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 10315279 B1

PDF
Full Text
Expired
Date of Patent:
Jun. 11, 2019

Filed:

Aug. 08, 2014
Applicant:

Siemens Aktiengesellschaft, München, DE;

Inventor:

Allister William James, Chuluota, FL (US);

Assignee:
Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B21D 39/00 (2006.01); B21D 39/03 (2006.01); B23K 20/02 (2006.01); B23K 20/18 (2006.01); B23P 11/00 (2006.01); B23K 20/24 (2006.01); F01D 25/28 (2006.01); B21D 53/78 (2006.01); B23K 101/00 (2006.01);
U.S. Cl.
CPC ...
B23P 11/00 (2013.01); B21D 39/00 (2013.01); B21D 39/03 (2013.01); B23K 20/021 (2013.01); B23K 20/18 (2013.01); B23K 20/24 (2013.01); F01D 25/28 (2013.01); B21D 53/78 (2013.01); B23K 2101/001 (2018.08); F05D 2230/42 (2013.01);
Abstract

A method () of using hot isostatic pressing to join metallic members that form a component in a gas turbine engine is disclosed. The method () may include applying () a surface treatment to the outer surfaces () of first and second metallic members () based on whether a mechanical or metallurgical joint for the component is desired. Additionally, the method () may include aligning () the outer surfaces () of the first and second metallic members () to create a sealed cavity, which encompasses the joint, between the first and second metallic members (). Once the outer surfaces () are aligned, the method () may include subjecting () the members () to hot isostatic pressing such that material from the first metallic member () flows into a recess () within the second metallic member () so as to join the first and second metallic members () to form a consolidated component (). The consolidated component () may then be machined and finished () for use in a turbine engine.


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