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. 07, 2023

Filed:

Nov. 16, 2016
Applicant:

Safran Aircraft Engines, Paris, FR;

Inventors:

Pascal Charles Edouard Coat, Moissy-Cramayel, FR;

Jean-François Endy Bersot, Moissy-Cramayel, FR;

Stephane Orcel, Moissy-Cramayel, FR;

Nicolas Jerome Jean Tantot, Moissy-Cramayel, FR;

Assignee:
Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B64D 31/00 (2006.01); B64D 27/00 (2006.01); B64D 27/10 (2006.01); B64D 27/16 (2006.01); B64D 27/24 (2006.01); B64D 27/02 (2006.01);
U.S. Cl.
CPC ...
B64D 31/00 (2013.01); B64D 27/00 (2013.01); B64D 27/10 (2013.01); B64D 27/16 (2013.01); B64D 27/24 (2013.01); B64D 2027/026 (2013.01);
Abstract

The invention relates to the rating (S) of a propulsion unit () comprising a main engine () providing main thrust assisted by an auxiliary engine () providing auxiliary thrust, according to the following steps: (i) determining (S) a distribution between the main thrust and the auxiliary thrust so as to obtain the takeoff thrust of the propulsion unit, the auxiliary thrust making a 5% to 65% contribution to the takeoff thrust, (ii) depending on the distribution determined for the takeoff condition, determining (S) distribution between the main thrust and the auxiliary thrust so its to obtain the top of climb thrust of the propulsion unit, the auxiliary thrust making at most 70% contribution to the top of climb thrust, and (iii) rating (S) the propulsion unit () in such a way that the main thrust of the main engine () determined fir the takeoff condition corresponds to the maximum thrust likely to be achieved by the main engine ().


Find Patent Forward Citations

Loading…