Inlet coating for gas turbines

Abstract

An abradable coating for gas turbines is provided. The abradable coating is used for sealing a radial gap between a casing ( 11 ) of the gas turbine and rotating blades ( 10 ) of the same. The abradable coating ( 13 ) is applied to the casing. The abradable coating ( 13 ) is at least single-layered, at least one outer layer of the abradable coating ( 13 ) being produced from a material having a magnetoplumbite structure, preferably lanthanum hexaaluminate.

1 - 7 . (canceled)  
   
   
       8 . An abradable coating for application to a casing of a gas turbine, comprising a coating produced from a material having a magnetoplumbite structure.  
   
   
       9 . The abradable coating as recited in  claim 8 , wherein the material is produced from lanthanum hexaaluminate.  
   
   
       10 . The abradable coating as recited in  claim 8 , wherein the abradable coating is a single-layer coating, and wherein the only layer of the single layer coating abradable coating is produced from lanthanum hexaaluminate.  
   
   
       11 . The abradable coating as recited in  claim 8 , wherein the abradable coating is a multi-layered coating, and an outermost layer of the abradable coating is produced from lanthanum hexaaluminate.  
   
   
       12 . The abradable coating as recited in  claim 11 , wherein the multi-layered coating includes an interior layer, disposed between the outer layer of lanthanum hexaaluminate and a casing to which the coating is applied.  
   
   
       13 . The abradable coating as recited in  claim 12 , wherein the interior layer is an adhesion-promoting layer.  
   
   
       14 . The abradable coating as recited in  claim 12 , wherein the multi-layered coating further includes an intermediate layer of zirconium dioxide disposed between the interior layer and the outer layer of lanthanum hexaaluminate.  
   
   
       15 . A gas turbine comprising 
 a plurality of rotating blades,    a casing enclosing the plurality of rotating blades; and    an abradable coating on the casing, the abradable coating sealing a radial gap between the casing and the rotating blades, wherein the coating is produced from a material having a magnetoplumbite structure.    
   
   
       16 . The gas turbine as recited in  claim 15 , wherein the material is produced from lanthanum hexaaluminate.  
   
   
       17 . The gas turbine as recited in  claim 15 , wherein the abradable coating is a single-layer coating, and wherein the only layer of the single layer coating abradable coating is produced from lanthanum hexaaluminate.  
   
   
       18 . The gas turbine as recited in  claim 15 , wherein the abradable coating is a multi-layered coating, and an outermost layer of the abradable coating is produced from lanthanum hexaaluminate.  
   
   
       19 . The gas turbine as recited in  claim 18 , wherein the multi-layered coating includes an interior layer, disposed between the outer layer of lanthanum hexaaluminate and the casing.  
   
   
       20 . The gas turbine as recited in  claim 19 , wherein the interior layer is an adhesion-promoting layer.