Turbo-engine including two separate ventilation flows
A non-faired propeller turbo-engine includes a gas generator and a propulsion unit that is separated from the gas generator by an intermediate housing. The turbo-engine includes a housing and a radially internal ferrule that are coaxial and are connected by hollow radial arms. The housing of the turbo-engine also defines, in part, a gas flow duct of a secondary gas flow. Each radial arm is hollow and is traversed by at least one service of the turbo-engine. Additionally, at least one arm is traversed by a ventilation gas circulation duct from the secondary gas flow and which leads to at least one component from among a power turbine and a mechanical transmission of said propulsion unit.
1. A turbo-engine with non-faired propellers comprising:
a gas generator;
a propulsion unit which is separated from the gas generator by an intermediate housing; and
a housing and a radially internal ferrule which are coaxial and define a gas flow duct of a primary gas flow, and which are connected by hollow radial arms, said housing also defining in part a gas flow duct of a secondary gas flow,
wherein each of the hollow radial arms is hollow and is traversed by at least one service duct of the turbo-engine, and
wherein at least one of the hollow radial arms is traversed by a ventilation gas circulation duct from the secondary gas flow and which leads to at least one component from among a power turbine and a mechanical transmission of said propulsion unit.
2. The turbo-engine according to claim 1 , wherein a radially internal end of the ventilation gas circulation duct leads to at least one distribution box.
3. The turbo-engine according to claim 2 , further comprising a plurality of injectors of ventilation gas towards said component of the propulsion unit which are connected to the distribution box.
4. The turbo-engine according to claim 3 , wherein the injectors are included directly in the distribution box.
5. The turbo-engine according to claim 2 , wherein said distribution box forms an annular element wherein each ventilation gas circulation duct leads.
6. The turbo-engine according to claim 2 , wherein the turbo-engine includes a plurality of distribution boxes distributed about the main axis (A) of the turbo-engine, and at least one ventilation gas circulation duct leads into each of the plurality of distribution boxes.
7. The turbo-engine according to claim 6 , wherein a radially external end of the ventilation gas circulation duct leads to a flow jet of the secondary gas flow and the radially internal end of the ventilation gas circulation duct leads to at least one distribution box of the ventilation gas flow.
8. The turbo-engine according to claim 7 , wherein at least one of the two radial ends of the ventilation gas circulation duct is oriented essentially radially with respect to the main axis A of the turbo-engine.
9. The turbo-engine according to claim 7 , further comprising means for securing each radial end of the ventilation gas circulation duct to the ferrule or to the associated housing enabling movement of said radial end of the ventilation gas circulation duct with respect to the ferrule or with respect to the associated housing along the main axis of said radial end of the ventilation gas circulation duct.
10. The turbo-engine according to claim 9 , wherein each of the housing and the internal ferrule includes a stop ring situated radially facing and at a distance from the radial end of the ventilation gas circulation duct which is associated with said ferrule or the housing, and against which ring, the radial end of the ventilation gas circulation duct is suitable for coming into abutment radially.
11. The turbo-engine according to claim 1 , wherein each of the hollow radial arms includes a structural arm connecting the ferrule and the housing with one another, which is traversed radially by the at least one service duct associated with the gas generator and a double skin at least partially covering the structural arm, which defines a volume situated downstream from the structural arm and through which at least the ventilation gas circulation duct is arranged.
12. The turbo-engine according to claim 11 , wherein said double skin has an aerodynamic cross-section.