Method for calculating the thickness of the trailing and leading edges on a blade profile

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United States of America Patent

PATENT NO 12005666
APP PUB NO 20220281198A1
SERIAL NO

17634716

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Abstract

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A verification method for verifying whether the aerodynamic profile of a real blade for an aircraft turbine engine complies with a theoretical blade, the method including constructing a camber line of the theoretical blade and constructing a camber line of the real blade; constructing a relationship for the thickness of the theoretical blade and constructing a relationship for the thickness of the real blade, the thickness relationship of a blade corresponding to the curve plotting the thickness of the blade as a function of curvilinear length along the camber line from a leading edge of the blade to a trailing edge of the blade, where thickness is the dimension of the blade extending perpendicularly to the camber line at each point of the camber line; superposing the thickness relationship of the real blade on the thickness relationship of the theoretical blade; and extracting the leading-edge and trailing edge thicknesses.

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Patent Owner(s)

Patent OwnerAddress
SAFRAN AIRCRAFT ENGINES75015 PARIS
SAFRAN AERO COMPOSITE75015 PARIS
SAFRAN AEROSPACE COMPOSITESB85 INNOVATION DRIVE ROCHESTER NH 03867

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Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Giacovelli, Clement Moissy-Cramayel, FR 1 1
Le, Cloarec Damien Vincent Moissy-Cramayel, FR 4 1
Sherman, Jeffrey Steven Moissy-Cramayel, FR 2 1
Thomas, Mickaelle Lucie Alicia Moissy-Cramayel, FR 1 1

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