Turbine rotor blade of a gas turbine and method for cooling a blade tip of a turbine rotor blade of a gas turbine

Abstract

The present invention relates to a turbine rotor blade of a gas turbine with a blade tip, on which means for duct-type guidance of cooling air extending from a front suction-side area of the blade tip to a rear area of the blade tip are provided, and to a method for cooling a blade tip of a turbine rotor blade of a gas turbine, where air from a hot gas flow is guided from a front suction-side area of a blade tip to a rear area of the blade tip through a duct-type guidance.

1 . Turbine rotor blade of a gas turbine with a blade tip, on which means for duct-type guidance of cooling air extending from a front suction-side area of the blade tip to a rear area of the blade tip are provided. 
     
     
         2 . Turbine rotor blade in accordance with  claim 1 , wherein the means are provided at least over part of the length of the blade tip. 
     
     
         3 . Turbine rotor blade in accordance with  claim 1 , wherein the means for the inlet of cooling air from the hot gas flow are provided in the front suction-side area of the blade tip. 
     
     
         4 . Turbine rotor blade in accordance with  claim 1 , wherein the means for the outlet of cooling air are provided in the pressure-side area of the rear blade tip or in the suction-side area of the rear blade tip or in the area of the blade trailing edge. 
     
     
         5 . Turbine rotor blade in accordance with  claim 1 , wherein a sealing edge and/or an overhang are/is provided at the blade tip. 
     
     
         6 . Turbine rotor blade in accordance with  claim 1 , wherein the means are designed in the form of a cover arranged at the blade tip and forming a flow duct. 
     
     
         7 . Turbine rotor blade in accordance with  claim 1 , wherein the means are designed for the introduction of air exiting at least one air duct extending inside the turbine rotor blade. 
     
     
         8 . Turbine rotor blade in accordance with  claim 1 , wherein at least one web or support is provided at the blade tip for guiding the cooling air in the flow duct. 
     
     
         9 . Turbine rotor blade in accordance with  claim 6 , wherein the cover is arranged on the web. 
     
     
         10 . Method for cooling a blade tip of a turbine rotor blade of a gas turbine, where air from a hot gas flow is guided from a front suction-side area of a blade tip to a rear area of the blade tip through a duct-type guidance.