The heat transfer performance of internal cooling passages inside gas turbine vanes and blades is one of

importance to the design engineers because higher cooling effectiveness generally allows increased turbine

temperatures, which increases its efficiency.

For design optimization of high temperature turbines, CFD tools are widely used. But it should be noted that each

calculation is connected with huge computation problems. And in order to overcome them experts with high

qualifications are required. In the meantime design of the construction is the responsibility of design engineers

who do not generally have the expertise in computation fluid dynamics. So, there is growing needs for design

engineers to have a CFD tool. This CFD tool should work together with the CAD system, be reliable, robust, give the

same quality of the results as other CFD tools and does not require a high qualification in CFD.

This paper presents the results of CAD-Embedded, CFD software FloEFD for evaluation of the thermal and

temperature conditions of vanes and blades. The FloEFD approach is based on two main principles: direct use of

native CAD as the source of geometry information; and synergy of full 3D CFD modeling, combined with simpler

engineering methods in cases where the mesh resolution is insufficient for a full 3D simulation.

To validate the CFD code in the field of heat transfer in gas turbine vanes and blades three independent

experiments are selected. For each case consideration is given to particular parameters of conjugate heat transfer

which is computed and compared with published tests.

Firstly, temperature and heat transfer coefficient in the real test conditions for a vane with profile C3X are

calculated. In the second case, convective heat transfer on the steam turbine vane is considered. The temperature

distribution in the vane is evaluated. The specificity of the case, is that the experimental test rig represents a

rectangular duct containing a three-vane cascade. In the third, FloEFD simulation, of film-cooled first-stage turbine

vanes are presented. Relatively simple geometry of the model allows you to demonstrate the contribution of the

film effect to the cooling process.

Finally, a numerical calculation for real industrial high-pressure turbine blades is performed. Complicated internal

cooling systems, includes channels filled with intensifiers. By taking the inlet gas parameters setting, circumferential

distortion is taken into account. The cooling air flowing out of the axial clearance is also considered in the

calculation.