Fan blade root integrated sealing solution

Number of patents in Portfolio can not be more than 2000

United States of America Patent

PATENT NO 10047625
APP PUB NO 20150104315A1
SERIAL NO

14401004

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Importance

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Abstract

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A gas turbine engine, a fan section for a gas turbine engine, and a method for assembling a fan section of a gas turbine engine are disclosed. The fan section may include a fan hub having a slot, a spinner having a castellated spinner seal, a fan blade including an airfoil extending from a root to a tip, wherein the airfoil has a leading edge and the root is received in the slot, and a platform secured to the fan hub and arranged between adjacent fan blades. The fan section may further include a flap seal having a base secured to a side of the platform, and a flap integral with and extending from the base portion and canted toward the root and engaging the blade, the seal trimmed back from the leading edge of the airfoil.

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Patent Owner(s)

  • UNITED TECHNOLOGIES CORPORATION

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Tatton, Royce E Firth, US 8 31

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