Engine assembly for an aircraft comprising an engine as well as an engine mounting structure for such an engine
An aircraft engine assembly including an engine, an engine suspension pylon, and a heat exchanger system including a second outlet located between the box and the engine, aft from the aft engine suspension. Furthermore, the exchanger in the heat exchanger system is at least partially arranged inside an aft aerodynamic fairing of the suspension pylon, the aft aerodynamic fairing being located entirely aft from the aft engine suspension.
1. An aircraft engine assembly, comprising:
an engine;
an engine suspension pylon, the pylon including a rigid structure that includes a box and a structural block installed fixed on the box between the box and the and the engine, and the pylon including a mounting system inserted between the engine and the rigid structure, the mounting system including an aft engine suspension, the structural block including an attachment interface for the aft engine suspension;
a heat exchanger system including an exchanger to which a hot fluid inlet, a cold air inlet, a first outlet communicating with the hot fluid inlet, and at least one second outlet communicating with the cold air inlet are connected, the hot fluid inlet being provided on a hot air duct connected to the exchanger and passing through the structural block in a longitudinal direction of the rigid structure, and each second outlet from the heat exchanger system being located between the box and the engine;
wherein each second outlet is located aft from the aft engine suspension, and
wherein the exchanger in the heat exchanger system is at least partially arranged inside an aft aerodynamic fairing of the suspension pylon, the aft aerodynamic fairing being located entirely aft from the aft engine suspension.
2. An engine assembly according to claim 1 , wherein the second outlet opens up inside the aft aerodynamic fairing of the suspension pylon.
3. An engine assembly according to claim 2 , wherein the aft aerodynamic fairing includes a controllable mobile structure including two lateral panels articulated at their forward ends on two corresponding lateral skins of the fairing, each of the panels configured to close/release an opening formed in its related lateral skin of the fairing.
4. An engine assembly according to claim 1 , wherein the aft aerodynamic fairing includes an air outlet opening including a controllable mobile structure, that, depending on its position, can modify an aerodynamic shape of the fairing.
5. An engine assembly according to claim 4 , wherein the mobile structure is placed across the air outlet opening.
6. An engine assembly according to claim 1 , wherein the first outlet from the heat exchanger system is provided on a first outlet pipe connected to the exchanger and passing through the box of the rigid structure.
7. An engine assembly according to claim 6 , wherein the first outlet is configured to be connected to a wing element of the aircraft.
8. An engine assembly according to claim 1 , wherein the heat exchanger system is a fluid/air type, the fluid passing through the hot fluid inlet and the first outlet and being among the group composed of air, oil and fuel.
9. An engine assembly according to claim 1 , wherein each second outlet is located between the box and the engine, adjacent to an engine exhaust nozzle or on the downstream side of the engine exhaust nozzle.
10. An aircraft comprising at least one engine assembly according to claim 1 .
11. An engine assembly according to claim 1 , wherein the box is made of a composite material.
12. An engine assembly according to claim 1 , wherein the mounting system further includes a thrust resistance device connected to an aft part of a fan casing of the engine and connected to the structural block.