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.

Date of Patent:
Jul. 20, 2021

Filed:

Mar. 20, 2020
Applicant:

United Technologies Corporation, Farmington, CT (US);

Inventors:

Changsheng Guo, South Windsor, CT (US);

Christopher W. Strock, Kennebunk, ME (US);

Assignee:

RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 5/20 (2006.01); F01D 11/12 (2006.01);
U.S. Cl.
CPC ...
F01D 5/20 (2013.01); F01D 11/122 (2013.01); F05D 2220/32 (2013.01); F05D 2230/10 (2013.01); F05D 2230/25 (2013.01); F05D 2230/90 (2013.01); F05D 2300/2112 (2013.01); F05D 2300/22 (2013.01); F05D 2300/2282 (2013.01); F05D 2300/2284 (2013.01); F05D 2300/30 (2013.01); F05D 2300/506 (2013.01); Y10T 29/49337 (2015.01);
Abstract

An integrally bladed rotor, including: a plurality of blades integrally formed with a hub as a single component, each of the plurality of blades having a blade body extending from the hub to an opposed blade tip surface along a longitudinal axis, wherein the blade body defines a pressure side and a suction side, and wherein the blade body includes a cutting edge defined between the blade tip surface of the blade body and the pressure side of the blade body, wherein the cutting edge is configured to abrade a seal section of an engine case. A method for manufacturing an integrally bladed rotor includes: forming a plurality of airfoils integrally with a hub to form a single component, each of the plurality of airfoils having an opposed tip surface with respect to the hub extending along a longitudinal axis, wherein each of the plurality of airfoils defines a pressure side and a suction side; and forming a cutting edge between the tip surface and the pressure side of each of the plurality of airfoils, wherein the cutting edge is configured to abrade a seal section of an engine case.


Find Patent Forward Citations

Loading…