Nacelle cowling structure for a turbomachine
Embodiments of the invention are shown in the figures, where a nacelle cowling structure for a turbomachine having a bypass duct defining a path for an airflow is provided, the nacelle cowling structure including: an outer layer defining an external surface of the nacelle cowling structure, an inner layer defining a surface of the bypass duct, a front mounting area for fixation to the turbomachine and a rear mounting area for fixation to the turbomachine downstream the front mounting area with respect to the bypass duct flow path, wherein a space between the outer and inner layers and between the front and rear mounting areas is filled with acoustic material.
1. A nacelle cowling structure for a turbomachine having a bypass duct defining a flow path for an airflow, the nacelle cowling structure comprising:
an outer layer defining an external surface of the nacelle cowling structure,
an inner layer defining a surface of the bypass duct,
an acoustic material and a load-carrying backskin,
a front mounting area for fixation to the turbomachine and a rear mounting area for fixation to the turbomachine downstream of the front mounting area with respect to the bypass duct flow path,
wherein a space between the outer and inner layers and between the front and rear mounting areas is filled with the acoustic material,
bulkheads and ribs connecting the outer layer and inner layer with one another between the front and rear mounting areas.
2. The nacelle cowling structure according to claim 1 , and further comprising an access opening extending through the outer layer, acoustic material, and inner layer.
3. The nacelle cowling structure according to claim 2 , and further comprising a door closing the access opening in a closed state and providing access to the bypass duct in an opened state.
4. The nacelle cowling structure according to claim 3 , the door comprising a portion of the an outer layer and a portion of the inner layer, and a portion of the acoustic material in between.
5. The nacelle cowling structure according to claim 3 , and further comprising a hinge and latch connecting the door to the nacelle cowling structure inner layer.
6. The nacelle cowling structure according to claim 1 , wherein the inner layer comprises the front and rear mounting areas.
7. The nacelle cowling structure according to claim 1 , wherein the outer layer comprises a carbon composite material, the inner layer comprises at least one chosen from a composite material and a metal, and the acoustic material comprises a honeycomb structure.
8. The nacelle cowling structure according to claim 1 , wherein the outer layer is mounted on the inner layer, and the inner layer carries the outer layer.
9. The nacelle cowling structure according to claim 1 , wherein each of the front and rear mounting areas comprises a flange.
10. The nacelle cowling structure according to claim 1 , wherein the acoustic material is a sound absorber.
11. The nacelle cowling structure according to claim 1 , having a cylindrical or curved shape.
12. The nacelle cowling structure according to claim 1 , surrounding an area for housing a core of the turbomachine, the core comprising combustion equipment.
13. A nacelle cowling structure for a turbomachine having a bypass duct defining a flow path for an airflow, the nacelle cowling structure comprising:
an outer layer defining an external surface of the nacelle cowling structure,
an inner layer defining a surface of the bypass duct,
an acoustic material and a load-carrying backskin,
wherein the acoustic material is arranged in a space between the outer and inner layers,
the nacelle cowling structure further comprising an access opening extending through the outer layer, acoustic material, and inner layer,
a front mounting area for fixation to the turbomachine and a rear mounting area for fixation to the turbomachine downstream of the front mounting area with respect to the bypass duct flow path,
bulkheads and ribs connecting the outer layer and inner layer with one another between the front and rear mounting areas.
14. The nacelle cowling structure of claim 1 , wherein the front mounting area is fixed to a case of the turbomachine and the rear mounting area is fixed to a turbomachine core of the turbomachine.
15. The nacelle cowling structure according to claim 14 , wherein a fan directs an airflow through the bypass duct and the turbomachine core, wherein the bypass duct surrounds the turbomachine core.
16. The nacelle cowling structure according to claim 14 , wherein the turbomachine is an aircraft engine and the turbomachine core comprises a gas turbine engine.
17. The nacelle cowling structure according to claim 14 , wherein the front mounting area is fixed to the case by a bolted connection and the rear mounting area is fixed to the turbomachine core by a bolted connection.
18. The nacelle cowling structure according to claim 14 , providing a mechanical connection to an exhaust system.
19. The nacelle cowling structure according to claim 18 , wherein the exhaust system comprises at least one chosen from a fixed nozzle, a thrust reverser, a variable exhaust nozzle and an afterburner.
20. A nacelle cowling structure for a turbomachine having a bypass duct defining a flow path for an airflow, the nacelle cowling structure comprising:
an outer part comprising or being formed by an outer layer defining an external surface of the nacelle cowling structure,
an inner part comprising an inner layer defining a surface of the bypass duct, an acoustic material and a load-carrying backskin,
a front mounting area for fixation to the turbomachine and a rear mounting area for fixation to the turbomachine downstream of the front mounting area with respect to the bypass duct flow path,
wherein a space is formed between the outer and inner layers, and
bulkheads and ribs connecting the outer and inner parts with one another between the front and rear mounting areas.