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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 9714577 B1

PDFFull Text
Date of Patent:
Jul. 25, 2017

Filed:

Oct. 24, 2013

Gas turbine engine rotors including intra-hub stress relief features and methods for the manufacture thereof

Applicant:

Honeywell International Inc., Morristown, NJ (US);

Inventors:

Harry Lester Kington, Scottsdale, AZ (US);

Brian Hann, Avondale, AZ (US);

Assignee:

HONEYWELL INTERNATIONAL INC., Morris Plains, NJ (US);

Attorney:

Lorenz & Kopf, LLP

Primary Examiner:

Sean J Younger

Int. Cl.
CPC ...
F01D 5/02 (2006.01); F01D 5/04 (2006.01); F01D 5/34 (2006.01); B22F 3/15 (2006.01); F01D 5/14 (2006.01); B22C 9/04 (2006.01); B22D 25/02 (2006.01); B22F 5/00 (2006.01); B23P 15/00 (2006.01); B22F 5/10 (2006.01);
U.S. Cl.
CPC ...
F01D 5/147 (2013.01); B22C 9/04 (2013.01); B22D 25/02 (2013.01); B22F 3/15 (2013.01); B22F 5/009 (2013.01); B23P 15/006 (2013.01); F01D 5/04 (2013.01); F01D 5/048 (2013.01); F01D 5/34 (2013.01); B22F 2005/103 (2013.01); F05D 2230/21 (2013.01); F05D 2230/50 (2013.01); F05D 2260/941 (2013.01); Y10T 29/49321 (2015.01);
Abstract

Embodiments of a gas turbine engine rotor including stress relief features are provided, as are embodiments of method for producing a gas turbine engine rotor. In one embodiment, the method includes producing a hub preform in which a plurality of elongated sacrificial cores are embedded. Blades are attached to an outer circumference of the hub preform by, for example, bonding a blade ring to the outer circumference of the preform. The blades are spaced about the rotational axis of the gas turbine engine rotor and circumferentially interspersed with the plurality of elongated sacrificial cores. The plurality of elongated sacrificial cores are then removed from the hub preform to yield a plurality of stress distribution tunnels extending in the hub preform.

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