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:
May. 21, 2024

Filed:

Oct. 05, 2021
Applicant:

Rolls-royce Plc, London, GB;

Inventors:

Natalie C Wong, Bristol, GB;

Thomas S Binnington, Bristol, GB;

David A Jones, Bristol, GB;

Daniel Blacker, Bristol, GB;

Assignee:

ROLLS-ROYCE plc, London, GB;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02C 7/04 (2006.01); F02C 7/18 (2006.01); B64D 27/10 (2006.01); B64D 33/02 (2006.01); B64D 33/04 (2006.01); B64D 33/08 (2006.01); B64D 27/20 (2006.01); B64D 33/10 (2006.01); F02K 3/06 (2006.01); F02K 3/075 (2006.01); F02C 7/08 (2006.01); F02C 7/12 (2006.01); F01D 9/06 (2006.01); F02C 7/14 (2006.01); F02K 3/115 (2006.01);
U.S. Cl.
CPC ...
F02C 7/04 (2013.01); B64D 27/10 (2013.01); B64D 27/20 (2013.01); B64D 33/02 (2013.01); B64D 33/04 (2013.01); B64D 33/08 (2013.01); B64D 33/10 (2013.01); F01D 9/065 (2013.01); F02C 7/08 (2013.01); F02C 7/12 (2013.01); F02C 7/18 (2013.01); F02K 3/06 (2013.01); F02K 3/075 (2013.01); B64D 2033/024 (2013.01); B64D 2033/0286 (2013.01); F02C 7/14 (2013.01); F02K 3/115 (2013.01); F05D 2220/323 (2013.01); F05D 2220/36 (2013.01); F05D 2260/213 (2013.01);
Abstract

An aircraft comprises a machine body. The machine body encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, a combustor module, and an exhaust module. The machine body comprises either one or two fluid inlet apertures. The or each fluid inlet aperture is configured to allow a fluid flow to enter the machine body and to pass through the heat exchanger module. The heat exchanger module is configured to transfer a waste heat load from the gas turbine engine and the ancillary systems to the fluid flow prior to an entry of the fluid flow into the fan module, and thence into the compressor module, the turbine module, the combustor module, and the exhaust module.


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