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Turbine airfoil cooling system with rotor impingement cooling

Image Number 2 for United States Patent #8128365.

A turbine airfoil cooling system of a turbine engine having a hollow, disc post body positioned between adjacent roots of turbine airfoils and aligned with the roots to cool inner aspects of the turbine engine. The hollow, disc post body may be configured to pass cooling fluids through impingement orifices in the hollow, disc post body to impinge on inner surfaces of platforms of the turbine airfoils. The cooling fluids may then be directed to the internal cooling systems of the turbine airfoils rather than being discharged as film cooling fluids through the platforms of the turbine airfoils.

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