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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 11268446 B1

PDFFull Text
Date of Patent:
Mar. 08, 2022

Filed:

Nov. 14, 2019

Method of starting a gas turbine engine including a bowed-rotor cooling phase

Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Joseph Daniel Garrett, III, Cincinnati, OH (US);

Mark Edward Linz, Everdale, OH (US);

Tod Robert Steen, West Chester, OH (US);

Thomas Charles Swager, Mainville, OH (US);

Andrew Todd Lehmann, Hamilton, OH (US);

Michael Scott McCambridge, Cincinnati, OH (US);

Robert Charles Hon, Fort Mitchell, KY (US);

Thomas Earl Gillingham, Cincinnati, OH (US);

Daniel Roy Kiracofe, Cincinnati, OH (US);

Kenneth Kirchmayer, Cincinnati, OH (US);

Joseph Roger Broda, West Chester, OH (US);

Kevin Richard Graziano, Cincinnati, OH (US);

Steven Alan Ross, West Chester, OH (US);

Amid Ansari, Mason, OH (US);

Assignee:

GENERAL ELECTRIC COMPANY, Schenectady, NY (US);

Attorneys:

Venable LLP

Edward A. Kmett

Michele V. Frank

Primary Examiner:

Alain Chau

Int. Cl.
CPC ...
F02C 7/26 (2006.01); F02C 7/12 (2006.01); F01D 19/02 (2006.01); F02C 7/268 (2006.01); F02C 3/04 (2006.01); F02C 9/00 (2006.01);
U.S. Cl.
CPC ...
F02C 7/26 (2013.01); F01D 19/02 (2013.01); F02C 3/04 (2013.01); F02C 7/12 (2013.01); F02C 7/268 (2013.01); F02C 9/00 (2013.01); F05D 2260/85 (2013.01); F05D 2270/042 (2013.01); F05D 2270/304 (2013.01); Y02T 50/60 (2013.01);
Abstract

A gas turbine engine and method of starting, the gas turbine engine having a rotor comprising at least a shaft mounted compressor and turbine, with a casing surrounding the rotor. The method comprises an acceleration phase, a bowed-rotor cooling phase, during the acceleration, and a combustion phase. The bowed-rotor cooling phase comprises a time where the rotational speed of the rotor is maintained below a bowed-rotor threshold speed until a non-bowed condition is satisfied, wherein the air forced through the gas turbine engine cools the rotor. The combustion phase occurs after the bowed-rotor cooling phase and upon reaching the combustion speed, wherein fuel is supplied to the gas turbine engine is turned on.

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