US2011189014A1PendingUtilityA1

Gas turbine and method for varying the aerodynamic shape of a gas turbine blade

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Assignee: MTU AERO ENGINES GMBHPriority: Jul 18, 2008Filed: Jul 17, 2009Published: Aug 4, 2011
Est. expiryJul 18, 2028(~2 yrs left)· nominal 20-yr term from priority
Inventors:Sven-J. Hiller
F04D 29/542F04D 29/023F04D 29/563F01D 5/148Y02T50/60F01D 5/141F05D 2300/611F05D 2300/505F05D 2230/90
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Claims

Abstract

A gas turbine and a method for varying the aerodynamic shape of a blade of the gas turbine is disclosed. The blade has a coating made of a shape-memory alloy. Hot air is transported via channels to the coated blade in order to cause a phase change in the coating and an aerodynamic shape change to the blade.

Claims

exact text as granted — not AI-modified
1 - 11 . (canceled) 
     
     
         12 . A gas turbine, comprising:
 a blade, wherein the blade includes a phase-changeable shape-memory alloy and wherein the shape-memory alloy is a coating on the blade; and   a channel, wherein the channel directs hot air and wherein the channel ends at the blade.   
     
     
         13 . The gas turbine according to  claim 12 , wherein the coating is on an outer side of the blade. 
     
     
         14 . The gas turbine according to  claim 12 , wherein the blade is a compressor blade. 
     
     
         15 . The gas turbine according to  claim 12 , wherein the channel starts from a downstream compressor stage and directs hot air upstream from the downstream compressor stage. 
     
     
         16 . The gas turbine according to  claim 12 , wherein the channel ends at a housing. 
     
     
         17 . The gas turbine according to  claim 12 , wherein the channel discharges into an interior of the blade and wherein hot air is blowable into the blade. 
     
     
         18 . The gas turbine according to  claim 12 , wherein the blade is a guide blade and/or a rotor blade. 
     
     
         19 . The gas turbine according to  claim 12 , wherein a variable guide baffle is not provided in the gas turbine. 
     
     
         20 . The gas turbine according to  claim 12 , wherein the blade is made of a metal alloy. 
     
     
         21 . A method for varying an aerodynamic shape of a blade of a gas turbine, comprising the steps of:
 conveying hot air on a shape-memory alloy coated on the blade; and   causing a phase change of the shape-memory alloy by the conveyed hot air.   
     
     
         22 . The method according to  claim 21 , wherein the hot air is hot compressor air.

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