Patent ID: 7938359

Claim:
An integrated propulsion system, comprising: a turbofan engine, the turbofan engine including an intermediate case; and a nacelle which bears the intermediate case of the turbofan engine which delimits an annular space for a flow of bypass air around the turbofan engine, wherein the nacelle includes a downstream cylindrical part which is rigid, the downstream cylindrical part includes an upstream annular flange disposed at an upstream end of the downstream cylindrical part which contacts at least 180 degrees about an axis of the turbofan engine of an external circumference of the intermediate case of the turbofan engine, an annulus disposed at a downstream end of the downstream cylindrical part which supports and guides an exhaust case of the turbofan engine with connecting rods arranged in the form of an equilateral triangle and securing members which secure the turbofan engine to the airplane, wherein the flow of bypass air passes between the upstream annular flange and the axis of the turbofan engine, wherein the upstream annular flange extends 360 degrees about the axis of the turbofan engine, and wherein the upstream annular flange is attached to the external circumference of the intermediate case of the turbofan engine.