Abstract: A gas turbine vane or blade having a novel internal structure that allows for cooling under low pressure ratios. The vane has an air inlet passage that communicates with an inner cooling cavity positioned between the air passage and the vane's trailing edge. Disposed within this cavity are deflectors, turning members, ribs, and deflecting pins arranged so as to direct the cooling air through the cavity in a manner that minimizes pressure loss. Thus maintaining the velocity and flow of the cooling air.

Abstract: A turbine blade such as a rotor blade or stator vane in a gas turbine engine is provided of the type having an internal flow path for flow-through passage of a cooling gas stream, wherein the turbine blade includes a heat transfer surface designed for improved heat transfer with the cooling gas. The heat transfer surface comprises a regular pattern of turbulator vanes which extend generally transversely to the flow direction of the cooling gas stream, in combination with comparatively shorter heat transfer ribs which extend generally parallel to the gas stream flow direction. The pattern of turbulator vanes and heat transfer ribs provides significantly improved heat transfer between the turbine blade and the cooling gas stream, such that the cooling flow requirement is reduced to result in increased engine efficiency.

Abstract: Method and apparatus for delivering cooling fluid flow to the internal blade cooling passages in a gas turbine engine, wherein cooling flow is injected into a radial side face of the hub of the turbine wheel and is ported therefrom through internal passages in the hub to the blade internal cooling passages.