Casing for a turbomachine, installation safeguard and turbomachine

Abstract

Disclosed is a casing of a turbomachine which comprises at least a first casing portion comprising a first material having a first coefficient of thermal expansion and a second casing portion comprising a second material having a second coefficient of thermal expansion. The second casing portion comprises a casing structuring with flow-guiding elements and is connected in a force-fitting manner to the first casing portion by a radial press fit. Also disclosed are an installation safeguard and a turbomachine comprising the casing.

What is claimed is: 
     
         1 . A casing of a turbomachine, wherein the casing comprises at least a first casing portion comprising a first material having a first coefficient of thermal expansion (α 1 ) and a second casing portion comprising a second material having a second coefficient of thermal expansion (α 2 ), the second casing portion comprising a casing structuring with flow-guiding elements and being connected in a force-fitting manner to the first casing portion by a radial press fit. 
     
     
         2 . The casing of  claim 1 , wherein the second coefficient of thermal expansion (α 2 ) is different from the first coefficient of thermal expansion (α 1 ). 
     
     
         3 . The casing of  claim 2 , wherein the second coefficient of thermal expansion (α 2 ) is higher than the first coefficient of thermal expansion (α 1 ). 
     
     
         4 . The casing of  claim 1 , wherein the first coefficient of thermal expansion (α 1 ) is lower than or equal to 10×10 −6  per Kelvin in a temperature range of from at least 20 degrees Celsius to 90 degrees Celsius. 
     
     
         5 . The casing of  claim 1 , wherein the second coefficient of thermal expansion (α 2 ) is higher than 10×10 −6  per Kelvin in a temperature range of from at least 20 degrees Celsius and 90 degrees Celsius. 
     
     
         6 . The casing of  claim 4 , wherein the second coefficient of thermal expansion (α 2 ) is higher than 10×10 −6  per Kelvin in a temperature range of from at least 20 degrees Celsius and 90 degrees Celsius. 
     
     
         7 . The casing of  claim 1 , wherein the first material is or comprises a titanium alloy. 
     
     
         8 . The casing of  claim 1 , wherein the second material is or comprises a titanium alloy or a steel. 
     
     
         9 . The casing of  claim 8 , wherein the second material is or comprises a titanium alloy or a steel. 
     
     
         10 . The casing of  claim 1 , wherein the flow-guiding elements are integrally connected to the casing structuring. 
     
     
         11 . The casing of  claim 1 , wherein the second casing portion is in one part or in one piece. 
     
     
         12 . The casing of  claim 1 , wherein the second casing portion is segmented in multiple parts in circumferential direction. 
     
     
         13 . The casing of  claim 1 , wherein the first casing portion is an axially split casing portion of the casing of the turbomachine. 
     
     
         14 . An installation safeguard, wherein the safeguard comprises the casing of  claim 1  and wherein the first casing portion comprises an axial delimitation for positioning the second casing portion as an installation safeguard of the second casing portion with respect to the first casing portion. 
     
     
         15 . The installation safeguard of  claim 14 , wherein the axial delimitation is a radial step. 
     
     
         16 . The installation safeguard of  claim 14 , wherein the second casing portion comprises at least one radially offset portion, which extends beyond the axial delimitation of the first casing portion. 
     
     
         17 . A turbomachine, wherein the turbomachine comprises the casing of  claim 1 . 
     
     
         18 . The turbomachine of  claim 17 , wherein the turbomachine is a compressor. 
     
     
         19 . The turbomachine of  claim 18 , wherein the compressor is a high-pressure compressor. 
     
     
         20 . The turbomachine of  claim 17 , wherein the turbomachine is an aero engine.