Planetary gear drive and aircraft gas turbine with a planetary gear drive

1. A planetary gearbox having a ring gear support, for a geared fan engine, comprising:

a plurality of bolt connections connecting the ring gear support to a static component, wherein the bolt connections are arranged around a circumference of the ring gear support to extend in an axial direction of the planetary gearbox,

the bolt connections configured and arranged to engage at least one backing ring to clamp the ring gear support and the static component together in the axial direction to form a circumferential frictional joint with a defined frictional force between the ring gear support and the static component,

a circumferentially extending channel positioned adjacent to the ring gear support and/or the static component such that the bolt connections axially pass through the channel, the channel being open in a circumferential direction such that the bolt connections are movable circumferentially in the channel with respect to the ring gear support and/or the static component upon an overload situation where an applied torque exceeds a slipping torque of the frictional joint.

2. The planetary gearbox according to claim 1 , wherein the ring gear support and/or the static component has a flange, through which the bolt connections pass and which is part of the frictional joint.

3. The planetary gearbox according to claim 1 , and further comprising an annular covering device which at least partially surrounds the bolt connections axially on one side.

4. The planetary gearbox according to claim 3 , wherein the covering device is U-shaped, and includes at least one arm connected to the ring gear support and/or the static component by the frictional joint.

5. The planetary gearbox according to claim 3 , wherein the covering device includes openings at a base of the U-shape for mounting the bolt connections.

6. The planetary gearbox according to claim 3 , wherein the at least one backing ring includes through holes for the bolt connections, the at least one backing ring arranged within the covering device parallel to a radially extending flange of the ring gear support and/or the static component.

7. The planetary gearbox according to claim 1 , wherein, the channel is formed by a part of the static component.

8. The planetary gearbox according to claim 1 , wherein the static component connects the ring gear support to a fixed structure of the geared fan engine.

9. The planetary gearbox according to claim 1 , wherein the frictional joint between the static component and the ring gear support has a slipping torque 1.5 to 4 times a maximum operational torque of the gearbox.

10. The planetary gearbox according to claim 1 , wherein the bolt connections are preloaded.

11. The planetary gearbox according to claim 1 , wherein the plurality of bolt connections includes between 40 and 140 bolt connections.

12. The planetary gearbox according to claim 1 , wherein bolts of the bolt connections have a nominal diameter in a range of from 0.3 to 2 cm, in particular between 0.5 and 1.5 cm.

13. A gas turbine engine for an aircraft comprising:

a core engine comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor;

a fan, which is positioned upstream of the core engine, wherein the fan comprises a plurality of fan blades; and

a gearbox, driven by the core shaft, wherein the fan is driven by the gearbox at a lower speed than the core shaft, wherein the gearbox is the planetary gearbox according to claim 1 .

14. The planetary gearbox according to claim 1 , wherein the frictional joint between the static component and the ring gear support has a slipping torque of 3 to 4 times a maximum operational torque of the gearbox.

15. The planetary gearbox according to claim 1 , wherein the plurality of bolt connections includes between 70 and 110 bolt connections.

16. The planetary gearbox according to claim 1 , wherein bolts of the bolt connections have a nominal diameter in a range of from 0.5 to 1.5 cm.