Annular-combustion-chamber bypass

Abstract

An annular combustion chamber ( 1 ) for a gas turbine, the chamber having an outer shell ( 12 ) which has at least one inlet opening ( 4 ) for a burner ( 3 ) and an outlet ( 7 ) which opens into a turbine chamber ( 8 ), wherein ducts ( 14 ) which can be closed, which are oriented substantially parallel to the symmetry axis ( 2 ) of the annular combustion chamber ( 1 ), and through which final compressor air is guided into the annular combustion chamber ( 1 ) are provided in the outer shell ( 12 ) in the region of the outlet ( 7 ). Ring segments around the outer shell have projections selectively movable to at least partially block and open the ducts. A gas turbine is also disclosed.

1 . An annular combustion chamber for a gas turbine, the combustion chamber having an outer shell and the outer shell has at least one inlet opening for a burner and has an outlet that opens into a turbine space;
 ducts in the outer shell located in the region of the outlet, the ducts are closable, the ducts are oriented substantially parallel to an axis of symmetry of the annular combustion chamber, and compressor outlet air can selectively be guided through the ducts and into the annular combustion chamber;   an adjustment device, comprising a ring that is oriented coaxially with the annular combustion chamber and may be moved axially with respect to the annular combustion chamber, the ring is provided on the exterior of the outer shell and is configured and located for selectively closing and opening the ducts.   
     
     
         2 . The annular combustion chamber as claimed in  claim 1 , comprising a last row of heat-shield plates arranged in the circumferential direction on the outer shell in the region of the outlet from the interior of the annular combustion chamber, and
 a second-to-last row of heat-shield plates arranged next to the last row in the direction toward the at least one inlet opening   a gap between the last and second-to-last rows of heat-shield plates, in the region of the opening of the ducts into the interior of the annular combustion chamber.   
     
     
         3 . The annular combustion chamber as claimed in  claim 1 , wherein the ring is movable in a continuously variable manner for the selective closing and opening of the ducts. 
     
     
         4 . The annular combustion chamber as claimed in  claim 1 , wherein the ring has, on a side thereof facing away from the turbine, projections for engaging in respective the ducts. 
     
     
         5 . The annular combustion chamber as claimed in  claim 4 , wherein the projections engaging in the ducts are of trapezoidal shape. 
     
     
         6 . The annular combustion chamber as claimed in either of  claim 4 , wherein the projections have a thermal barrier coating on surfaces exposed to hot gas. 
     
     
         7 . The annular combustion chamber as claimed in  claim 6 , wherein the interior of the outer shell has a thermal barrier coating in the region of the gap. 
     
     
         8 . The annular combustion chamber as claimed in  claim 2 , wherein the last row of heat-shield plates is metallic and the second-to-last row of heat shield plates is ceramic. 
     
     
         9 . A gas turbine having an annular combustion chamber as claimed in  claim 2 . 
     
     
         10 . The annular combustion chamber as claimed in  claim 1 , wherein the ring is comprised of a plurality of ring segments which together define the ring.