Effects of the multicavity tip coolant injection on the blade tip and the over tip casing aerothermal performance in a high-pressure turbine cascade

Figures & data

Figure 1. Overview of the first stage in GE-E3 turbine.

Table 1. Geometric and flow conditions.

Parameters	Values
Mainstream inlet total temperature/K	709
Mainstream inlet total pressure /KPa	344.74
Rotating speed (rpm)	8450
Vane count Vane count (zoomed)	46 38
Blade count	76
Inlet angles	0°
Inlet turbulence intensity	5%
Outlet pressure/KPa Coolant inlet total temperature/K	141.44 344
Mass Flow Rate (g*s^−1)	0.24
Another wall	Adiabatic wall

Figure 2. Overview of the structured mesh for the cavity tip.

Table 2. Numerical method.

Solution type	Steady
Fluid	Air (ideal gas)
Inlet boundary condition	Total Pressure, Total temperature
Outlet boundary condition	Average static pressure
Computational method	Time marching method
Discretization scheme	High resolution
Turbulence model	k − ω
Wall properties	Adiabatic, smooth surface

Figure 3. Validation of the numerical method.

Figure 4. Cavity tip definition.

Figure 5. Definition of the multicavity tip.

Figure 6. Film cooling effectiveness and streamlines on blade tip.

Figure 7. Area-averaged film cooling effectiveness on blade tip.

Figure 8. Flow structure and total temperature near the blade tip clearance.

Figure 9. Distribution of shear strain rate on the blade tip.

Figure 10. Vortex structure inside the tip cavity visualized by the Q-criterion.

Figure 11. Film cooling effectiveness and streamlines on over-tip casing.

Figure 12. Area-averaged film cooling effectiveness on over-tip casing.