Annular combustion chambers for a gas turbine and gas turbine
The invention relates to an annular combustion chamber for a gas turbine wherein the annular combustion chamber extends in an axial direction, encloses a combustor and has on its inside facing the combustor a bearing structure on which a lining element secured to this lines the annular combustion chamber. The object is to disclose an annular combustion chamber with a lining element that meets the mechanical requirements while at the same time taking account of the system's maintenance-friendliness. The object is achieved in that the annular combustion chamber has a lining element wherein on the rear side facing away from the combustor of two edge areas on the lining element a plurality of interlocking means are located which have a hook width and wherein the lining element is secured to the corresponding bearing structure such that in order to release the lining element from the bearing structure the lining element is moved by the extent of the hook width of the interlocking means in the axial direction.
1. An annular combustion chamber for a gas turbine extending in the axial direction, comprising:
a combustor enclosed by the combustion chamber;
a bearing structure arranged on the inside of the combustion chamber and facing the combustor;
a lining element having a rear side facing away from the combustor and having two edge areas extending in the axial direction, each said edge area being secured to the bearing structure that lines the annular combustion chamber by and
a plurality of interlocking devices separated by a plurality of axial spacing having a width arranged on the lining element such that in order to release the lining element from the bearing structure the lining element is moved by the extent of the width of the interlocking devices in the axial direction, wherein
two interlocking devices of the lining element that are immediately adjacent in the axial direction have an axial spacing which is identical to or greater than the width of the interlocking devices.
2. The annular combustion chamber according to claim 1 , wherein a further plurality of interlocking devices are located as a central support midway between two edge areas of the lining element running in the axial direction.
3. The annular combustion chamber according to claim 1 , wherein each interlocking device has the identical hook width.
4. The annular combustion chamber according to claim 1 , wherein two interlocking devices of the lining element that are immediately adjacent in the axial direction have an axial spacing which is twice the width of an interlocking device.
5. The annular combustion chamber according to claim 1 , wherein two interlocking devices of the lining element that are immediately adjacent in the axial direction have an axial spacing which is three times the width of an interlocking device.
6. The annular combustion chamber according to claim 4 , wherein each spacing between two interlocking devices of the lining element that are immediately adjacent in the axial direction is identical.
7. The annular combustion chamber according to claim 1 , wherein the lining element has stiffening ribs running in the circumferential direction of the annular combustion chamber on its rear side facing away from the combustor.
8. The annular combustion chamber according to claim 7 , wherein the stiffening rib is distanced from the interlocking devices.
9. The annular combustion chamber according to claim 1 , wherein the interlocking devices are L- and/or T-shaped.
10. A gas turbine with an annular combustion chamber wherein the combustion chamber comprises:
a combustor enclosed by the combustion chamber;
bearing structure arranged on the inside of the combustion chamber and facing the combustor;
a lining element having a rear side facing away from the combustor and having two edge areas extending in the axial direction, each said edge area being secured to the bearing structure that lines the annular combustion chamber by and
a plurality of interlocking devices separated by a plurality of axial spacings having a width arranged on the lining element such that in order to release the lining element from the bearing structure the lining element is moved by the extent of the width of the interlocking devices in the axial direction, wherein
two interlocking, devices of the lining, element that are immediately adjacent in the axial direction have an axial spacing which is identical to or greater than the width of the interlocking devices.
11. A combustion chamber for a gas turbine, comprising:
a combustor enclosed by the combustion chamber;
a bearing structure arranged on the inside of the combustion chamber and facing the combustor;
a lining element having a rear side facing away from the combustor and having two edge areas extending in the axial direction, each said edge area being secured to the bearing structure that lines the annular combustion chamber by and
a plurality of interlocking devices separated by a plurality of axial spacing having a width arranged on the lining element such that in order to release the lining element from the bearing structure the lining element is moved by the extent of the width of the interlocking devices in the axial direction, wherein
two interlocking devices of the lining element that are immediately adjacent in the axial direction have an axial spacing which is identical to or greater than the width of the interlocking devices.
12. The annular combustion chamber according to claim 11 , wherein the interlocking devices face away from the combustor.
13. The annular combustion chamber according to claim 11 , wherein the interlocking device is a hook.
14. The annular combustion chamber according to claim 11 , wherein the width is the hook width.
15. The annular combustion chamber according to claim 1 , wherein the interlocking device is a hook.
16. The annular combustion chamber according to claim 1 , wherein the width is the hook width.
17. The annular combustion chamber according to claim 2 , wherein two interlocking devices of the lining element that are immediately adjacent in the axial direction have an axial spacing which is identical to or greater than the hook width of the interlocking devices.
18. The annular combustion chamber according to claim 2 , wherein each interlocking device has the identical hook width.
19. The annular combustion chamber according to claim 2 , wherein two interlocking devices of the lining element that are immediately adjacent in the axial direction have an axial spacing which is twice the hook width of an interlocking device.