US 11,053,852 B2
Turbojet engine with thrust take-up means on the inter-compressors case
Nils Edouard Romain Bordoni, Moissy-Cramayel (FR); Michel Gilbert Roland Brault, Moissy-Cramayel (FR); Romain Guillaume Cuvillier, Moissy-Cramayel (FR); Guillaume Patrice Kubiak, Moissy-Cramayel (FR); Arnaud Nicolas Negri, Moissy-Cramayel (FR); and Nathalie Nowakowski, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 16/63,929
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Dec. 12, 2016, PCT No. PCT/FR2016/053332
§ 371(c)(1), (2) Date Jun. 19, 2018,
PCT Pub. No. WO2017/109328, PCT Pub. Date Jun. 29, 2017.
Claims priority of application No. 1563322 (FR), filed on Dec. 24, 2015.
Prior Publication US 2018/0372001 A1, Dec. 27, 2018
Int. Cl. F02C 7/20 (2006.01); F01D 25/16 (2006.01); F01D 25/24 (2006.01); F01D 25/28 (2006.01); F02K 3/06 (2006.01)
CPC F02C 7/20 (2013.01) [F01D 25/162 (2013.01); F01D 25/24 (2013.01); F01D 25/28 (2013.01); F02K 3/06 (2013.01); F05D 2240/90 (2013.01); F05D 2250/241 (2013.01); Y02T 50/60 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A multi-flow turbojet engine, comprising:
an upstream ducted fan driven by a gas generator, whereby the gas generator comprises a first compressor and a second compressor that is coaxial with the first compressor;
an inlet case configured to form a support for a fan rotor of the upstream ducted fan and a first compressor rotor of the first compressor;
an inter-compressor case located downstream from the inlet case, and configured to form a support for a second compressor rotor of the second compressor;
attachment means for a plurality of thrust take-up rods arranged on the inter-compressor case; and
at least one axial stress transmission rod that connects the inlet case to the inter-compressor case.