Annular torsional rigid static component for an aircraft engine
In an annular torsional rigid static component for an aircraft engine, the component includes at least one arrangement for mounting the engine to an aircraft. The mounting arrangement comprises a body formed in a composite material.
1. An annular torsional rigid static component for an aircraft engine, the component comprising a rigid annular support member and at least one means for mounting the engine to an aircraft, wherein the mounting means comprises a connection element for connection to the aircraft, wherein the mounting means comprises a composite body formed in a composite material and the composite body is rigidly secured to the annular support member, wherein the rigid support member comprises an outer ring and an inner ring, the mounting means is arranged between the inner and outer ring and the composite body is rigidly connected to both rings thereby forming a torsional rigid unit.
2. A component according to claim 1 , wherein the composite body forms a wall structure.
3. A component according to claim 2 , wherein the wall structure comprises a front wall facing in an axial direction of the annular component and the front wall has a curved shape.
4. A component according to claim 3 , wherein the rigid member comprises a curved portion with a complementary shape to a curvature of the front wall, and that the curved portion is fitted against the front wall for distributing thrust forces to the composite body.
5. A component according to claim 1 , wherein the mounting means comprises a rigid member fitted around the composite body and that the rigid member comprises the connection element for connection to the aircraft.
6. A component according to claim 5 , wherein the rigid member comprises two mutually movable parts, which are clamped around the composite body.
7. A component according to claim 5 , wherein the rigid member is of metal material.
8. A component according to claim 1 , wherein the composite body is formed in a polymer composite material.
9. A component according to claim 1 , wherein the composite body material comprises a thermo set matrix material.
10. A component according to claim 1 , wherein the composite body material comprises an epoxy matrix.
11. A component according claim 1 , wherein the composite body material at least partially comprises a plurality of high strength fibers.
12. A component according to claim 11 , wherein the plurality of high strength fibers forms an extended structure in a circumferential direction of the annular component and the fiber structure extends over a longer distance in the circumferential direction of the annular component than the composite body material does.
13. A component according to claim 11 , wherein the plurality of high strength fibers forms a continuous annular structure in a circumferential direction of the annular component.
14. A component according to claim 11 , wherein the plurality of high strength fibers is at least partly embedded in a matrix material.
15. A component according to claim 11 , wherein the fibers are formed by a carbon material.
16. A component according to claim 1 , wherein the rigid support member is made of metal material.
17. A component according to claim 1 , wherein the component comprises at least two circumferentially spaced mounting means.
18. A component according to claim 1 , wherein the component comprises three circumferentially spaced mounting means, a first of the mounting means is arranged at an uppermost position for connection to the aircraft and a second and third of the mounting means are arranged on opposite sides of the first mounting means in the circumferential direction of the annular component.