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:
Nov. 03, 2020

Filed:

Mar. 12, 2018
Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Charles William Dowdell, Ipswich, MA (US);

Jacques Paul, Somerville, MA (US);

Paul J. Morrison, Piedmont, CA (US);

Assignee:

General Electric Company, Schenectady, NY (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02D 21/00 (2006.01); F01D 21/00 (2006.01); B64D 45/00 (2006.01); F02C 9/18 (2006.01);
U.S. Cl.
CPC ...
F01D 21/003 (2013.01); B64D 45/00 (2013.01); F02C 9/18 (2013.01); B64D 2045/0085 (2013.01); F05D 2220/323 (2013.01); F05D 2260/80 (2013.01); F05D 2260/81 (2013.01); F05D 2260/83 (2013.01); F05D 2270/3011 (2013.01); F05D 2270/311 (2013.01); F05D 2270/312 (2013.01); F05D 2270/313 (2013.01);
Abstract

A method for determining an engine heath of an aircraft engine includes determining, by one or more control devices, the aircraft engine is operating in a bleed off condition; determining, by the one or more control devices, a first engine health modifier value while the aircraft engine is operating in the bleed off condition, the first of engine health modifier value including a compressor leakage flow value; determining, by the one or more control devices, a second plurality of engine health modifier values while the aircraft engine is operating in a bleed on condition; and determining, by the one or more control devices, an engine health parameter using at least one of the second plurality of engine health modifier values determined while the aircraft engine is operating in the bleed on condition and the compressor leakage flow value determined while the aircraft engine was operating in the bleed off condition.


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