Gas turbine annular combustor arrangement

1. A combustor arrangement, the combustor arrangement being annular and being arranged about an axis, the axis defining an axial direction, comprising:

an annular combustion chamber;

an annular housing that houses a plurality of burners and the annular combustion chamber;

the plurality of burners arranged circumferentially about the axis inside the annular housing;

an annular space being defined between the annular housing, the plurality of burners and the annular combustion chamber, the annular space arranged to guide a compressed fluid;

a plurality of stiffening plates, each arranged within the annular housing, wherein two adjacent ones of the plurality of burners are separated by one of the stiffening plates;

a combustor separating wall arrangement separating the annular space from the annular combustion chamber and providing openings for the plurality of burners;

further plates extending into the annular space;

wherein the stiffening plates are arranged angled to, and connected to the combustor separating wall arrangement and two boundary walls of the annular housing, and the further plates,

wherein the combustor separating wall arrangement comprises:

the openings which each hold a tip region of a respective burner of the plurality of burners;

a heat shield with cooling holes, the cooling holes arranged for guiding the compressed fluid into the combustion chamber;

an impingement plate parallel to the heat shield and defining a cooling cavity between the heat shield and the impingement plate, the impingement plate comprising further holes for impingement cooling of the heat shield, wherein the further holes are arranged to be supplied with the compressed fluid from the annular space,

further comprising burner rings each being located inside one of the openings of the combustor separating wall arrangement, each of the burner rings having a through-hole into which the tip region of the respective burner is mounted,

wherein the stiffening plates and the impingement plate are connected fixedly to another; and

wherein the impingement plate is slidably locked to each of the burner rings and to the heat shield.

2. The combustor arrangement according to claim 1 ,

wherein the combustor separating wall arrangement comprises a support ring located in the annular space, the support ring comprising the openings of the combustor separating wall arrangement to slidably hold the plurality of burners,

wherein the stiffening plates are connected to the support ring.

3. The combustor arrangement according to claim 1 ,

wherein the stiffening plates are manufactured from sheet metal or integrally formed with the annular housing.

4. The combustor arrangement according to claim 1 ,

wherein each of the burner rings comprises elongated effusion cooling holes directed onto the tip region of the respective burner or onto a front face of the tip region of the respective burner, and/or into a groove between a rim of each of the burner rings and the tip region of the respective burner.

5. The combustor arrangement according to claim 1 ,

wherein the further plates comprise at least a barrier penetrating the annular space such that cooling air from a combustion chamber liner is guided to an axial mid region of the annular space, the barrier being a liner extension plate of the combustion chamber liner.

6. The combustor arrangement according to claim 5 ,

wherein the liner extension plate and the combustion chamber liner are angled to another via an obtuse angle between 155° and 180°.

7. The combustor arrangement according to claim 5 ,

wherein a further wall of the annular housing and the combustion chamber liner define a cooling fluid passage there-between with a cooling fluid passage cross-section, the cooling fluid passage leading into a diffuser, the diffuser being defined by one of the two boundary walls of the annular housing and the liner extension plate.

8. The combustor arrangement according to claim 7 ,

wherein an inlet into the cooling fluid passage is defined by a section of the further wall smoothly becoming parallel, in respect of a cooling fluid flow direction along the liner during operation, to the liner of the combustion chamber.

9. The combustor arrangement according to claim 7 ,

wherein the liner extension plate and the combustion chamber liner are connected via bolts.

10. The combustor arrangement according to claim 7 ,

wherein the liner extension plate and the combustion chamber liner and the combustor separating wall arrangement are connected via bolts.

11. The combustor arrangement according to claim 10 ,

wherein a contact region between a connection of the liner extension plate and the combustion chamber liner and the combustor separating wall arrangement is sealed by means of rope seals or brush seals in order to minimize leakage from the annular housing to the annular combustion chamber through the contact region.

12. The combustor arrangement according to claim 9 ,

wherein the bolts comprise bolt heads and threads, and

wherein the bolts are configured such that

the bolt heads extend into the diffuser and/or the threads extend into the annular space, or

the bolt heads extend into the diffuser and/or the threads extend into the cooling fluid passage.

13. The combustor arrangement according to claim 9 ,

wherein the bolts are fastened via nuts applied from the annular space.

14. The combustor arrangement according to claim 9 ,

wherein the barrier provides an axial stop for engaging the combustion chamber liner with the barrier.

15. The combustor arrangement according to claim 9 ,

wherein a contact region between a connection of the liner extension plate and the combustion chamber liner is sealed by means of rope seals or brush seals in order to minimize leakage from the annular housing to the annular combustion chamber through the contact region.

16. The combustor arrangement according to claim 13 , wherein an extension sleeve is provided for each of the bolts positioned between one of the nuts and the barrier for providing continuous strain on each of the bolts.

17. The combustor arrangement according to claim 1 ,

wherein the angular arrangement is perpendicular.