Gas turbine blade/guiding blade

Abstract

The turbine blade (1) has a blade section (2) supplied with a cooling medium (K), e.g. air, flowing in the direction of the blade, axis via flow and return channels (6,8) extending over its full length. The flow and return channels are coupled together so that the cooling medium flows between them in a transverse direction across an internal partition wall (16) of the blade section.

Description

technical field [0001] The invention relates to a gas turbine blade / guide vane system, which has, essentially in the longitudinal direction of the steam turbine blade / guide vane, a blade / guide vane profile extending along the blade / guide vane axis and through which a cooling medium can flow. Background technique [0002] Gas turbines are used in many fields to drive electrical generators or other machinery. In this process, the energy content of the fuel is used to cause the turbine shaft to turn. To achieve this, fuel is burned in the combustion chamber, while compressed air is supplied from an air compressor. In this process, the high-temperature and high-pressure working fluid generated by the combustion of fuel in the combustion chamber is sent through a steam turbine unit connected downstream of the combustion chamber, where the gas expands and power is output. [0003] To turn the steam turbine in the process, a plurality of rotor blades, usually combined into blade ...

AI Technical Summary

Problems solved by technology

However, in view of the limited mechanical load-carrying capacity of the individual components of a gas turbine, the design power of a gas turbine cooled in this way is limited since a further increase in power can generally only be achieved by increasing the fuel supply

This in turn leads to a relative increase in the cooling medium requirement for cooling the turbine blades / guide vanes, which in turn results in a significant loss of available compressor mass flow

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