Guide vane ring for a turbomachine and turbomachine

Abstract

The present invention relates to a guide vane ring ( 1 ) for a turbomachine, having a plurality of rotatable guide vanes ( 3 ), and having an inner ring ( 5 ), wherein the inner ring ( 5 ) has a seal ( 17 ) for sealing a radial gap between the inner ring ( 5 ) and an opposite-lying rotor segment ( 7 ), and wherein the inner ring ( 5 ) comprises at least two inner ring segments ( 11 ). The inner ring ( 5 ) is produced from a material or has a material that has a heat expansion coefficient α of less than 6*10 −6 per Kelvin in a temperature range between at least 20 degrees Celsius and 90 degrees Celsius. In addition, the present invention relates to a turbomachine having at least one guide vane ring ( 1 ) according to the invention.

What is claimed is: 
     
         1 . A guide vane ring ( 1 ) for a turbomachine, having a plurality of rotatable guide vanes ( 3 ), and having an inner ring ( 5 ), wherein the inner ring ( 5 ) has a seal ( 17 ) for sealing a radial gap between the inner ring ( 5 ) and an opposite-lying rotor segment ( 7 ), and wherein the inner ring ( 5 ) comprises at least two inner ring segments ( 11 ), wherein the inner ring ( 5 ) is produced from a material or has a material that has a heat expansion coefficient α of less than 6*10 −6  per Kelvin in a temperature range between at least 20 degrees Celsius and 90 degrees Celsius. 
     
     
         2 . The guide vane ring ( 1 ) according to  claim 1 , wherein the material of the inner ring ( 5 ) has a heat conductivity λ of greater than 10 watts per meter and per Kelvin at a temperature between 20 degrees Celsius and 25 degrees Celsius. 
     
     
         3 . The guide vane ring ( 1 ) according to  claim 1 , wherein the inner ring ( 5 ) comprises at least two divided inner ring segments ( 11 ) on the periphery of the inner ring ( 5 ). 
     
     
         4 . The guide vane ring ( 1 ) according to  claim 1 , wherein the material of the inner ring ( 5 ) is a nickel-alloyed steel. 
     
     
         5 . The guide vane ring ( 1 ) according to  claim 1 , wherein the material of the inner ring ( 5 ) comprises a nickel fraction of at least 25 weight percent. 
     
     
         6 . The guide vane ring ( 1 ) according to  claim 1 , wherein the material of the inner ring ( 5 ) comprises an iron fraction of at least 50 weight percent. 
     
     
         7 . The guide vane ring ( 1 ) according to  claim 1 , wherein the material of the inner ring ( 5 ) comprises a cobalt fraction of at least 10 weight percent. 
     
     
         8 . The guide vane ring ( 1 ) according to  claim 1 , wherein the material of the inner ring ( 5 ) has a heat expansion coefficient α of less than 6*10 −6  per Kelvin in a temperature range between at least 20 degrees Celsius and 500 degrees Celsius. 
     
     
         9 . The guide vane ring ( 1 ) according to  claim 1 , wherein the guide vane ring ( 1 ) is configured and arranged in a turbomachine. 
     
     
         10 . The guide vane ring ( 1 ) according to  claim 9 , wherein the turbomachine is an axial high-pressure compressor.