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:
Jan. 30, 2024

Filed:

Jun. 25, 2019
Applicant:

Rolls-royce Plc, London, GB;

Inventors:

Robert J Corin, Bristol, GB;

John R Whurr, Derby, GB;

Assignee:

ROLLS-ROYCE plc, London, GB;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B64D 33/02 (2006.01); B64C 30/00 (2006.01); F02C 7/04 (2006.01); F02K 1/08 (2006.01); F02K 1/38 (2006.01); F02K 3/075 (2006.01);
U.S. Cl.
CPC ...
B64D 33/02 (2013.01); B64C 30/00 (2013.01); F02C 7/04 (2013.01); F02K 1/08 (2013.01); B64D 2033/026 (2013.01); B64D 2033/0286 (2013.01); F02K 1/386 (2013.01); F02K 3/075 (2013.01); F05D 2220/80 (2013.01); F05D 2250/51 (2013.01);
Abstract

Engine has core compressor, combustor and turbine, fan located upstream of core and supersonic intake for slowing down incoming air at inlet formed by intake, bypass duct surrounding engine core, fan generates airflow to engine core and bypass airflow through bypass duct. Engine has mixer for exhaust gas flow exiting engine core, bypass airflow exiting bypass duct, thrust nozzle for discharging mixed flows, and controller for thrust produced by engine. To change level of engine thrust between transonic push operation and supersonic cruise operation, controller adjusts one or more components which vary relative areas available for hot exhaust gas flow and cold bypass airflow at mixer while holding fan inlet non-dimensional mass flow w √{square root over ( )} T/P substantially constant, where w is mass flow of incoming air at fan inlet, T is stagnation temperature of incoming air at fan inlet and P is stagnation pressure of incoming air at fan inlet.


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