Abstract
In order to achieve high process efficiencies for the economic
operation of stationary gas turbines and aero engines, extremely
high turbine inlet temperatures at adjusted pressure ratios are
applied. The allowable hot gas temperature is limited by the
material temperature of the hot gas path components, in particular
the vanes and blades of the turbine. Thus, intensive cooling is
required to guarantee an acceptable life span of these components.
Modern computational tools as well as advanced calculation
methods support essentially on the successful design of these
thermally high-loaded components. The homogeneous, or
sometimes also mentioned as “full”, conjugate calculation
technique for the coupled calculation of fluid flows, heat transfer
and heat conduction is such an advanced numerical approach in the
design process and huge experiences on validation and application
have been collected throughout the years. This paper summarizes
the numerical approach for this method as well as provides a
collection of numerical results obtained by the authors for
validation cases for a convection-cooled turbine vane test case as
well as comparison to calculation data for this test case provided in
open literature. Furthermore, systematic studies on the impact of
calculation parameters, e.g. hot gas fluid properties, and numerical
models for turbulence calculation are performed and the numerical
results are compared to the experimental results of the test case.
