Blade and gas turbine

Abstract

The invention relates to a turbomachine, in particular to a gas turbine and to a method for accelerating a temperature modification of a rotor shaft rotationally mounted in said turbomachine. The aim of said invention is to develop a device and a method for the turbomachine making it possible to reduce the size of a radial split of the turbomachine in order to obtain greater degree of efficiency. The inventive turbomachine comprises a rotor rotationally mounted in the case of the turbomachine, a feeding channel embodied in the rotor for introducing a fluid and an outlet channel embodied in the rotor for removing said fluid. An inlet orifice of the feeding channel is disposed further inside than the outlet orifice of the outlet channel, and means influencing a liquid flow is formed of an actuating device dependent on centrifugal force. Methods for cooling the rotor only by decelerating the gas turbine and for heating the turbomachine rotor by heating fluid flowing therethrough are also disclosed.

1 - 14 . (canceled) 
   
   
       15 . A blade for use in a turbomachine, comprising:
 a blade root;   a platform region; and   a main blade part having a blade length from a blade leading edge to a blade trailing edge and a blade height from the platform region to a main blade part tip and that is formed from at least one base body segment and in the region of at least one of two blade edges and from at least one edge segment that is connected in a positively locking manner to the base body segment,   wherein in that the positively locking connection is produced by means of projections which are formed integrally on one of the segments and are spaced apart from one another in the direction of the blade height, with the other segment at least partially arranged projecting in between the projections.   
   
   
       16 . The blade as claimed in  claim 15 , wherein the base body segment and the edge segment each have a plurality of projections with recesses between the projections and in that the projections arranged on one of the two segments project in a positively locking manner into the opposite recesses in the other segment forming positively locking toothing. 
   
   
       17 . The blade as claimed in  claim 15 , wherein a pin-like holding element that extends in the direction of the blade edge secures the segments against relative movements by the holding element penetrating transversely through the projections of both segments. 
   
   
       18 . The blade as claimed in  claim 15 , wherein the segments are made from different materials. 
   
   
       19 . The blade as claimed in  claim 15 , wherein at least one segment is made from a particularly thermally conductive material. 
   
   
       20 . The blade as claimed in  claim 15 , wherein at least one segment is made from a material which is resistant to high temperatures. 
   
   
       21 . The blade as claimed in  claim 15 , wherein at least one segment is made from a ceramic material. 
   
   
       22 . The blade as claimed in  claim 15 , wherein at least one segment is made from a metal and/or a metal alloy. 
   
   
       23 . The blade as claimed in  claim 15 , wherein at least one segment is made from a plastic material. 
   
   
       24 . The blade as claimed in  claim 15 , wherein the segments are coated. 
   
   
       25 . The blade as claimed in  claim 15 , wherein at least one segment has a cavity. 
   
   
       26 . The blade as claimed in  claim 25 , wherein the cavity is filled with a material that is different from the segment material. 
   
   
       27 . The blade as claimed in  claim 15 , wherein the blade is designed as a guide vane or as a rotor blade. 
   
   
       28 . A gas turbine, comprising:
 a compressor element;   a combustion element;   a turbine element,   wherein the turbine element has a plurality of blades, the blades comprising;
 a blade root, 
 a platform region, and 
 a main blade part having a blade length from a blade leading edge to a blade trailing edge and a blade height from the platform region to a main blade part tip and that is formed from at least one base body segment and in the region of at least one of two blade edges and from at least one edge segment that is connected in a positively locking manner to the base body segment, 
 wherein in that the positively locking connection is produced by means of projections which are formed integrally on one of the segments and are spaced apart from one another in the direction of the blade height, with the other segment at least partially arranged projecting in between the projections. 
   
   
   
       29 . The gas turbine as claimed in  claim 28 , wherein the blades have at least one segment that has a cavity. 
   
   
       30 . The gas turbine as claimed in  claim 29 , wherein the cavity is filled with a material that is different from the segment material.