Integrated propulsive system comprising a bypass turbojet engine
View Patent ↗An integrated propulsive turbofan engine system includes a downstream cylindrical nacelle structure in two parts. The first of the two parts is fixed and fastens engine attachment elements and an intermediate casing to the aircraft. The second of the two parts may move between a closed position used during operation and an open position during maintenance when access to engine components is needed.
1. An integrated propulsive system for an aircraft, comprising:
a turbofan engine, including an intermediate casing; and
a nacelle which bears the intermediate casing of the turbofan engine which defines an annular flow space for a secondary stream around the turbofan engine, the nacelle comprises a downstream cylindrical structure which includes
a fixed framework which is fastened via engine attachment elements to a part of the aircraft and which is fastened to the intermediate casing of the turbofan engine, and
a moveable part which is borne by the fixed framework and which moves between a closed position during operation of the turbofan engine and an open position in which the movable part is moved to allow access to engine components,
wherein the system includes a locking device which secures the moveable part to the fixed framework in the closed position,
wherein the fixed framework includes a downstream annular part in the shape of an annulus and the secondary stream travels through the downstream annular part, and
wherein the fixed framework includes an upstream annular flange which is fastened to an external annular flange of the intermediate casing of the turbofan engine.
2. The propulsive system as claimed in according to claim 1 , wherein the moveable part moves at least one of rotationally or translationally with respect to the fixed framework.
3. The propulsive system as claimed in claim 2 , wherein components of the locking device are mounted on the upstream annular flange and on a longitudinal strut of the fixed framework.
4. The propulsive system as claimed in claim 3 , wherein the moveable part comprises two semicylindrical lattices that are articulated around longitudinal axes on the fixed framework.
5. The propulsive system as claimed in claim 4 , wherein fairing or cowling panels are mounted on the system and the fairing or the cowling panels slide longitudinally on the two semicylindrical lattices to allow an operation of a thrust reverser.
6. The propulsive system as claimed in claim 5 , wherein the lattices open at an angle within a range from 40 degrees to 180 degrees with respect to the fixed framework.
7. The propulsive system as claimed in claim 6 , further comprising:
a substantially cylindrical case which provides an internal guide surface for the secondary stream, an upstream end of the substantially cylindrical case is fastened to the intermediate casing, a downstream end of the substantially cylindrical case which supports an exhaust casing, the exhaust casing guides a combustion flow that has exited from a turbine of the turbofan engine, and the substantially cylindrical case includes removable panels which allow access to the engine components.
8. The propulsive system as claimed in claim 4 , wherein the lattices open at an angle within a range from 40 degrees to 180 degrees with respect to the fixed framework.
9. The propulsive system as claimed in claim 1 , wherein components of the locking device are mounted on the annular flange and on a longitudinal strut of the fixed framework.
10. The propulsive system as claimed in claim 1 , wherein the moveable part comprises two semicylindrical lattices that are articulated around longitudinal axes on the fixed framework.
11. The propulsive system as claimed in claim 1 , further comprising:
a substantially cylindrical case which provides an internal guide surface for the secondary stream, an upstream end of the substantially cylindrical case is fastened to the intermediate casing, a downstream end of the substantially cylindrical case which supports an exhaust casing, the exhaust casing guides a combustion flow that has exited from a turbine of the turbofan engine, and the substantially cylindrical case includes removable panels which allow access to the engine components.
12. The propulsive system as claimed in claim 1 , wherein the moveable part pivots from the fixed framework.
13. The propulsive system as claimed in claim 1 , wherein the upstream annular flange is fastened to the external annular flange of the intermediate casing of the turbofan engine around an entire circumference of the external annular flange of the intermediate casing of the turbofan engine.
14. A downstream cylindrical structure of a nacelle for an integrated propulsive system attached to an aircraft, the integrated propulsive system including a turbofan engine which includes an intermediate casing, the downstream cylindrical structure comprising:
a fixed framework which is fastened via engine attachment elements to a part of the aircraft and which is fastened to the intermediate casing of the turbofan engine; and
a moveable part which includes two semicylindrical lattices articulated about longitudinal axes on the fixed framework, the moveable part is supported by the fixed framework and which moves between a closed position in which the movable part is fully attached to the fixed framework during an operation of a turbofan engine and an open position in which the movable part is moved to allow access to engine components, and the moveable part includes a locking device which secures the moveable part to the fixed framework in the closed position,
wherein the nacelle bears the intermediate casing of the turbofan engine, and the nacelle defines an annular flow space for a secondary stream around the turbofan engine,
wherein the fixed framework includes a downstream annular part in the shape of an annulus, and the downstream annular part permits the secondary stream to travel through the downstream annular part, and
wherein the fixed framework includes an upstream annular flange which is fastened to an external annular flange of the intermediate casing of the turbofan engine.
15. The downstream cylindrical structure as claimed in claim 14 , wherein the two semicylindrical lattices are perforated.
16. The downstream cylindrical structure as claimed in claim 15 , further comprising cowling panels which are mounted on the two semicylindrical lattices and which slide longitudinally on the two semicylindrical lattices.
17. The downstream cylindrical structure as claimed in claim 14 , further comprising cowling panels which are mounted on the two semicylindrical lattices and which slide longitudinally on the two semicylindrical lattices.