Dual flow turbine engine for an aircraft including structural means for stiffening the central casing

• Main Authors: AU QUANG AUDREY, REAUX CLARISSE SAVINE MATHILDE, DERENES JACKY RAPHAEL MICHEL, SEIZE GUILHEM
• Format: Patent
• Language: Chinese; English
• Published: 12.09.2012
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; ENGINE PLANTS IN GENERAL; GAS-TURBINE PLANTS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS; INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04; JET-PROPULSION PLANTS; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; NON-POSITIVE DISPLACEMENT PUMPS; POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS; STEAM ENGINES; WEAPONS

The invention relates to a turbine engine for an aircraft, including shell means (36) arranged as a rear extension of an inner shroud (22) of an intermediate casing and provided around a central casing (18). The means (36) include a structural upstream shroud (54) mounted on the inner shroud (22) and defining the front portion (37a) of an internal limiting surface (37) of the secondary stream, and a main shell (56) forming a backward extension of the upstream shroud (54). The turbine engine includes structural means (72) for stiffening the central casing, surrounded by the shell (56) and extending backward between the upstream shroud (54) and the central casing (18) on which said means (72) are mounted.