Turbine blade or a turbine vane for a gas turbine
A turbine blade or vane for a gas turbine has successively along a radial direction of the gas turbine, a root for attaching the turbine blade or vane to a carrier, a platform, an aerodynamically shaped hollow airfoil with a suction side wall and a pressure side wall extending with respect to the di...
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Main Authors | , |
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Format | Patent |
Language | English |
Published |
06.07.2021
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Subjects | |
Online Access | Get full text |
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Abstract | A turbine blade or vane for a gas turbine has successively along a radial direction of the gas turbine, a root for attaching the turbine blade or vane to a carrier, a platform, an aerodynamically shaped hollow airfoil with a suction side wall and a pressure side wall extending with respect to the direction of a hot gas flow from a common leading edge to common a trailing edge and extending transversely thereof from the platform to an airfoil tip. The airfoil has at least one cooling cavity extending in a cooling fluid flow direction from a platform level to the airfoil tip, the cooling cavity in fluid connection with a number of cooling fluid outlets distributed along the trailing edge through an array of impingement cooling features located therebetween. The array extends into a region which is located radially outside the airfoil within the platform having impingement cooling features. |
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AbstractList | A turbine blade or vane for a gas turbine has successively along a radial direction of the gas turbine, a root for attaching the turbine blade or vane to a carrier, a platform, an aerodynamically shaped hollow airfoil with a suction side wall and a pressure side wall extending with respect to the direction of a hot gas flow from a common leading edge to common a trailing edge and extending transversely thereof from the platform to an airfoil tip. The airfoil has at least one cooling cavity extending in a cooling fluid flow direction from a platform level to the airfoil tip, the cooling cavity in fluid connection with a number of cooling fluid outlets distributed along the trailing edge through an array of impingement cooling features located therebetween. The array extends into a region which is located radially outside the airfoil within the platform having impingement cooling features. |
Author | Gossilin, Ralph Heselhaus, Andreas |
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RelatedCompanies | Siemens Energy Global GmbH & Co. KG Siemens Aktiengesellschaft |
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Snippet | A turbine blade or vane for a gas turbine has successively along a radial direction of the gas turbine, a root for attaching the turbine blade or vane to a... |
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SubjectTerms | BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS |
Title | Turbine blade or a turbine vane for a gas turbine |
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