Turbine engine comprising a contrarotating propeller receiver supported by a structural casing attached to the intermediate housing

摘要

An open rotor type aircraft turbine engine including a contrarotating propeller receiver and a dual-body gas generator having a low-pressure compressor and a high-pressure compressor separated by an intermediate housing, in which the gas generator is arranged upstream from the receiver is provided. The turbine engine includes a structural casing for supporting the receiver, surrounding the gas generator and having a downstream end attached to the receiver and an upstream end attached to the intermediate housing; and a connection device between the structural supporting casing and the gas generator, arranged between the upstream and downstream ends of the casing.

主权项

1. An aircraft turbine engine comprising:
contrarotating propeller receiver and a dual-body gas generator comprising a low-pressure compressor and a high-pressure compressor separated by an intermediate housing, said dual-body gas generator being arranged upstream from said contrarotating propeller receiver; a structural casing for supporting the contrarotating propeller receiver, said structural casing surrounding the dual-body gas generator and having a downstream end attached to an upstream flange of a stator outer housing of said contrarotating propeller receiver and an upstream end attached to said intermediate housing, said structural casing extending between said intermediate housing and said contrarotating propeller receiver; an annular space is defined externally by an inner surface of said structural casing and defined internally by an outer casing of said dual-body gas generator; and connection means connecting said structural casing to a downstream end of said outer casing of the dual-body gas generator, said connecting means being arranged between the upstream and downstream ends of the structural casing, wherein said connection means are designed to enable relative movement between said structural casing and the dual-body gas generator, wherein the contrarotating propeller receiver includes a free power turbine at an upstream end thereof, and wherein said connection means comprise a plurality of connecting rods distributed circumferentially with respect to each other, about a longitudinal axis of the aircraft turbine engine.