Blade for a rotating thermal machine

Abstract

A blade for a rotating thermal machine, such as a stator blade for a low-pressure turbine of a gas turbine with sequential combustion, includes a blade airfoil which extends essentially in the radial direction, is exposed to circumflow by an operating medium in a flow direction, and is delimited by a leading edge and a trailing edge in the flow direction. The concurring fluidic and constructional demands on the blade with sharp inclination of the flow are met by the blade airfoil being structured in such a way that an angle which the flow lines form with the trailing edge of the blade airfoil deviates from a right angle within a limited range.

1 . A blade for a rotating thermal machine, the blade comprising:
 a blade airfoil which extends essentially in a radial direction, is exposed to circumflow by an operating medium in a flow direction, and is delimited by a leading edge and a trailing edge in the flow direction,   wherein the blade airfoil is structured such that an angle which flow lines of the operating medium form with a shape of the trailing edge of the blade airfoil deviates within a limited range from a 90°-angle.   
     
     
         2 . The blade as claimed in  claim 1 , wherein the angle which the flow lines form with the trailing edge of the blade airfoil is less than 90°. 
     
     
         3 . The blade as claimed in  claim 1 , wherein the angle which the flow lines form with the trailing edge of the blade airfoil is more than 90°. 
     
     
         4 . The blade as claimed in  claim 2 , wherein the deviation of the angle which the flow lines form with the trailing edge of the blade airfoil lies within the range of between 0° and −10°. 
     
     
         5 . The blade as claimed in  claim 3 , wherein the deviation of the angle which the flow lines form with the trailing edge of the blade airfoil lies within the range of between 0° and +10°. 
     
     
         6 . The blade as claimed in  claim 4 , wherein the deviation of the angle which the flow lines form with the trailing edge of the blade airfoil lies within the range of between 0° and −5° over a largest area of a height of the blade airfoil. 
     
     
         7 . The blade as claimed in  claim 5 , wherein the deviation of the angle which the flow lines form with the trailing edge of the blade airfoil lies within the range of between 0° and +5° over a largest area of a height of the blade airfoil. 
     
     
         8 . The blade as claimed in  claim 1 , wherein the blade is a stator blade. 
     
     
         9 . A gas turbine comprising the stator blade as claimed in  claim 8 . 
     
     
         10 . A gas turbine generator set with sequential combustion, the gas turbine generator set comprising the gas turbine as claimed in  claim 9 . 
     
     
         11 . The blade as claimed in  claim 1 , wherein the blade has a twisted geometry. 
     
     
         12 . The blade as claimed in  claim 4 , wherein the blade is a stator blade. 
     
     
         13 . A gas turbine comprising the stator blade as claimed in  claim 12 . 
     
     
         14 . The blade as claimed in  claim 5 , wherein the blade is a stator blade. 
     
     
         15 . A gas turbine comprising the stator blade as claimed in  claim 14 . 
     
     
         16 . The blade as claimed in  claim 6 , wherein the blade is a stator blade. 
     
     
         17 . A gas turbine comprising the stator blade as claimed in  claim 16 . 
     
     
         18 . The blade as claimed in  claim 7 , wherein the blade is a stator blade. 
     
     
         19 . A gas turbine comprising the stator blade as claimed in  claim 18 . 
     
     
         20 . The blade as claimed in  claim 8 , wherein the stator blade has a twisted geometry.