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The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Patent No.:

US 12005666 B1

PDFFull Text
Date of Patent:
Jun. 11, 2024

Filed:

Aug. 07, 2020

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

Applicants:

Safran Aero Composite, Paris, FR;

Safran Aircraft Engines, Paris, FR;

Safran Aerospace Composites, Rochester, NH (US);

Inventors:

Damien Vincent Le Cloarec, Moissy-Cramayel, FR;

Clement Giacovelli, Moissy-Cramayel, FR;

Jeffrey Steven Sherman, Moissy-Cramayel, FR;

Mickaelle Lucie Alicia Thomas, Moissy-Cramayel, FR;

Assignees:

SAFRAN AERO COMPOSITE, Paris, FR;

SAFRAN AIRCRAFT ENGINES, Paris, FR;

SAFRAN AEROSPACE COMPOSITES, Rochester, NH (US);

Attorney:

Oblon, McClelland, Maier & Neustadt, L.L.P.

Primary Examiner:

Jermie E Cozart

Int. Cl.
CPC ...
B23P 15/02 (2006.01); B29D 99/00 (2010.01); G05D 5/02 (2006.01); F01D 5/14 (2006.01);
U.S. Cl.
CPC ...
B29D 99/0025 (2013.01); B23P 15/02 (2013.01); G05D 5/02 (2013.01); F01D 5/141 (2013.01); F05D 2230/18 (2013.01); Y10T 29/49336 (2015.01); Y10T 29/49771 (2015.01);
Abstract

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.

Find Patent Forward Citations

Le Cloarec, Damien. (2024). Method for calculating the thickness of the trailing and leading edges on a blade profile (U.S. Patent No. 12005666). U.S. Patent and Trademark Office. https://idiyas.com/patent/badge/12005666

Data source: USPTO (United States Patent and Trademark Office) public patent records. Weekly synchronization. How IDiyas builds this profile

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