
- a back surface, and
- a front surface, wherein said back surface is parallel to said front surface and said first side surface is parallel to said second side surface such that a non-square shape is formed by the intersection of the back surface, the first side surface, the front surface, and the second side surface and a first chamfer defined between said top surface and said front surface.
3 more elements
Dependencies are inferred from the claim text.