US2014030109A1PendingUtilityA1

low-Modulus Gas-Turbine Compressor Blade

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Assignee: ROLLS ROYCE DEUTSCHLANDPriority: Jul 30, 2012Filed: Jul 30, 2013Published: Jan 30, 2014
Est. expiryJul 30, 2032(~6 yrs left)· nominal 20-yr term from priority
Inventors:Karl Schreiber
F04D 29/324F01D 5/28F05D 2240/303F01D 5/288F01D 5/147
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Claims

Abstract

The present invention relates to an aircraft gas-turbine compressor blade having an airfoil with a leading edge, with at least the area of the leading edge being made from a low-modulus titanium alloy.

Claims

exact text as granted — not AI-modified
1 . Gas-turbine compressor blade having an airfoil with a leading edge, with at least the area of the leading edge being made from a low-modulus titanium alloy. 
     
     
         2 . Compressor blade in accordance with  claim 1 , characterized in that at least the area of the leading edge is made from Ti-28Nb-1Fe-0.5Si or Ti-36Nb-2Ta-3Zr-0.3O or Ti-24Nb-4Zr-8Sn. 
     
     
         3 . Compressor blade in accordance with  claim 1 , characterized in that the leading edge is designed in the form of a leading-edge element which is connected to the airfoil by means of a welding process. 
     
     
         4 . Compressor blade in accordance with  claim 3 , characterized in that the leading-edge element is connected to the airfoil by means of a laser welding process. 
     
     
         5 . Compressor blade in accordance with  claim 1 , characterized in that the area of the leading edge has a modulus of elasticity of substantially 50 to 70 GPa. 
     
     
         6 . Compressor blade in accordance with  claim 1 , characterized in that the airfoil is made from Ti64 or Ti6246 or Ti6242 or IN718. 
     
     
         7 . Compressor blade in accordance with  claim 1 , characterized in that the compressor blade is designed as a conventional compressor blade. 
     
     
         8 . Compressor blade in accordance with  claim 1 , characterized in that the compressor blade is designed as a fan blade. 
     
     
         9 . Compressor blade in accordance with  claim 1 , characterized in that the compressor blade is designed as a blisk blade.

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