Abstract: A nozzle guide vane for a gas turbine engine includes an integrally formed angled nozzle with radially outer and inner platforms and an airfoil extending therebetween. An internal cooling air passage extends between the platforms. A cooling air outlet in the inner platform communicates with the air passage and opens to an inter stage cavity between stages of the engine and is formed as part of the nozzle with an outlet axis angled with respect to a radial direction of the engine. A transition area between a radially outwards facing part of the nozzle and an approximately linear outlet part including the outlet axis is formed as a curved conduit bend. An investment casting core member includes a cone-shaped part that defines the bend, a support part attached to the cone-shaped part and a cylindrical part which extends to the surface of the inner platform.

Abstract: The present invention relates to a gas turbine with a turbine stator wheel, which is fitted with stator vanes and includes a ring segment-shaped vane root, where the stator vanes are designed hollow and have a vane interior which can be supplied with cooling air, where a ring-shaped sealing element of an inter-stage seal is arranged radially on the inside, relative to an engine axis, on the vane root, where in the vane root at least one outflow duct is provided, characterized in that between the vane root and the sealing element an annular space extending substantially in the axial direction is formed, into which the outflow duct issues and which discharges into the area of the inter-stage seal.

Abstract: A nozzle guide vane for a gas turbine engine includes an integrally formed angled nozzle with radially outer and inner platforms and an airfoil extending therebetween. An internal cooling air passage extends between the platforms. A cooling air outlet in the inner platform communicates with the air passage and opens to an inter stage cavity between stages of the engine and is formed as part of the nozzle with an outlet axis angled with respect to a radial direction of the engine. A transition area between a radially outwards facing part of the nozzle and an approximately linear outlet part including the outlet axis is formed as a curved conduit bend. An investment casting core member includes a cone-shaped part that defines the bend, a support part attached to the cone-shaped part and a cylindrical part which extends to the surface of the inner platform.

Abstract: The present invention relates to a gas turbine with a turbine stator wheel, which is fitted with stator vanes and includes a ring segment-shaped vane root, where the stator vanes are designed hollow and have a vane interior which can be supplied with cooling air, where a ring-shaped sealing element of an inter-stage seal is arranged radially on the inside, relative to an engine axis, on the vane root, where in the vane root at least one outflow duct is provided, characterized in that between the vane root and the sealing element an annular space extending substantially in the axial direction is formed, into which the outflow duct issues and which discharges into the area of the inter-stage seal.