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AssigneeSnecma
InventorsThierry Francois Maurice Duchatelle, Arnaud Sanchez
Estimating the term…
The invention relates to an intermediate casing (21) for an aircraft jet engine, comprising an outer shell (23) and also front and rear flanges (25, 27) which are arranged radially inside with respect to the outer shell, the casing (21) also comprising structural arms (17) which extend radially between the flanges as far as the shell (23), the rear flange being equipped with receiving means (34) for receiving a fixing bracket for fixing a rod for absorbing the thrust forces, and the first receiving means comprising bosses (36) coming from the rear flange, through which bosses through-orifices (38) are formed which are passed through by fixing screws of the bracket. According to the invention, at least one of the bosses (36) extends as far as making contact with one of the structural arms (17).
Intermediate casing (21) for an aircraft jet engine, comprising an outer shell (23) and also a front transverse flange (25) and a rear transverse flange (27) which are arranged parallel to one another and radially inside with respect to said outer shell, said intermediate casing also comprising structural arms (17) which are distributed angularly and extend radially between said front and rear flanges (25, 27) as far as said outer shell (23), said rear flange being equipped with first receiving means (34) for receiving a first fixing bracket (30) for fixing a first rod (8) for absorbing the thrust forces of the jet engine, said first receiving means comprising bosses (36) coming from said rear flange (27), through each of which bosses at least one through-orifice (38) is formed which is designed to be passed through by a fixing screw of said first fixing bracket, said through-orifices (38) being spaced apart angularly with respect to the structural arms (17),
Intermediate casing according to any one of the preceding claims, characterised in that each boss (36) extends over a substantially constant thickness.
Intermediate casing according to any one of the preceding claims, characterised in that each boss (36) extends from a front face (40) of said rear flange (27).
Intermediate casing according to any one of the preceding claims, characterised in that said first receiving means (34) also comprise an orifice (50) which is designed to house a shear pin (62) of said first fixing bracket.
Intermediate casing according to any one of the preceding claims, characterised in that said rear flange (27) is also equipped with second receiving means (34) for receiving a second fixing bracket for fixing a second rod for absorbing the thrust forces of the jet engine, said second receiving means comprising bosses (36) coming from said rear flange (27), through each of which bosses at least one through-orifice (38) is formed which is designed to be passed through by a fixing screw of said second fixing bracket, said through-orifices (38) being spaced apart angularly with respect to the structural arms (17), and in that at least one of said bosses (36) extends as far as making contact with one of said structural arms (17).
Intermediate casing according to any one of the preceding claims, characterised in that it is made in a single piece.
Jet engine (2) for an aircraft, comprising an intermediate casing (21) according to any one of the preceding claims, said outer shell (23) being arranged in the rear extension of the fan casing (12).
Dependencies are inferred from the claim text.