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:
Sep. 26, 2017

Filed:

Jan. 20, 2015
Applicant:

United Technologies Corporation, Hartford, CT (US);

Inventors:

Gabriel L. Suciu, Glastonbury, CT (US);

Alan H. Epstein, Lexington, MA (US);

Wesley K. Lord, South Glastonbury, CT (US);

Jesse M. Chandler, South Windsor, CT (US);

Stephen G. Pixton, South Windsor, CT (US);

Assignee:

United Technologies Corporation, Farmington, CT (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B64D 27/12 (2006.01); F02C 3/10 (2006.01); F02K 1/54 (2006.01); F02C 6/20 (2006.01); F02C 7/36 (2006.01); B64D 35/04 (2006.01);
U.S. Cl.
CPC ...
F02C 3/10 (2013.01); B64D 27/12 (2013.01); B64D 35/04 (2013.01); F02C 6/206 (2013.01); F02C 7/36 (2013.01); F02K 1/54 (2013.01);
Abstract

An aircraft body comprises a support structure. A gas turbine engine comprises a gas generator having at least one compressor rotor, at least one gas generator turbine rotor, and a combustion section. A fan drive turbine is positioned downstream of at least one gas generator turbine rotor, and is configured to drive a shaft. The shaft engages gears to drive a plurality of fan rotors. The gas turbine engine is embedded into the support structure such that there is an inlet leading through the support structure to the fan rotors to deliver air to the fan rotors. A gas turbine engine is also disclosed.


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